CA2138672C - Single crystal nickel-based superalloy - Google Patents

Single crystal nickel-based superalloy

Info

Publication number
CA2138672C
CA2138672C CA002138672A CA2138672A CA2138672C CA 2138672 C CA2138672 C CA 2138672C CA 002138672 A CA002138672 A CA 002138672A CA 2138672 A CA2138672 A CA 2138672A CA 2138672 C CA2138672 C CA 2138672C
Authority
CA
Canada
Prior art keywords
percent
cmsx
alloy
ksi
creep
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
CA002138672A
Other languages
French (fr)
Other versions
CA2138672A1 (en
Inventor
Gary L. Erickson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Cannon Muskegon Corp
Original Assignee
Cannon Muskegon Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Cannon Muskegon Corp filed Critical Cannon Muskegon Corp
Publication of CA2138672A1 publication Critical patent/CA2138672A1/en
Application granted granted Critical
Publication of CA2138672C publication Critical patent/CA2138672C/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C19/00Alloys based on nickel or cobalt
    • C22C19/03Alloys based on nickel or cobalt based on nickel
    • C22C19/05Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C19/00Alloys based on nickel or cobalt
    • C22C19/03Alloys based on nickel or cobalt based on nickel
    • C22C19/05Alloys based on nickel or cobalt based on nickel with chromium
    • CCHEMISTRY; METALLURGY
    • C30CRYSTAL GROWTH
    • C30BSINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B11/00Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
    • CCHEMISTRY; METALLURGY
    • C30CRYSTAL GROWTH
    • C30BSINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B29/00Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
    • C30B29/10Inorganic compounds or compositions
    • C30B29/52Alloys

Abstract

This invention relates to a single crystal casting to be used under high stress, high temperature conditions up to about 2030 ° F characterized by an increased resistance to creep under such conditions. The casting is made from a nickel-based superalloy consisting essentially of the following elements in percent by weight: from 6.2 to 6.8 percent rhenium, from 1.8 to 2.5 percent chromium, from 1.5 to 2.5 percent cobalt, from 8.0 to 9.0 percent tantalum, from 3.5 to 6.0 percent tungsten, from 5.5 to 6.1 percent aluminum, from 0.1 to 0.5 percent titanium, from 0.01 to 0.1 percent columbium, from 0.25 to 0.60 percent molybdenum, from 0 to 0.05 percent hafnium, from 0 to 0.04 percent carbon, from 0 to 0.01 percent boron, from 0 to 0.01 percent yttrium, from 0 to 0.01 percent cerium, from 0 to 0.01 percent lanthanum, from 0 to 0.04 percent manganese, from 0 to 0.05 percent silicon, from 0 to 0.01 percent zirconium, from 0 to 0.001 percent sulfur, from 0 to 0.10 percent vanadium, and the balance nickel + incidental impurities. The superalloy has a phasial stability number N V3B less than about 1.65.

Description

2 1 ~8 ~ 2 PCr/US93/06213 '-SINGLE C~YSTAL NICKEL-BASED SUPERALLOY
BACKGROUND OF THE INVENTION
1. Field of the Invention This invention relates to single crystal nickel-based sllr~ ys and, more particularly, single crystal nickel-based snr~ lloys and articles made LL~,~er~ for use in advanced gas turbine engines under high stress, high ~ .c-~ confliti-m~.
2. Desç~ ;o~ of the PAor Art A~lvd~lces over recent years in t~e rnetal ~ e-"l~ , and stress capability of single cryst~l articles have been the result of the cn--l;----;--g development of single crystal snrP~r~lloys, as well as ~l~e~ Ls in casting ~loce~s and engine ~ l;on t~-hnnl~gy. These single crystal snr~ralloy articles include lok~Lillg and ~
turbine blades and vanes found in the hot sections of gas turbine ~onginPs. However, gas turbine engine design goals have l. ~--~;-.''A the same during the past ~ s These goals include the desire to i~ ase engine o~ t~- ..l ~,.l...~" r~ "~l speed, thrust-to-weight ratio, fuel erri~ --y, and engine c{~ o.~"L durability and reliability.
The basic t~hnnlogy of alloys for the casting of single crystal cO~ o.~ L~ is de~s~rihe~l in U.S. Patent Nos. 3,494,709; 4,116,723 and 4,209,348. Development work resulted in first g. .~P,dl;on nickel-based snro,r~lloys, which were m~t~ri~lly ~lVV~l over those Aesr.i~A in the ~fol~ l;o"rA patents. However, these first ~,., .~ ,.1;-~.. nickel-based superalloys c~.. l~;.. ~A no ,1.~.. ;... Fx~mpllos of such first ge.~f.i.linn nickel-based S~ lO-ys~ CrJ~ f,cially known as CMSX-2 alloy and CMSX-3 alloy produced by C~nnon-M..~ oll Col~l~Lion, ~ign~e of the present appli~tion, are descriherl in U.S.
Patent No. 4,582,S48. Further development work resulted in second ~ dlion nickel-based s~lpe~lloys hav~ng Lllv~.~d creep ~ /creep rate. These second genc.d~ion nickel-based superalloys have a m~ te rh~nillm content of about 3 weight percent. An example of such a second generation nickel-based superalloy is described in U.S. Patent No 4,643,782. This patent discloses a superalloy, commercially known as CMSX~
alloy, having a specific nickel-based composition incl~ ing a rh~nillm content in the range of 2.8-3.2 weight percent. The present invention provides the next generation of nickel-based superalloys having higher total refractory element (W+Re+Mo+Ta) content and improved m~h~nic~l properties Single crystal articles are generally produced having the low-modulus (001) crystallographic orientation parallel to the component f1-~nclritic growth pattern or blade * tralie-mark A

. .

WO 94/00611 ~ PCI/US93/06213 ~ 7 ~ 2 sf~rl~ing axis. Face-centered cubic (FCC) superalloy single crystals grown in the (001) direction provide extremely good thermal fatigue rçci~t~nre relative to conventionally cast articles. Since these single crystal articles have no grain bonn~l~rilo~, alloy design without grain boundary stren~lhe~ , such as carbon, boron and zirconium, is possible. As these elements are alloy melting point de~.l,s~allL~, their reduction from an alloy design provides a greater potential for high Ic~ cldlulc m~rh~nir~1 ~Ll~,~lh achicvc Iclll since more complete gamma prime solution and microstructural homogel~-~aLion can be achieved relative to directionally solidified (DS) columnar grain and conventionally cast materials. Their reduction also makes possible a higher hlci~icllL melting Lcl~p~,lalulc.
These process bellcrlL~ are not nrces~rily realized unless a multi-faceted alloydesign approach is undertaken. Alloys must be de~ign~d to avoid tendency for casting defect formation such as freckles, slivers, spurious grains and l~c~ly~ 11i7~tinn.
Additionally, the alloys must provide an adequate heat LL.~ I window (numeric dirrelcnce beLwecll an alloy's gamma prime solvus and incipient melting point) to allow for nearly complete gamma prime solutioning. At the same time, the alloy compo~ition~1 balance should be design~d to provide an adçql~tr blend of cl~ elillg ~ y~lLies ~-rcee~,.,y for operation in gas turbine engines. Selected ~ pelLies gen~r~lly considered hll~ull~L by gas turbine engine designers include: elevated Lc IpCldlUlC creep-rupture strength, thermo-mrrh~nir~1 fatigue r~si~t~nre, impact rcsi~L~ce plus hot corrosion and oxidation l~ci~ re.
An alloy designer can attempt to improve one or two of these design l~rupcllies by adjusting the compositional balance of known superalloys. However, it is c~ ,llely difficult to improve more than one or two of the design ~lupcllies without ~i~nific~ntly or even severely cc,llll)rolllisillg the rlom~ining ylu~cllies. The unique superalloy of the present invention provides an excellent blend of the pl~opclLies nPce~ry for use in producing single crystal articles for operation in gas turbine engine hot sections.
SUMMARY OF THE INVENTION
This invention relates to a nickel-based superalloy comprising the following elements in percent by weight: from about 5.0 to about 7.0 percent rhPni1lm, from about 1.8 to about 4.0 percent clllullliulll, from about 1.5 to about 9.0 percent cobalt, from about 7.0 to about 10.0 percent t~nt~lllm, from about 3.5 to about 7.5 percent tungsten, from about 5.0 to about 7.0 percent ~I~,.,,i,""", from about 0.1 to about 1.2 percent S!J~lTUTE S~!~ET

WO94/00611 ~ 2 - , ' , -lil;.l,i,.,l" from about 0 to about 0.5 percent columbium, from about 0.25 to about 2.0 percent molyb~len~m, from about 0 to about 0. lS percent h~fnillm, and the balance nickel ~ plus incidental i.~.~uliLies, the superalloy having a p_asial stability number NV3B less than about 2.10.
Advantageously, this superalloy composition may be further cc,~ liscd of (pelccllldges are in weight percent) from about 0 to about 0.04 percent carbon, from about 0 to about O.Ol percent boron, from about 0 to about O.Ol percent yttrium, from about 0 to about O.Ol percent cerium and from about 0 to about O.Ol percent 1 "Ih~"......
Although incidental illl~uli~ies should be kept to the least amount possible, the superalloy can also be culll~lised of from about 0 to about 0.04 percent ~ n~ ese~ from about 0 to about 0.05 percent silicon, from about 0 to about O.Ol percent zirconium, from about 0 to about 0.001 percent sulfur, and from about 0 to about O.lO percent v~n~ lm In all cases, the base element is nickel. Fullllcllllore, this superalloy can advantageously have a phasial stability number NV3B less than about 1.85, and a chlullliulll content of from about 1.8 to about 3.0 percent, a .l..-~.i..,.. content of from about S.5 to about 6.5 percent, and a cobalt content of from about 2.0 to about 5.0 percent. This invention provides a superalloy having an increased l~ re to creep under high stress, high tclll~eldLconditions, particularly up to about 2030~F.
In one ~l~,rt;ll~d embo-limPnt this invention relates to a single crystal casting to be used under high stress, high ~lll~ela~ule conditions up to about 2030~F characterized by an increased reei~t~n-e to creep under such conditions. In this emborlim~nt, the casting is made from a nickel-based superalloy co~ .Li~ essentially of the following elem~nt~ in percent by weight: from 6.2 to 6.8 percent .l.~l.i-.-.., from 1.8 to 2.5 percent ch UllliUlll, from 1.5 to 2.5 percent cobalt, from 8.0 to 9.0 percent t~nt~lum, from 3.5 to 6.0 percent tungsten, from 5.5 to 6.1 percent ~ll--"i"---.., from O.l to 0.5 percent lil~--i-----, from O.Ol to O.l percent columbium, from 0.25 to 0.60 percent molybdenum, from 0 to 0.05 percent h~fnillm, from 0 to 0.04 percent carbon, from 0 to O.Ol percent boron, from 0 to O.Ol percent yttrium, from 0 to O.Ol percent cerium, from 0 to O.Ol percent 1~ -------, from 0 to 0.04 percent m~ng~n.ose, from 0 to 0.05 percent silicon, from 0 to O.Ol percent zirconium, from 0 to O.OOl percent sulfur, from 0 to O.lO percent v~n~-lil-m, and the balance nickel + inri-l~nt~l illl~uliLies, wh~ cill the superalloy has a phasial stability llulllbcl NV3B less than about 1.65.

SUB~llllllt SHEET

Wo 94/00611 Pcr/us93/o62l3 Single crystal articles can be suitably made from the snperAIIny of this invention.
The article can be a component for a turbine engine and, more particularly, the colllpo~ellt can be a gas turbine blade or gas turbine vane.
The superalloy compositions of this invention have a critically bAI~nre-l alloy ch~ y which results in a unique blend of desirable ~lu~Lies. These ~ Lies include: e~rellent single crystal colll~ollc..t castabiliy, particularly for moderately sized blade and vane conl~olle~L~ qll~t~ cast culll~oncl~L solutionability; ex~ nt le~ .n~e to single crystal cast colll~o~cnL lc~ly~ lli7Atic)n; ultra-high creep-rupture ~Llc~Lh to about 2030~F; c~Llclllcly good smooth and nntrll~A low cycle fatigue sllcll~L~; c~LLl~.llely good high cycle fatigue ~Lle~;Lll; high impact ~Lle~Lh; very good bare hot corrosion reci~t~nre; very good bare oxi.1~tinn l~ nre; ~(leq~l~te coatabiliyy; and ~dloqn~te microstructural stability, such as l~ e to the undesirable, brittle phases called topologically close-packed (TCP) phases.
Accordingly, it is an object of the present invention to provide superalloy compositions and single crystal articles made thelcrl~ having a unique blend of desirable properties. It is a further object of the present illvcllLioll to provide superalloys and single crystal articles made ~ercrl~,lll for use in advanced gas turbine engines under high stress, high l~ ,laLulG conditions, such as up to about 2030~F. These and other objects and advantages of the present invention will be a~l~alcllL to those skilled in the art upon lc:fercllce to the following description of the plcr~ ,d embo-1im~nt~.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a chart of hot corrosion test results ~IÇolllled to 117 hours on one embodiment of the alloy of this invention and on two prior art alloys;
FIG. 2 is a chart of hot corrosion test results performed to 144 hours on another embodiment of the alloy of this invention and on a prior art alloy;
FIG. 3 is a graphical culllpaliSon of bare alloy oxidation data from tests performed at 2012~F on two emborlim~ont~ of this invention and on three other alloys;
FIG. 4 is a graphical COlll~aliSOll of bare alloy oxi-l~tinn data from tests pc,lrolllled at 1886~F on two embodiments of this invention and on three other alloys;
FIG. 5 is a graphical c~,.,.p~ Qll of bare alloy corrosion data from tests pelrolllled at 1742~F on t~,-vo embo-1im~ont~ of this invention and on two other alloys; and FIG. 6 is a graphical COIllpdlisOn of bare alloy corrosion data from tests S~gSTlTUTE SHEET

WO 94/0061 1 ~ 3- 3 ~ ~ 7 2 Pcr/US93/062l3 ~clr~.lllled at 1742~F on four embodiments of this invention and on two other alloys.
DESCRIPTIQN QF THE PREFERRED EMBODIMENTS
The nickel-based superalloy of the present invention c~ ,ises the following elem-ont~ in percent by weight:
E2h--nillm about 5.0-7.0 Clno liUlll about 1.8~.0 Cobalt about 1.5-9.0 T~nt~lllm about 7.0-10.0 Tungsten about 3 .5-7.5 ,~hlmimlm about 5.0-7.0 Tit~nillm about 0.1-1 .2 Columbium about 0-0.5 Molybdenum about 0.25-2.0 ~fninm about 0-0.15 Nickel + ~nrid~nt~l balance uliLies This superalloy composition also has a phasial stability llulllber NV3B less than about 2.10. Further, this invention has a critically b~l~nred alloy ~h~ which results in a unique blend of desirable ~ ies. These ~lupelLies include increased creep-rupture .7Llc;ll~,Lh relative to prior art single crystal superalloys, single crystal component castability, cast colllpo~ solutionability, single crystal component r~S~ re to lecly~ lli7~tion, fatigue strength, impact ~7Ll~ Lh, bare hot corrosion l~ e, bare oxicl~tion re~i~t~nre, cclllpoll~llL coatability, and microstructural stability, inrhlrling re to TCP phase formation under high stress, high L~lllpeldture conditions.
Unlike prior nickel-based superalloys known in the art, the superalloys of the present invention have a low ChL~llliulll, low cobalt and high .l.- .-;----- content. The ~ chromium is about 1.8~.0% by weight. Advantageously, the chlullliulll content is from 1.8% to 3.0% by weight. This chlc,llliulll content is signifir~ntly lower than that typically found in prior art single crystal nickel-based superalloys. In the present superalloy, Chlvllliulll provides hot corrosion l~ e, alth~ h it may also assist with the alloy's oxidation capability. T~nt~lllm and .l..~ also assist toward hot corrosion SUÇX ~ SHEET

~ ~$~2 -6- ~

~lu~ y ~tt~inmPnt7 and ~ minllm is present at sllffiripnt levels to provide ~deqll~tr oxi-l~tion reCi~t:~nre~ so that relatively low arl~lition of chrul. iulll is tolerable in this alloy.
Besides lowering the alloy's gamma prime solvus, Chl~llliUlll collLlibul~s to the formation of Cr, Re, W-rich TCP phase and must be b~l~nre~ accordingly in these compositions.
The cobalt content is about 1.5-9.0% by weight. Advantageously, the cobalt content is from 2.0% to 5.0% by weight. This cobalt content is lower than that typically found in prior art single crystal nickel-based superalloys. In the present sllrer~lloy, cobalt assists in providing an a~lu~liàL~ heat tre~tmPnt window since it has the effect of low~li~ the alloy's gamma prime solvus while generally not afr~ , its hlci~iellLmPlting point. Rh~-nillm-co~ g alloys are genPrally desi~nPd with much higher cobalt content than the present invention for the purpose of hllpalLiug increased solid solubility and phasial stability. However, the superalloys of the present invention ...~ .eclr~lly show that much lower cobalt cc llLt;llL~ are possible and desirable toward providing optimized phasial stability, inrllltling control of TCP p ase form~tic)n The rhPninm content is about 5.0-7.0 % by weight and, advantageously, rhPninm ispresent in an amount of from 5.5% to 6.5% by weight. The amount of .1.~;", in the superalloy of the present invention is ~i~";rjr_"lly greater than the .1.~9~,;... content of prior art single crystal nickel-based surçr~lloys. Fu~Lh~,lllore, the sllper~llnys of this invention are generally ~lpsignp~l with an hl~;icased level of lcrlaCLoly element content, e.g., W+Re+Mo+Ta. The tungsten content is about 3.5-7.5 % by weight and, advantageously, the amount of t~lngstPn is from 3.5 % to 6.5 % by weight. T..u~ is added since it is an effective solid solution ~Ll..~ ..., and it collLlibu~es to strengthPning the gamma prime. ~fl-litinn~lly, tungsten is ~rre~;~ive in raising the alloy's incipient melting temperature. The amount of ~ n added to these superalloys is b~l~nrecl with the amount of rh~ninm added since they both co..l . ;h..l~ to the formation of "freckle"
defects during the single crystal invPstmPnt casting process. They also both strongly effect the plupel~i~y for TCP phase formation.
Similar to lllll~.~ilr~ h ~ n.. iS err~;LiVt; in raising the alloy's incipient melting point. However, ~1-PI-;--"~ is a more effective ~L~ r than l..,.~ -, molybdenum and t~nt~lllm in terms of elevated ~ el~lule creep-rupture and, therefore, .1.~,~;.1l.. iS
added a~plu~liaLely. Additionally, .l.~,~i.. has a positive infllnPnre on this alloy's hot corrosion l~ nre. Moreover, lhelliulll partitions primarily to the gamma matrix, and S~BS I I ~ SHEET

WO 94/00611 ~ ~ PCI/US03/06213 it is erre-;Livc in slowing gamma prime particle growth during high LCll~CldLUlC, high stress conditions. Besides reqlliring the balancing of rhtoninm with ~ung~en for castability reasons, W+Re must also be set at a level co~ cllL with minimi7ing TCP phase formation. In general, the TCP phases which occur in such m~trri~l are rich in Cl~ullliulu, L~ , and .l-~.i.--.. content, with .l.~.;.. being present in the ~l~,dLC!i~
pl~olLion. Thus, careful Re/W ratio control is ~-rce~,..y in this alloy to control the Cl~i~y for TCP phase formation.
The molybdenum content is about 0.25-2.0% by weight. Advantageously, molybdenum is present in an amount of from 0.25% to 1.5% by weight. Molybdenum is a good solid solution ~ lgLllCllCl, but it is not as effective as tungsten, .l.. ~.~i.. and t~nt~lllm However, since the alloy's density is always a design con~i-ler~tion, and the molybdenum atom is lighter than the other solid solution strengthPnrrs, the addition of molybdenum is a means of ~ ting control of the overall alloy density in the compositions of this invention.
The t~nt~l-lm content is about 7.0-10.0 % by weight and, advantageously, the t~nt~hlm content is from 8.0% to 10.0% by weight. T~nt~lnm is a ~ignifir~nt contributor to this alloy's ~ ,LIl through means of solid solution ~ i..g and c,~h~r~...rnt of gamma prime particle ~LIell~ Lh (t~nt~lnm also partitions to the gamma prime phase). In this alloy, t~nt~lllm is able to be utilized at relatively high concellL~d~ion since it does not collLlibuLc to TCP phase formation. Additionally, t~nt~hlm is an dLLldC~iVC single crystal alloy additive in tbis composition since it assists in ~lcvell~ g "freckle" defect formation during the single crystal casting process. T~nt~hlm is also beneficial in this colll~!o~i~ion since it tends to raise this alloy's gamma prime solvus, and it is crrc.;Livc toward promoting good alloy oxidation and hot corrosion le~ nre, along with ~lnmini~
coating durability.
The ~ll....i...-... content is about 5.0-7.0 % by weight. Furthermore, the amount of ~ll-.. i... present in this c~ o~i~ion is advantageously from 5.3% to 6.5% by weight.
~hlmimlm and lil;...i-.... are the primary elements comprising the gamma prime phase.
These elements are added in this composition in a proportion and ratio con~i~tent with achieving ~lrqll~tr alloy castability, solution heat treatability, phasial stability and high mrcll~nir~l strength. ~h.. i... is also added to this alloy in plopol~ions sufficient to provide nxi~l~ti~n r~ . .re .

~IBS ~ SHEET

Wo 94/0061 I PCr/US93/06213 2 ~ 7 2 -8-The ~ .. , content is about 0.1-1.2% by weight. Advantageously, lil;.. -i.. is present in this composition in an amount from 0.2% to 0.8% by weight. Titanium is generally beneficial to the alloy's hot corrosion ~ ..re, but it can have a lley,aLivc effect to oxidation r.~ ..re, alloy castability and alloy l~,sl-ollse to solution heat tre~tm~t Accordingly, the lilA.. i.. content must be I'IA;III5';llf~l within the stated range of this Co~ osiLioll~
The colulll~iulll content is about 0-0.5% by weight and, advantageously, the columbium content is from 0 to 0.3% by weight. Columbium is a gamma prime forming element and it is an crrc~;Livc strengthenrr in the nickel-based superalloys of t_is invention. Generally, however, columbium is a deLli.llellL to alloy oxidation and hot corrosion ~lopelLies, so its addition to tbe composition of t_is invention is ...i.-i...;,~ cl Moreover, columbiu,n is added to t_is invention's composition for the purpose ofy,e~Lcl ug carbon, which can be chemi-sorbed into component sllrfAres during non-optimized vacuum solution heat Llg,.l...~ procedures. Any carbon pick-up will tend to form columbium carbide instead of ~ l or t~ntAl~lm carbide, thereby ~lcselvillg the greatest proportion of ~ lll and/or t~nt~ m for gamma prime and/or solid solution strengthening in this alloy.
The h~fninm content is about 0-0.15% by weight and, advantageously, h~fnillm is present in an amount from 0.02 to 0.05% by weight. ~fninm is added in a small proportion to the present composition in order to assist with coating adherence. I:l~fnillm generally partitions to the gamma prime phase.
The balance of this invention's superalloy composition is cc~l,lised of nickel and small amounts of incidental hll~ulilies. Generally, these incidental illl~uliLies are entrained from the in~ tri~l process of production, and they should be kept to the least amount possible in the composition so that they do not affect the advantageous aspects of the superalloy. For example, these inri~l~nt~l hll~uliLies may include up to about 0.04%
by weight m~ng~n~se, up to about 0.05% by weight silicon, up to about 0.01% by weight zirconium, up to about 0.001% by weight sulfur, and up to about 0.10% by weight v~n~rlillm Amounts of these i ll~uliLies which exceed the stated amounts could have an adverse effect upon the resnlting alloy's pr~clLies.
~ r1dition~lly, the superalloy may optionally contain about 0-0.04% by weight carbon, about 0-0.01% by weight boron, about 0-0.01% by weight yttrium, about 0-U l t SREEr WO 94/00611 ~ ~ 3 ~ ~ 7 ~ PCI/US93/06213 g 0.01% by weight cerium and about 0-0.01% by weight l~n~h:lnllm.
Not only does the superalloy of this invention have a composition within the above specified ranges, but it also has a phasial stability number NV3B less than about 2.10.
Advantageously, the phasial stability number NV3B is less than 1.85 and, preferably, the phasial stability number NV3B is less than 1.65. As can be appleciated by those skilled in the art, NV3B is defined by the PWA N-35 method of nickel-based alloy electron vacancy TCP phase control factor calculation. This calculation is as follows:

Conversion for weight percent to atomic percent:

Atomic percent of element i = Pi = u~ X100 ~i ~ui/~i where: Wi = weight percent of element i Ai = atomic weight of element i Calculation for the amount of each element present in the continuous matrix phase:
~lement Atomic amount Rii remaininq Cr Rcr ~ ~ 97Pcr--~ ~ 375PB--1 . 75PC
Ni RNj=PNjlo~s2spB-3(pAl~oo3pcr~pTi-o5pc+o5pvpTapcbpHf) Ti, Al, B, Ri=o C, Ta, Cb, Hf V Rv=0.5Pv W R(u) Pu 0~167PC Pu PMO +PU
MO R(MO)=P(MO)--O ~ 75PB--O ~ 167PC Pl1 P ) 'Note: weight ~e~;e~ ge Re is added to weight percentage W for the calculation above.

- S ~ ~ @ ~ r ~ ,~
t~ J~ t SHEET

~ 2 -lo-EOU~TION 3 Calc~ t;orl of NV3B using atomic factors from Equations 1 and 2 above:
Nji = R~ then N~8 = ~jNi(NV)i where: i = each individual element in turn.

Nli = the atomic factor of each element in matrix.

(NV~i = the electron vacancy No. of each re~pective ~element.
This r~k~ is ~ in detail in a t._cl.ni~l paper entitled ~PHACOMP
Revisited", by H. J. Murphy, C. T. Sims and A. M. Bcltran, published in Volume 1 of T..~ ;onal SY"'1~~~ " on SLLU~;IUIZ11 Stability in Supperalloys (1968). As can be a~,~iaL~d by those skilled in the art, the phasial stability number for the superalloys of this invention is critical and must be less than the stated ..-~x;...l--.. to provide a stable mio,~v~L..l~lur~ and capability for the desired ~u~ Lies under high t~ , high stress conditions. The phasial stability number can be ~let~ormin~oA ~.mriric~lly, once the pr~i*~ n~r skilled in the art is in l,o.~i~e~ion of the present subject matter.

. .
The supeMlloy of this invention can be used to suitably make single crystal articles, such as components for turbine engines. Preferably, this superalloy is utilized to make a single crystal casting to be used under high stress, high temperature conditions characterized by an increased ~ e to creep under such conditions, particularly high temperature conditions up to about 2030"F. Furthermore, it is believed that this invention has an increased resic~nf~e to creep under high stress, high temperature conditions at about 2125~F and above co,.,pa,ed to similar prior art materials, such as the CMSX~
superalloy. While this superalloy can be used for any purpose requiring high strength castings incorporating a single crystal, its particular use is in the casting of single crystal WO94/006~ 7~ PCI/US93/06213 blades and vanes for gas turbine engines. This alloy possesses an unusual rPsi~t~nre to component l~"ly~,l;.lli7~tion during solution heat tre~tmPnt, which is considered an important alloy cnaracteristic that is l-~ces~,..y when producing advanced technology, multi-piece, cast bonded single crystal airfoils. Additionally, t'nis superalloy provides the alloy castability chdld~;L~ .Lics believed n~cec~ to produce conventional-process-cast, moderately-si_ed turbine airfoils with hlL i~;dL~ cooling passages.
While this superalloy's plilllal~ use is in aircraft turbine engines, there are stationary engine applications requiring the speciali_ed high pelrclllldllce characteristics of this alloy. Tnis is particularly the case in turbine engines which require performing characteristics with very restricted cle~ances7 t'nereby materially limiting the amount of pelllli~sible creep. Fngin.os decign~-l to develop nigh ~clrlJllll~ce cnaracteristics are normally operated at higher colu~olltllL lelllpeldLulcs and, Lh~.erole, the problem of creep is increased. Generally, creep in excess of 1% is considered unacceptable in these cases.
The creep characteristics of known state of the art alloys have limited opcldLillg te~ peldLul~s and, thus, m~ximlnn p~lr )....,..-re capability. The superalloy of this invention has an increased resi~t,.nre to creep under high stress, high lelllpeldLul~:
conditions, particularly up to 2030~F.
The single crystal components made from this invention's compositions can be produced by any of the single crystal casting techniques known in the art. For example, single c;ystal directional solillifir~tinn processes can be lltili7P~l7 such as the seed crystal process and the choke process.
The single crystal ç~ting~ made from the superalloy of the present invention are advantageously subjected to a high Itlllp~,la~ul~ aging heat tre~trntont in order to optimi_e the creep-rupture ~l~,p.,.lies of these alloys. This invention's single crystal c~ting~ can ~U~T~TUTE SHET

WO 94/00611 PCr/US93/06213 7 2 _, be aged at a Lclllp~ lulc of from about 1950~F to about 2125~F for about 1 to about 20 hours. Advantageously, this invention's single crystal c~tingc can be aged at a km~ ldLulc of from about 2050~F to about 2125~F for about 1 to about 20 hours.
However, as can be a~ ,ciaLed by those skilled in the art, the o~LiLuulll aging LeLu~cldLulc and time for aging ~epenrl~ on the precise coLu~o~7iLion of the superalloy.
This invention provides sl~p~ lloy compositions having a unique blend of desirable p~upclLies. These ~lu~lLies include: excellent single crystal component castability, particularly for moderately sized blade and vane components; excellent cast CULU~O11C11L solutionability; excellent lcci~ e to single crystal cast coul~oll~.lL
recryst~lli7~ti~ n; ultra-high creep-rupture ~.L ~ Lh to about 2030~F; c~L..,,uely good low cycle fatigue ~.Llcl~Lh; extremely good high cycle fatigue ~.L ~,l-y,Lh; high impact strength;
very good bare hot corrosion l~ e; very good bare nxirl~tion re~ e; ~ qll~t~
Cclll~ullcllL coatability; and microstructural stability, such as re~ e to formation of the undesirable TCP phases. As noted above, this superalloy has a precise composition with only small penni~ihle variations in any one el~o~n~ont if the unique blend of ~lul~clLies is to be m~int~in.otl In order to more clearly illustrate this invention and provide a cOLu~alis.oll with ~rcsenLaLivc superalloys outside the claimed scope of the invention, the examples set forth below are present.-cl The following examples are included as being illustrations of the invention and its relation to other superalloys and articles, and should not be construed as limiting the scope thereof.
EXAMPLES
A large number of superalloy test m~teri~l~ were plc~alcd to investigate the compositional variations and ranges for the superalloys of the present invention. Some of ~S~11311t SWEET

~ 2 ~ 2 the a-lloy compositions tested and reported below fall outside the claimed scope of th present invention, but are included for comparative purposes to assist in the understanding of the invention. Representative alloy aim chemistries of those materials tested are reported in Table 1 below.

See ~Key~ Belou ~ll~v C B Cr Co Ho ~ Cb Ti Al Ta Re Hf ~i ~v3B~ 1 2 3 CMBX-10A - - 3.0 B.5 .70 7.2 .30 .65 6.0 7.6 5.0 .05 BAL Z.08 12.46 6.65 14.55 20.76 -10B - - 2.6 8.2 .70 6.95 .30 .68 6.0 7.9 4.95 .06 BAL 2.02 11.9 6.68 14.88 20.5 -10C - - 2.5 7.7 .70 6.6 .30 .65 5.9 8.2 4.8 .05 BAL 1.90 11.4 6.55 15.05 20.3 -10D - - 4.0 ~.8 .60 6.4 .30 .60 5.7 8.2 4.9 .03 BAL 1.95 11.3 6.30 14.80 20.1 -'OE - - 2.2 7.2 .70 6.3 .25 .72 5.85 8.3 4.8 .042 BA- 1.84 11.1 6.57 15.12 20.1 -'OF .02 .02 2.4 7.6 .65 6.45 .28 .63 5.9 8.5 5.0 .046 BAL 1.89 11.45 6.53 15.31 20.6 -'OG - - 2.4 6.3 .50 6.4 .20 .70 5.8 8.0 5.5 .04 BAL 1.82 11.9 6.5 14.7 20.4 -'OGa - - Z.4 4.0 .50 6.2 .15 .55 5.8 8.3 5.6 .04 BAL 1.72 11.8 6.35 14.8 20.6 10K-'OGb - - 2.3 3.3 .40 5.5 .10 .30 5.7 8.4 6.3 .03 BAL 1.60 11.8 6.0 14.5 20.6 -'OH - - Z.2 5.9 .50 6.4 .15 .80 5.9 8.0 5.5 .04 BAL 1.82 11.9 6.7 14.85 ZO.4 -'01 - - 2.5 4.7 .50 6.4 .15 .70 5.8 7.9 6.0 .04 BAL 1.81 12.4 6.5 14.65 20.9 -'Ola - - 2.5 3.3 .40 6.1 .10 .60 5.8 7.9 6.0 .04 BAL 1.69 12.1 6.4 14.4 20.4 -10J .015 .01 2.65 4.0 .50 6.0 .20 .65 5.8 9.0 5.5 .04 BAL 1.79 11.5 6.45 15.65 21.0 -10L - - 2.0 2.7 .40 5.3 .10 .20 5.65 8.4 6.3 .03 BAL 1.50 11.6 5.85 14.35 20.4 CHSX-1~A - - 3.0 4.5 .35 5.5 - 1.0 5.65 9.0 5.5 .04 BAL 1.84 '1.0 6.65 15.65 20.35 -1-B - - 3.5 3.0 .35 5.0 - .90 5.60 8.8 6.0 .04 BAL 1.80 '1.0 6.5 15.3 20.15 -1'C - - 2.8 3.5 .40 5.3 - .75 5.60 8.8 5.8 .04 BAL 1.70 '1.1 6.35 15.15 20.3 12D-1 1CA - - 2.5 3.2 .45 4.7 - .50 5.60 8.7 6.3 .03 BAL 1.61 ~1.0 6.10 14.8 20.15 -1''E - - 2.0 3.0 .45 4.7 - .40 5.60 8.7 6.3 .03 BAL 1.50 '1.0 6.0 14.7 20.15 CMSX-10Ri - - 2.65 7.0 .60 6.4 .40 .80 5.8 7.5 5.5 .06 BAL 1.91 11.9 6.6 14.5 20.0 CMBX-12Ri - -3.4 8.0 .50 6.0 - 1.0 5.6 7.6 5.3 .06 BAL 1.92 11.3 6.6 14.6 19.4 Kev~ + Re 2 - Al + Ti 3 - Al + Ti + TD + Cb 4 - ~ + Re + Mo + TA
~ Calculated using P~A N-35 Method S~B~llllllt SHET

WO94/00611 ~ &72 Pcr/US93/06213 Third geneldLion single crystal alloy development to investigate the co~ o~ilional variations for the superalloys of the present invention began with the definition and ev~ tinn of a series of experim,ont~l compositions. Increased creep-rupture ~L1G11~I11 was the ~.i..laly objective of the initial development effort, with elt-mPnt~l b~l~nring to provide a combination of useful L~ lF~ - ;llg characteristics following the dcr ,ilion of a base concept for i. c..,dsed ~LIcll~Lll.
The initial m~t~ri~ explored the utility of higher levels of refractory element and gamma prime forming elements than are present in similar prior art cu ,~osi~ions. As shown in Table l, the alloy chromium content was reduced to improve alloy stability.
Cobalt content, initially thought to be required for inc.~ased solid solubility, could be ~i~nifi-~ntly reduced. Refractory elem~ont content (W+Re+Mo+Ta) was varied, while the ~.. i~inn of the ~lilllal~ gamma prime partitioning elPm~nt~ (Al+Ti+Ta+Cb) was also varied. The alloy's Re content was initially explored at col.vs;..~;nn~l levels, but it was found that the Re level had to be increased.
Standard NV3B c~lrnl~tions were pc-ro--lled during the initial alloy design stage to assist respective alloy phasial stability predictions, with that number varying from one alloy composition to another.

S~BSTITUTE SHEET

WO 94/0061 1 2 1 3 ~ ~ 7 2 pCr/US93/06213 Some of the alloys were produced using production-type procedures. These alloys were vacuum in~ r-ion melted in the Cannon-Muskegon Co,l.oldlion V-~furnace, yielding appl-"c;...,lt~ Iy 200-300 Ibs. of bar product per alloy (see Table 2 below~.
Qn~ntitit-s of each c~ pos~Lional iteration, as reported in Table 2, were made into test bars and test blades by ~d~;uu~n i~ llc.~ casting. Solution heat ~ JIOC~lUI-_S
were developed in the labo,al< ly in 3 and 6" ~ m~or tube Ç.. ~.Y 5 Gamma prime aging ~ were also performed in the laboratory.

V-l Vl~ U.OE HEAT ~ K~t';
All~Hent Uo_ C 8 Cr Co ~o U CbTi ~1 Ttc Re Hf ul Hsx-10~Vf 778.001 <.00' 2.9 8.5.7 7.2 _3 .70 6.05 7.6 5.0 .OS B~SE
-108YF 831.OOZ ~.00' 2.6 8.2.7 6.9 .3 .68 6.06 7.9 4.9 .OS BASE
-10RYf 96S.001 <.00' 2.6S 7.0 .66.4 .4 .80 s.n 7.6 S.S .06 8ASE
-10RYf ~66.001 <.00' ''.69 7.0 .66 3 _4 .80 5_66 7.6 5.4 .06 8ASE
-10RYF ~80.001 <.00' 2.66 7.0 .66.3 .4 .79 5.78 7.6 5.4 .06 BASE
-12RYf "63.00' <.00' '.3 8Ø48 6.0 <.OS 1.01 5.69 7.6 5.3 .07 BASE
-12R YF ~64 .00' <.00' ,.4 8.0 .48 6.1 <.OS 1.00 5.60 7.6 5.3 .06 Bl~SE
-12R Yf ~79 .00' <.00' ,.4 ~.. 0 .50 6.1 <.OS l.aO 5.56 7_6 5.3 .06 8ASE
-10G~ YF C83 .00' <.00' 5.4 _.9S .41 6.1 .14 .~;6 5.83 8.4 5.9 .03 B~SE
-12C Yf ~785 .00' <.001 2.7 _ 5 .4S 5.3 <.OS .'5 5.66 8.8 6.0 .OZS BASE
-lOGb(-10K) Yf~794 _00' <.00' 2 2 3.3 .40 5.5 09 . '4 5.74 8.Z 6 4 .02S 8~5E
-12C~(-12D) yfc93 .001 <.001 2.4 3.2 .46 4.8 <.01 .' 0 5.64 8 6 6.4 .025 8ASf * t r a d e--ma rk A

WO 94/0061 1 PCr/US93/06213 All other specimens reported in Table 1 above were produced by blending base alloy bar stock with the virgin elemental additions nPcess~ry to achieve the desired composition. The blending was done during test bar and blade m~nl-f~cture. The base alloy bar stock plus virgin additions were placed into the casting furnace melt crucible, melted and the bath homogenized prior to pouring into an a~ u~liat~ shell mold. It is believed that good correlation beLweell alloy aim chemistry and test bar/blade chemistry was routinely achieved (see Table 3 below).

ALLOY TEST BAR CHEMISTRIES
~ E~ c B CrCo , M~ ~Cb Ti ~I Ta , Re _~~_ Ni Nv3B~
CMSX-'OA - - ~.9 8.5 .68 7.4 .29 .69 ~.0 7.5 5.1 .07 BAL ~.09 -'OB - - ~.7 d.1 .69 6.95 . 9 .6V ~.0 7 ~. 4.8 .06 BAL ''.01 -'OC - '.6'.7 .69 6.4 ..0 .6' ~.7 8.i 4.7 .07 BAL '.86 -'OD - - ~'~ i.0 .62 6.0 .31 .5V i.44 8.' 4.7 .04 BAL '.8, -'OE - - ''.7 '.Z .70 6.4 .-'6 .63 i.89 8 '' 4.8 .05 BAL '.8~
-'0F .014 .OZ7''.~ 7.7 .65 6.4 .Z8 .6; i.96 7,v 5.0 .04 BAL '.8h -~0G - - '''~ 6.5 .53 5.5 .~'0 .68 '.6 8.- 4.6 .05 BAL '.6O
-'OGn - - 2.L 4.0 .41 6.Z .14 .55 5.79 8.3 6.0 .0Z5 BAL '.~' -lOGb~10K)- - Z., 3.5 .4Z 5.9 .10 .43 5.67 8.5 6.0 .OZ4 BAL '.6, -'OH - - 2.3 5.6 .51 6.Z .17 .76 5.58 7.8 5.4 .05 BAL '.69 - 01 - 2.~ 4.8 .52 6.6 .14 .67 5.65 7 4 5.4 .04 BAL '.70 - 0I~ - - .7 .5 .47 5.2 .10 .60 5.80 8.0 5.8 ,0L BAL '.67 - 0J .017 .01''.6L,O .48 6.0 .19 .62 5.74 8.a 5'7 ,OL BAL '.76- 0L - - .9 ~.7 .41 5.4 .10 .22 i.68 8~L 6.2 .0, BAL '.49 -'2A - - 3.0 4.6 .39 5.3 ~.01 .96 ~.61 9.~ 5.0 .0 BAL '.80 -'2B - - ~.5 '.0 .38 5.1 <.01 .84 '.5Z 8.8 6.1 .O'i BAL '.79 -'2C - - '.7 ,.5 .45 5.4 '.01 .75 i.6Z 8 8 6.0 .0~ BAL ' 72 -1ZC~lZD) - -''.5 ,.Z .46 5.0 ~.01 .61 ~.56 8.7 6.0 .0' BAL '.60 -1ZE - - '.0 ,.0 .45 4.7 ~.01 .40 U63 8.7 6.3 .0~ BAL '.51 -10Ri - - '.65 7.0 .60 6.4 .40 .80 '.67 7.6 5.5 .065 BAL '.87 -1ZRi - - ,.4 8.0 .48 6.1 ~.01 .99 '.54 7.6 5.3 .07 BAL '.9Z
P~A ~-35 Method t SHEEl WO 94/00611 ~ ~ ~ 8 6 ~ 2 PClr/US93/06213 For the CMSX-lOD specimen (see Table 1), high quality virgin elemental additions were vacuum melted and the refined material was poured into 2" ~ m~ttor bars.
In turn, a ~lu~llLiLy of the reslllting bar was used to produce single crystal test bar/blade specimens by illVIo~ casting.
It was a~pa,ellL that considerable variation in the hlv~ l casting process iUL~ iLy may have occurred during ~pe~ ~ .,.. r~ .. c since varying levels of test bar freckle formation, secondary dendrite arm spacing and ~lu~elly ~tt~inm-ont were ~ppalc.lL. Derivative alloy response to solution treatment (reported in Table 4 below) varied, and was a function of both alloy coll~o~,iLion and test specimen quality.
Heat Llc~LlllcllL~ developed for the alloy iterations are reported in Table 4 below.
Full gamma prime solutioning was desired for each material, however, this objective was not ullivel.,ally achieved. Primary gamma prime aging was pelrol,lled to effect a more desirable gamma prime particle size and distribution. Secondary gamma prime aging was y-,lrol~lled to effect ~l~ci~ilaLion of col~ ional matrix gamma prime ~l~Ci~iLaleS along with ultra-fine gamma prime ~eci~iL~L~s located within the matrix channels b~Lweell the primary gamma prime particles for these sl.e~;iulells.

I I UIt SHEEI

WO 94/0061 1 PCr/US93/06213 72 -18- ~

Heat Treatnrnt Oetail Allov Peak Solution T~ X ~' Solutioned~ PrimarY ~' Aninn~ S~ b.t ~' Aqin~+
'F C
CMSX-10A2460 13499i'.0-98.0 ~ C~75~F/4 Hrs 1600~FJ20 + 1400~F/24 -lOB 2465 135297.0-98.0 ' C~75~F/4 Hrs 1600~F/ZO + 1400~F/24 ' ~75-F~19.5 Hrs -lOC 2470 135499.0-9,~.5 ~' 00~F/8 Hrs . 1600~F~20 + 1400~F/Z4 ~o7noFr~o Hrs -10D 2450 1343~, ,~.9-100 ' ~~~F/' O Hrs '~00~F~''2 + 1400~F/24 -10E 2465 1352 100 ~ V7~~F~' r; Hrs ' 600-F/ 'O + 1400'F/24~ ~7~i-F/-~ Hrs '~00~F/ 5.5 + 1400~F/23 -lOF 2444 1340 95 197~~F/'~- Hrs '~00~F/'3 + 1400~F/24 -lOG 2475 13579,~.0-9,~.5 197~~F/' ~ Hrs '~00~F/ 4.5 + 1400~ '/17 -101;a2485-90 1363-6599.5-100207~~F/~ Hrs '600~F/-'0 + 1400~F/''3 207';~F/6 Hrs '600~F/' 4 + 1400~F/ O
' 612~F/~8 + 1414~F/''2 -lOGb(10K) Z485 1363 100 '075nF/6 Hrs '600~F/-4 + 1400~F/ O-lOH 2475 135798.5-9,~.0' 975~F/16 Hrs 1600~F/''7.5 + 1400~F/27 ' 975~F/18 Hrs 1600~F/' 01 + 1400~F~46 -101 2475 1357 100 ~075~F/5 Hrs 1600~F/''2 + ~405~F/-4 -lOln 2480 1360 9,~.5-100075~F/5 Hrs 1600~F/ '4 + '400~F/ 4 -lOJ 2480 136098.0-9,~.0'9~~F/15 Hrs '~00~F/'4 + '400~F/_O
''0~;~F/5 Hrs '600~F/ '4 + '400~F/JO
-lOL 2490 1365 100 07';~F/6 Hrs '600-F/''4 + '400~F/,O
-12~ 2475 135798.5-~, ,~.0' ,07 '-F/16.5 Hrs '~00~F/ 4 + ' 400~F/,2~9~r~F/12 Hrs '~00~F/ 4 + '~00~F/27.5 -12B 2480 13609,~.0-9,~.5' 9~-F/13 Hrs ' bOO-F/ 7 + ' ~00~F/39 -12C 2485-90 1363-659,~ 5-100''O~i-F/5 Hrs '600-F/20 + '~00-F/5 07~-F/~ Hrs '~OO-F/24 + ' 400~F/30 -12Cn(12D) 2485 1363 100 2075~F/6 Hrs 1600'F/24 + ' ~00~F/30 -12E 2490 1365 1002075~F/6 Hrs 1600~F/24 + '~00~F/30 -lORi 2460 134998.5-99.82075~F/6 Hrs 1600~F/24 + ' ~.00~F/30 -12Ri 2455 1346 1002075~F/~ Hrs 1600~F/24 + '400~F/30 * Determined by visual estimation + Specimens nir cooled from nll nS~ing trentments Fully heat treated test bars were creep-rupture tested. lhe ~,eci~ ns were m~nhinPd and low-stress ground to ASTM standard proportional specimen dimension. The specimens were creep-rupture tested at various conditions of temperature and stress, according to standard ASTM procedure.
A significant factor of the CMSX-lOA alloy design was the shift to higher Re content. At the same time, W, Cr, Ta and other gamma prime strength~-nt-rs were balanced to provide the desired alloy characteristics and properties. The alloys higher Re level resulted in significantly improved creep-rupture ~ ,Lh throughout the entire test regime, as indicated by the results reported in Table 5 below for the CMSX-lOA
sp~im~ns S~51~ 1~1 t SHEET

WO 94/00611 2 ~ 3 ~ ~ 7 2 PCr/US93/06213 -C~SX- 10A CREEP-RUPTURE
TIHE IR HWRS
RWTURE TI~E X X FIRAL CREEP READIRG TO REACH
TEST CORDITIOR HWRS ~5 RAt. hoursX ~r~on 1.0X 2.0X
1600-F/75.0ksi 534.4 24.2 26.9534.2 22.331 10.9 21.0 328.4 22.027.8328.321.0556.38.7 527.3 21.126.3526.317.55228.472.2 1700~F/50.0ksi 305.0 31.1 34.5304.2 28.614 62.1 108.9 292.4 19.219.9291.819.32471.5123.7 87.6 2.6 5.885.71.47465.9 1800~F/30.0ksi 415.6 16.1 21.4413.8 15.643 182.7 246.1 848.0 37.133.0846.334.326460.4 524.3 1016.233.230.51014.332.984476.8 655.1 1800~F/36.0ksi 586.5 38.1 38.0585.6 33.050 395.0 425.0 572.7 36.935.3570.729.029395.0 422.0 546.5 26.434.2545.725.843373.0 406.0 420.3 22.426.3418.718.105286.7 317.6 426.0 14.817.0425.110.244326.5 353.2 239.8 24.323.8239.723.26494.1123.9 255.7 19.927.4253.618.510115.2 152.7 1900~F/25.0ksi 32.35.511.0 31.02.075 26.7 30.7 129.7 43.238.9128.739.55630.448.1 168.7 34.736.4166.130.81658.278.4 228.1 ' 8.132.3226.416.926146.3 160.6 277.7 ~9.531.1276.427.3239.929.9 423.4 ~9.738.3422.735.121218.4 250.9 383.8 ,5.936.1382.734.861192.9 226.7 373.3 .1.335.7371.626.138211.6 238.0 2000~F/18.0ksi 1,8.0 22.3 .3.0136.3 ' 9.052 33.9 77.0 1.4.9 40.7.6.5134.738.32854.771.9 1-2.9 23.234.9122.0'9.05050.169.4 1' 5.634.2.6.6114.430.86140.856.8 2~.5.235.1.6.2244.3-9.844135.7157.9 2"1.9 36.3~5.4221.8~3.737113.0 140.0 181.2 32.134.2180.1'-9.24953.161.4 2050~F/15.0ksi 126.4 47.9 49.0124.1 30.086 45.8 69.8 150.5 45.547.8148.139.30816.834.5 140.5 30.640.0138.723.59630.676.4 120.8 29.539.7120.029.47916.355.6 79 0 11.714.479.011.64441.754.8 112 2 24.331.3112.121.40155.969.5 2100~F/12.5ksi 94.122.127.594.120.520 42.2 62.6 112.5 39.4:3.1112.'29.'2628.058.8 96 6 25.9,5.995.14. ,425 '.362.5 123 6 43.440.4122.~31.0504~.963.5 50.8 21.7 -9.649.~9.,303 ;.137.6 90.5 41.6 ~3.789.737.4221;.638 5 1800~F/36.0ksi ~ 420.6 23.9 35.1419.9 Z3.196 213.8 286.0 396.1 37.134.0394.731.623239.4 264.9 384.9 31.134.0382.925.554220.5 247.9 As - So l ut i oned Cond i t i on ~e~T~TUTE SHEET

WO 94/0061 1 ~ ~ PCr/US93/06213 ~1 3~672 -20-Microstructural review of the failed rupture specillle.ls of this alloy revealed that TCP phase pl~,ci~iL~Lion occurred during the l.,~eeLivc creep-rupture tests, particularly those at l900oF and above. It became a~a~ L that the NV3B phasial stability number r~lr~ tinn would be an errecLivc tool in preAirting alloy stability and, crre-;Lively, high L~ eldLulc creep strength for the invention.
Wherein the CMSX-lOA ~ecilllcll~s NV3B number was 2.08, CMSX-lOB was r~ n~ to the 2.02 level. This was accomplished by the further reduction of alloy Cr content and similar reduction to Co and W+Re level. W was reduced more than the Re in this specimen since Re is more crrecLive in the solid solution. Additionally, wherein some loss in W contrihlltinn to the gamma prime could be anticipated, it was sufficiently replaced by the modest increase to Ta content in this composition. These rll~nges resulted in the CMSX-lOB alloy specimen exhibiting even more ilu~l-)vcd creep ~Llcll~Lh at 18000F. Table 6 reported below illu~LIaLes that three ~e~;hllems achieved an average life of 961 hours, with 1.0% creep occurring at an average of 724 hours. However, it was observed that TCP phase was present at higher Le l~.aLulc.

S~S ~ l t SHttl WO 94/00611~ 1 3 ~ 6 7 2 PCI/U593/06213 CRSX-10B cREEr , ~ ~ u~-TIR~ IR NOURS
RWTURE TI~E X X FINAL CREEP READING TO REACH
TEST CONOITION HOURS ELONG. RA ~ hours X ~r~. ~ion 1 0X 2.0X
1800~F/36.0 ksi 907.119.234.0 907.0 17.~3' 697.2 752.7 98~.3 18.9 33.598N.17 65' 768.1 817.8 98u.4 35.9 36.198-.331.,13 705.8 767.5 50'.0 4~.1 45.450'.741.-'48317.9 3 2.6 598.1 Lh,9 43.459~.42.,4n 386.5 4'5.2 40.. 3 6-~.652.140'.'' 54.~7v 187.3 2''6.5 26,.3 ,~.7 43.726''.'37.'0'87.6 1'9.2 38-.3 4'~.5 46.238,.'~39.031177.4 2'3.4 41''.8 L3 4 40.5410.638.771189.1 223.4 38~.3 51.5 44.2386.836.920220.5 249.2 45~.5 40.0 46.3458.039.513210.2 291.1 258.0 38.1 40.6257.936.743 32.1 90.2 484.1 27.9 40.0483.426.296288.1 326.7 376.9 16.4 20.4376.816.088 96.0 226.6 481.0 50.5 48.2478.834.557Z64.4 297.5 461.5 35.1 40.6460.130.786181.1 265.3 483.0 47.1 46.8482.143.714286.2 320.7 500.1 33.4 37.0499.730.486 11.9 280.1 1800~F/40 ksi 436.740.244.1 436.2 39.818 294.6 318.9 390.8 50.1 42.8390.341.817250.9 276.2 336.9 52.7 48.1335.246.697226.5 240.9 1900~F/25.0 ksi 237.855.945.7 237.4 53.854 33.0 113.5 295.7 57.4 49.1295.646.592123.7 170.9 2000~F/18.0 ksi 192.731.526.6 191.6 27.n3 56.3 88.6 166.5 41.4 25.3166.534.102 46.2 72.7 ln .3 36.6 27.0171.431.481 24.0 66.1 2050~F/15.0 ksi 219.640.140.4 218.6 37.871 13.2 56.8 122.3 28.2 47.9120.6''6.61437.0 63.7 118.4 33.2 60.0116.9''9.98636.7 56.5 179.7 44.1 48.1179.1~9.188 8.4 75.3 ~4.9 44.2 48.674.634.800 6.8 14.5 168.3 48.6 49.7167.043.171 36.9 77.1 104.8 17.0 27.2102.81.626 66.1 155.9 46.3 49.8155.238.388 64.4 81.9 90.6 15.1 21.487 11.046 75.5 120.5 46.3 55.8118.735.143 10.3 27.7 150.7 39.8 49.7150.133.903 21.4 60.9 149.5 33.2 46.2148.923.166 n .3 88.3 142.9 42.0 47.5142.541.524 54.9 70.5 2050~F~15.0 ksi 163.052.549.2 161.9 46.146 20 5 76.9 1~1.1 66.4 45.6150.759.115 52.7 75.5 1,1.8 57.3 44.4131.548.310 26.3 57.1 *1'6.0 54.4 41.0155.945.502 55.5 78.3 *1,3.7 57.2 56.0132.741.75367.5 80.7 *1,5.1 59.7 52.3134.346.31754.9 71.5 1'l1.1 66.4 45.6150.759.11552.7 75 5 131.8 57.3 44.4131.548.31026.3 57.1 2100~F/15.0 ksi 69.754.2 48 1 69.4 47.674 25.3 36 3 * As-Solutioned Condition S~J~S 111 ll lt SHE~

WO 94/00611 1 . : ~ PCr/US93/06213 Only about 97-98% gamma prime solutioning was achieved in the CMSX-lOA and -lOB materials (see Table 4) which was in~lffirirnt for the purpose of ~ alloy mrrll~nir~l propelLies and microstructural homogeneity. ~ ." of a greater level of gamma prime sollltioning, Lllclc~lc, became an equal priority in tandem with ~ JVillg .licro~Lluctural stability at ~rl~lp~ Il.cs above l900oF.
To conrll , the ~u~e~;Lcd composition of the TCP phase forming in the alloys, SC~nning electron microscope (SEM) wavelength dispel~ive x-ray (WDX) microrllP~ try analyses of CMSX-lOB test bar contained needles was undertaken and c~ al~,d to the alloys gamma and gamma prime compositions. The results, reported in Table 7 below, col~ ll. that the needles were enrirllrcl in Cr, W and Re.

SU~ ll l t SREEr WO 94/00611 ~ 8 ~ 2 PCI/US93/06213 ~ . .

~MSX-10B Micro-Chemistry AnDlYses - Cnst 7est Bar (VF 831) - TI~ Ia~cr~e Section. Bottom Bar Location.
- Solutioned to 2465~F
- Aged 1975~F/19 5 Hrs./AC
1600~F/20 Hrs./AC
1400~F/24 Hrs./AC
GAMMA PHASE GAMMA PRIME PHASE NEEDLE CONSTITUEUT
ELEM K Z A FELEM K Z A F ELEM K Z A F
ALK 0.0101 1.090 0.324 1.000 ALK 0.0145 1.084 0.3Z2 1.000 ALK 0.0116 1.107 0.347 1.000 TIK 0.0069 1.007 0.930 1.051 TIK 0.0084 1.002 0.934 1.052 TIK 0.0077 1.026 0.908 1.039 CRK 0.04Z8 1.008 0.963 1.108 CRK 0.0250 1.002 0.965 1.117 CRK 0.0390 1.028 0.949 1.083 COK 0.0970 O.W4 0.984 1.018 COK 0.0761 0.988 0.987 1.022 COK 0.0755 1.016 0.977 1.025 NIK 0.6891 1.033 0.988 1.010 NIK 0.7270 1.026 0.991 1.005 NIK 0.6143 1.056 0.983 1.024 TAL 0.0485 0.794 1.020 1.000 TAL 0.0697 0.788 1.024 1.000 TAL 0.0389 0.814 1.018 1.000 U L 0.0329 0.788 0.963 1.000 U L 0.0311 0.783 0.962 1.000 U L 0.0682 0.808 0.968 1.000 REL 0.0422 0.785 0.968 1.000 REL 0.0085 0.779 0.968 1.000 REL 0.1083 0.805 0.9n 1.000 UT % UT X UT %
ELEM CPS ELEM ELEM CPSELEMELEM CPS ELEM
AL K12.1800 2.87 AL K 17.94004.19 AL K ll.W00 3.02 Tl K5.5200 0.71 Tl K 6.8400 0.86 Tl K 5.2500 0.79 CR K27.~.400 3.98 CR K 16.45002.31 CR K 21.5800 3.69 CO K40.6800 9.74 CO K 32.54007.64 CO K 27.1700 7.42 Nl K253.1300 66.84 Nl K 272.380071.11 Nl K 193.7500 57.84 TA L6.5667 5.99 TA L 9.6329 8.64 TA L 4.5259 4.70 U L 4.0775 4.33 U L 3.9375 4.13 U L 7.2620 8.71 RE L4.6000 5.56 RE L 0.9500 1.13 RE L 10.1300 13.82 _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ TOTAL 100.00TOTAL 100.00TOTAL 100.00 The calculated NV3B numbers were 1.90 for CMSX-lOC and 1.95 for CMSX-10D. Re was m~in~inPd at around 5% while W was further reduced to improve stability in these specimens. Alloy Ta was increased since it did not participate in TCP formation and the Ta/W ratio was effectively i"lpl~Jved, which assisted with alloy castability.
Chromium was reduced in the -lOC specimens but increased to 4.0% in the -lOD
specimens to provide an opportunity to determine the suitability of the Cr levels from a hot corrosion standpoint. Co was reduced in both materials, significantly in the -lOD

specimen, while Al+Ti level was also reduced to assist in achieving more complete gamma prime solutioning. Creep-rupture results for the two specimens are reported below in Tables 8 and 9, respectively. Even though the -lOD alloy specimens were SUB~ ~ !TilTE SHE~

WO 94/0061 1 ~ PCr/US93/06213 2 ~ 2 -24-observed to exhibit full gamma prime solutioning (as opposed to 99.-99.5% for CMSX-10C) the alloys greater Cr content, which necessitated a lower Al+Ti level, effected lower plu~elLies than attained with CMSX-lOC. However, both materials exhibited improved alloy stability and higher temperature p,~p~lLies. so that attempts to balance the alloys low and high tt:l"pe,~Lure creep response were favorable. .

. TIHE IN HDURS
R W TURE TIHE X X FINAL CREEP READIRG TO RE~CH
TEST CONDIT10~ HoURS~LONG. R~ t. HOURSX DEFORHATION l OX Z~OX
1800~F~36.0 ksi 556.131.4 30.5 555.~ Z6.615316.1 376.3 636.6 43.9 37.5 636.L ,8.460416.6 455.4 609.Z 23.3 34.7 607.b '9.074410.6 ~60.6 635.7 44.9 45.6 635.3 4.991407.3 L43,4 612.8 43.5 38.8 611.~ 41.951409.8 438.7 1850~F/36.0 ksi 252.230.Z 37.8 252.0 22.03361.1 166.3 298.1 41.3 39.0 297.6 37.953170.3 194.8 231.1 33.6 39.5 230.2 29.689127.8 146.0 19ZZnF/Z0.3 ksi 49Z.45Z.5 5Z.4 491.6 48.9ZZ176.5 Z51.7 5Z9.8 38.6 45.5 5Z8.9 33.353Z69.6 306.Z
637.5 48.9 43.3 635.2 45.804189.5 318.3 Z000~F/18.0 ksi Z58.835.0 41.5 Z58.7 3Z.44474.Z 1Z7.5 Z93.1 49.Z 44.1 Z9Z.1 4Z.079145.6 170.9 221.9 43.0 48.5 2Z0.9 33.50755.6 1Z3.3 266.1 35.1 44.0 264.6 33.759113.6 143.6 2050nF/15.0 ksi 196.639.7 40.3 194.1 27.75526.0 134.8 170.4 30.1 46.3 169.Z Z5.62411.1 51.4 193.2 38.1 4Z.9 191.9 3Z.28846.5 76.5 Z47.3 33.1 40.5 246.0 Z6.4941ZZ.0 150.8 ~IIU~E SHET

WO 94/00611 ~ 2 PCr/US93/06213 C~ISX~ ,h._.. JI' I Uh~
TIRE IH HOURS
RWTURE TIRE X XFI~AL CREEP READING TO REACH
TEST COUDITIO~S HOURS ELOUG. RA t. hours X J ro. ~ion l.VX Z.OX
1800~F/36.0 ksi 428.0 26.729.3 426.3 24.166 189.2 248.3 1850~F/36.0 ksi 141.0 23.126.8 140.1 20.660 57.8 79.7 140.7 14.7 26.1140 Z 13 741 56 2 77 6 166.0 17.5 28.9165 0 15 640 76 5 100 1 192Z~F/20.3 ksi 519.9 23.824.9 518.9 22.608 202.0 345.6 667.0 17.6 23.7665 2 16 819 151 8 391 4 680.3 14.9 28.2678 9 14 476 340 2 500 3 2000~F~18.0 ksi 370.3 18.821.3 369.9 15.560 20.9 106.9 401.5 11.1 18.0400 0 8 903 19 8 125 5 366.6 17.5 25.8366 6 8 049 223 9 306 1 2050~F/15.0 ksi 465.3 12.920.5 465.2 12.639 61.0 305.9 338.8 9.8 24.8337.7 9.468 30.8 204.4 The acceptability of the alloys' low Cr content was confirmed through extremely ag~lGssivt: short-term burner rig hot corrosion tests performed at 1650~F, 1% sulfur, 10 ppm sea salt condition. FIGS. 1 and 2 illustrate the results for tests performed to 117 and 144 hours for the CMSX-lOC and CMSX-lOD speciments, .~ e~;Lively. In both cases, the materials performed similar to MAR M 247-type materials, thereby confirming the suitability of the low Cr alloy design concept.
With the above-noted results, another series of alloys, CMSX-lOE, -lOF, -lOG, -10H, 10I, and -12A were designed, produced and evaluated. The alloys explored Re level ranging 4.8-6.3%, 2.2-3.0% Cr level, 4.7-7.6% Co level and the remainder balanced to m~intz~in castability, improve solutionability and improve phasial stability.
The NV3B number ranged between 1.81-1.89.

S7~S~lllJlt SHEEI

WO 94/0061 1 ~ PCr/US93/06213 7 ~ _ One of the series, CMSX-lOF, contained .02% C and .02% B. These additions were observed to improve casting yield and may have assisted in providing more consistent yield and may have assisted in providing more consistent control of single crystal cast article orientation. However, the melting point depl~s~allk., C and B, IG:jtlict~d the specimen's response to solution heat t,c:atl~ent. The CMSX-lOF creep-rupture properties are reported in Table 10 below.

CrSX--lOF ~,h~ JA--TIIIE IU HnURS
RW'TLIRE TIHE X X FIUAL CREEP RE~DIUG TO REACH
TEST COI/DITIOII H~URs ~LONG. Rl~ t hours X ~r~.. R tiorl 1 _OX ~j~
1800~F/36 0 kri 616.0 18.1 2Z.4 615.8 16.898 439.9 477.6 666.6 45.6 48.0 666.4 43.261 464.6 492.3 603.1 25.3 - 24.3 602.5 24.281 398.4 444.0 1850~F/36.0 ksi 243.9 19.6 28.2 243.0 18.045 129.1 160.9 285.9 26.8 32.1 285.5 25.701 187.8 206.0 258.6 19.2 29.1 258.3 18.175 168.3 189.5 1922-F/20.3 ksi 499.5 40.0 41.0 498.5 37.756 208.2 272.6 649.2 55.6 52.9 648.3 51.045 197.6 338.8 361.0 15.8 21.9 357.7 2.599 273.2 335.7 2000~F718.0 ksi 235.4 39.6 51.7 235.4 37.881 100.8 133.2 276.1 43.7 52.8 274.4 36.762 115.1 155.9 290.0 36.7 47.3 289.1 33.304 125.3 162.1 2050~F/15.0 ksi 255.4 28.7 36.6 255.0 27.426 67.4 131.0 255.1 33.4 43.1 254.9 31.378 46.2 102.2 254.5 25.4 33.3 254.4 23.737 50.9 118.7 S~ SHttl WO94/00611 ~ 72 PCI/US93/06213 The CMSX-lOE, G, H and I, plus CMSX-12A creep-rupture specimen results are reported below in Tables 11, 12, 13, 14, and 15, respectively. The results show a general improvement to alloy creep-rupture strength above l900"F while m:~inf~ining extremely good ~Llen~ at lower temperatures.

CRSX-10E ~h~ ~ IU~.

RUPTURE TIRE X X FIHAL CREEP READlbG TO REACH
TEST CO~DITION HOURS ELONG- RA t HOURS X DEFOR~ATION 1 m Z 0X
1800~F/36 0 ksi 664.5 31.4 36.3663.5 30.435 436.5 470.8 604.4 35.1 36.7 603.333.371 253.7 355.9 582.5 41.5 36.1 581.739.792 78.9 329.3 553.5 35.9 37.0 552.533.172 326.4 357.1 1850~F/36.0 ksi 257.9 25 3 32 0257 0 22 n4 149 4 170.3 199 2 18 4 32 1 198.616 261 122 4 139 4 260 5 33 6 33 4 259.731 315 159 9 174 0 1922~F/20 3 ksi810.6 38.6 33.0808.4 33.523 210.2 378.2 800.9 35.3 36.4 799.132.405 339.7 434 2 859 9 39 0 35 4 859.637 036 364 6 465 2 2000~F/18.0 ksi362.8 27.7 29.3362.4 24.887 98.4 177.3 411.2 29 4 27 0 409 926 426 173.6 218.6 369.7 15.3 28 2 368.812.941 170.3 221.9 379.7 26.4 26 1 379.227.656 177.9 206 6 2050~F/1~ 0 ksi 476.9 21.8 23.4476.3 18.233 196.6 255.9 418.4 27 5 24.7 417.525.854 180.0 227.3 397.7 19.0 23.8 396.817.5Z2 112.6 198.2 SUB~ l lt ~Ht~l WO 94/0061 1 . . PCI'/US93/06213 ~3~172 TI~E IN H W RS
RUPTURE TluE X XFINAL CREEP READING TO REACH
TEST OC~iDlTlONH0URS ELONG. RA t,H W RS % DEFOR~ATIOR 1.0% Z 0X
1700-F/55 0 ksi671.8 19.6 28.6 670 5 14.775 447.Z 508.1 693.~ Z6.0 24.2 691.7 Z1.750 441.Z L93 4 7Z4.~ Z3.3 29.7 7Z3.2 19.913 464.8 i20.4 58Z.i 18.6 20.1 581.1 15.200 77.0 _i56.7 681.~ 20.9 24.1 679.Z 19.115 56.4 iil4.8 538.~ 21.6 17.5 538.3 17.857 242.1 308.7 523.0 17.7 21.8 522.4 14.157 235.3 308.0 569.7 17.5 19.8 568.5 15.035 287.0 354.9 1800'F/36.0 ksi775.2 29.6 29.3 7 n .8 28.826 315.0 539.9 719 7 29 5 28.5 717.8 '7.266 3Z1.2 486.4 ~41.6 Z8.0 25.9 740.3 -4.870 ~84.5 464 Z
682.8 45.6 34.7 681.1 ,9.289 409.1 452.4 764.0 23.2 33.7 764.0 '2.884 ~43.6 586.6 790.4 41.4 35.6 789.4 ,8 17Z ill~6 565.3 799.1 27.0 32.3 797.4 -5. n 7 'iZ9.8 579.1 1850'F/36.0 ksi354.4 19.3 30.Z 351.9 16.000 246.7 271.4 344.5 28.5 31.9 344.3 26.174 220.8 241.9 315.4 Z3.7 30.7 315.1 23 571 183.4 205.6 192Z'F/20.3 ksi753.4 31.7 34.8 753.2 27.914 352.3 462.1 728.0 31.5 33.5 727.1 28.362 281.1 422.1 n 1.6 34.3 38.8 n 0.5 30.770 339.3 437.3 1976'F/28.1 ksi95.4 29.3 29.4 94.922.842 41.5 i0.9 95 7 Z6 7 Z7.2 94.7 Z0 130 45.8 i~.7 104.6 30 4 33.2 104.4 27.517 41.8 L 4 100.8 25 6 35 1 98.9 Zl.577 49-Z i~
95.8 25.9 28 9 93.6 19.748 41. i'.4 110 0 Z9 3 30.3 108 0 Z2.669 48.i 60.1 108.2 43.R
104.8 45 2000DF/18.0 ksi464.4 23.1 21.3 463.6 18.190 257.7 293.5 411.9 18 3 Z3 0 410 4 16.347 103.5 227.6 370.9 27.0 38.7 369.8 Z5.3Z6 7.6 47.3 ZOlZ'F/14.5 ksi790.Z 31.2 34.9 788.7 2L.939 299.9 406.0 671.4 23.6 25.7 670.3 13.397 303.3 396.i 512.1 22.6 28 1 510.4 2 094 192.5 277.7 651.7 27 4 39.7 651.3 16.328 315 7 434.7 754.6 29.7 25.4 753.1 24.032 193.8 388.' 908.3 17 7 18.3 758.9 30 8 26.5 758.7 24 090 388.7 438.2 740.0 19.8 20.5 n 9 5 16.96Z 316.5 4Z6 7 671.5 26.4 23.8 669.3 15.578 359.8 412.4 2050'F/15.0 ksi410.8 22.9 27.4 410.0 18.655 226.5 272.2 283.5 18 0 31.2 283.5 15.303 156 4 191.2 320.0 16 8 17.4 318 3 12.979 156.4 191.2 389.7 22.0 22.1 389 7 18.488 29.9 189.1 381.4 Z7.0 Z4.1 381.1 Z4.758 69.5 197.9 2100~F/12.0 ksi254.4 12.7 30 4 252.9 8.984 108.4 185.5 419.8 20.5 Z6.0 419.8 18.917 Z01.1 Z74.3 2100'F/lZ.5 ksi331 4 16 9 Z1 7 331 1 15.069 25.Z 83.Z
367.7 19 Z 23.Z 366.5 17.530 76.2 177 4 387.3 16.8 17.2 386.5 12.742 236.9 282.0 383.1 34.1 32.4 381.6 32.135 10.5 164.3 SUB~ t SHEI

WO 94/00611 ~ ~ ~ 8 ~ 7 ~ PCI~/US93/06213 - C~SX-l OH ~ Jr I U-~-T IW~ lll H~lURS
RuPTv71E TII~E X X FIUAL CREEP RE~DIUG TO RE/~CH
TEST COIIDITIAII H0RS ELaRG. _R~ t. hv~rs X ~rv~ on 1.0X j~
1800-F/36 0 ksi 563 4 23.Z27 Z 563 Z 2Z 669 318 5 366 2 553 1 24 5 Z3 0 55Z 7 Zl 3Z4 373 1 40Z 8 526 9 20 7 27 3 526.4 19.715 358.2 390.7 594.5 35.1 41.4 594.4 32.090 328.8 372.8 - 1850~F/36.0 ksi 242.9 24.3 20.1 242.2 20.686 107.3 155.6 221 9 17 0 21 0 221.0 14.888 115.9 150.4 223 4 21 3 21 0 221.7 19.196 128.4 144.7 1922~F/20.3 ksi 520.6 26.1 29.3 520.4 23.183 Z34.3 319.1 470.4 26.3 21.Z 469.Z 19.333 176.1 253.2 574.7 16.8 Z3 0 573.0 14.411 Z82.1 373.0 Z000~F/18.0 ksi 434.0 Z1.5 18.7 43Z.1 ZO.Z34 103.5 Z33.1 437.3 27.1 33.8 437.3 'Z6.306 18Z.6 Z40.8 430.7 24.6 20.4 430.723.244 68.8 192.1 430.1 Z1.1 19.3 428.919.050 73.7 213.8 2050~F/15.0 ksi 366.1 16.3 12.0 365.5 11.3Z6 239.8 273.3 384.0 17.4 16.0 382.31Z.055 168.Z 242.9 420.2 12.2 13.3 418.610.017 127.3 273.Z

SIJBS I I I ll It SHEr WO 94/0061 1 PCI'/US93/06213 2 ~ 7 2 ~--TI~E 1~ BOURS
RUpTURE TIRE X X FI~AL CREEP RE~DING TO REACH
TEST CONDITION HOURSELoNG. R~ t. hoursX J~r~,. Iion 1.0X 2.0X

1800~F/36.0 k~i 565.135.2 32.0 564.829.774 297.0 368.9 581.9 32.4 29.3 580.228.689371.9 402.5 514.1 24.1 30.2 514.121.207318.3 358.2 1850~36.0 260.525.0 24.8 259.323.255 156.7 175.3 247.5 22.4 29.1 245.717. n 0131.9169.0 246.1 23.7 29.0 246.120.277137.6 156.7 1922/20.3 916.324.9 30.3 914.822.465 472.9 549.3 934.8 32.2 33.0 934.830.165353.7 475.2 863.6 27.8 28 5 862.927.057295.6 442.5 1976/28.1 116.119.5 20.1 116.119.155 57,4 70.1 65.6 22.9 20.6 64.221.368 17.8 26.4 91.6 23.2 25.3 90.415.54437.6 49.7 2000~18.0430.1 22.7 25.7 429.218.44958.9 93.0 483.8 19.8 25.1 483.817.860102.4 245.4 2050/15.0 39'.717.9 ,0.0 397.313.264 239.8 292.9 48'.7 1.4 '9 L87.18.854248.2 318.4 46~.3 8.4 ,5 L67.n15.800194.1 300.1 2100/12.0 50~,3A0.1 '~.9 L98.7 0.615 40'., '6.8 26.3 399.715.429 6.6 25.5 210.6 '1.5 '~.7 210.30.373 ~UBS i i ~ SHEEl WO 94/00611 ~ ~ 3 ~ ~ 7 2 PCI/US93/06213 C~SX - 12A Lh... ~ RE
TIRE 1~ HOURS
RWTURE TIR~ % X FI~AL CREEP READI~G TO RE~CH
TEST COUDITIOU HoUuS ELO~G RA t. hours X deformation 1.0X Z.0%
1800~F/36.0 k~ 4Cl.9 40.Z 41.6 491.8 38.605 254.0 93.7 4~0.4 23.5 31.9 420.319.299 234.9 ''77.
3'~.4 25.3 26.2 382.922.920 198.1 -'44.
4-'6.2 ''4.1 26.1 454.522.58Z 89.9 ''65.'~
4 ~8.0 ,0.7 32.7 457.126.155 253.2 '92.
386.8 ,0.1 30.4 386.327.031 172.7 ~16.
403.7 ,4.5 28.8 402.731.033 140.2 '04.~
398.7 ''1.6 23.5 398.420.277 181.1 ''36.1 1850f36.0 208.5 32.1 40.5 208.3 31.248 100.8 119.6 189.5 21.2 25.2 189.420.461 99.1 116.3 1922/20.3 829.6 46.5 45.3 828.8 44.488 315.8 400.7 797.0 33.5 32.5 796.932.856 315.3 400.5 2000/18.0 500,3 31.7 29.6 499.2 24.922 218.4 268.5 227.6 36.5 41.2 227.126.825 90.6 113.9 430.4 18.5 23.3 430.418.180 181.0 234.1 2050/15.0 424.8 17.0 27.5 423.3 15.832 263.5 301.2 366.1 26.2 42.8 365.520.399 146.6 197.8 400.8 18.2 25.4 400.716.910 184.6 251.3 2100/12.0 255.4 25.8 45.8 253.6 22.920 64.1 125.8 483.9 10.1 19.3 482.7 8.602 378.6 421.9 325.1 7.1 16.6 324.7 4.315 268.8 302.5 Varying the primary gamma prime aging treatment was explored with most of the development activity concentrated on achieving optimized gamma prime size and distribution through longer soak times at 19750F (see Table 4) since higher ~t~ el~ture aging treatments accelerated TCP phase formation during the aging cycle.
Ten to twenty-one hour soak times at 1975~F were successful since they provided average gamma prime particles of about 0.5 um dimension. However, it appeared that shorter primary gamma prime aging time at higher temperature may be more practical, once more stable microstructures were defined.

Microcheînical SEM WDX needle particle analyses was performed on a failed CMS~-lOG creep-rupture specimen. The specimen, tested at 19760F/28.1 ksi condition, exhibited needles in its microstructure. The results of the analysis are reported in Table s~!~sTlTuTE SHET

WO 94/00611 i . PCr/US93/06213 ~ ~S~72 -32-16 below and indicate, again, that the needles formed in this class of material are particularly rich in Re, but are also enrichened with Cr and W.

CMSX--lOG
1976~E/28.1 ksi 104. 6 HRS.
ELEM K Z A E
CRK O. 04261.1050.793 1.049 COK 0. 05841.094o.888 1.086 NIK O.17401.140o . slo1.116 w L o .2107o .941 o .972 1.000 REL 0.47670.9410.979 l.ooo NF.~nLE CHEMISTRY
WT %
ELEM CPS ELEM
CRK 113. 7000 4. 63 COK 112.1100 5.54 NIK 305. I425 15.02 w L 134.8988 23. 03 REL 276.4000 51.76 100. 00 A standardized test for resistance to le.;-y~L~llization was performed on a CMSX-lOG test bar. The test method and the results are reported in Table 17 below. The test results indicate that the CMSX-lOG specimen exhibited similar resistance to cast process/solution treatment/bonding process recrystallization level in comparison to CMSX-4 alloy.

S~STITUTE SHEEl WO 94/00611 2 ~ ~ g ~ 7 2 PCI/US93/06213 -33- ~ :-Method: A controlled level of compressive stress is impDrted on the entire surface of nn ns-cast test bar. The bnr is then ~olution heat treated. Follo~ing solution treatment, the bar is sectioned and the 1 ,sv~.se section is observed metallographically. Depth of recrystalli~tion me~surements nre t~en.
Evaluation Stnndards:
Resist~nce To RX
~nticipated in Blade Alloy Depth of RX Castings CMSX-4 .004" Very Good SX 792 Entire Bar Very Poor CMSX-1OG .004~ Very Good The CMSX-lOGa -lOIa, -12B, -12C, -lOJ, -lORi and -12Ri compositions were defined and evaluated. No creep-rupture properties were generated for the CMSX-lOJ
- s~ecilllen, although test bars were produced and a solution heat treatment developed.
Again, the inclusion of C and B in the -lOJ composition appeared to have positive effect to single crystal test specimen yield. Additionally, the lower leve1s of C and B than evaluated in CMSX-lOF specimen, particularly lower B, made the material more amenable to solution heat treatment. Ninety-eight to ninety-nine percent gamma prime solutioning was achieved, as opposed to the approximate 95% level typical of the CMSX-10F composition.
The CMSX-lOGa and -lOIa alloys were designed with NV3B numbers of about 1.70. These alloy specimens contain about 2.5% Cr, 3.3-4.0% Co, 5.6-6.0% Re, greater Ta/W ratio, reduced Cb, and reduced Al+Ti content. Such reduction to Cb+Al+Ti level improved the solutioning characteristics of the materials (see Table 4), plus assisted achievement of increased alloy stability. Both specimens exhibited nearly full gamma prime solutioning.

SUBSI 1111 lt SHEEr WO 94/0061 1 ~ PCr/US93/06213 2 ~ 7 2 _34 The lowered NV3B number continued to show erre.;Livenes~ in providing better creep-rupture capability at t~ l~c.dLule greater than 1900~F, while m~int~ining t;~ ,.lleiy good creep-~Ll~ Lh at lower le~..pf~ . CMSX-lOGa test results from specimens produced with iLuploved casting process controls ~ibil~d 700 hours or more life with about 475 hours required to creep to 1.0% for 18000F/36.0 ksi condition. For higher k;lllp~,.dLult exposure, the ~le.,iLUCll provided the iLupl~vc:d average life of about 500 hours at 20500F/15.0 ksi conr1iti{)n and average 1.0% creep dt:rlJlLuaLion that occurred at about 250 hours, as in~lir~t~cl by the results reported in Table 18 below.

S~ lt SHEl WO 94/00611 ~ ~ ~ g ~ ~ ~ PCI'/US93/06213 _~ . .

CMSX-10Git CREEP-R W TURE
TI~E IN HoURS
RUPTURE TI~E X X FIN~L CREEP RE4DING TO RE~CH
TEST COhDlTlON HoURS ELONG. U4 t. hours X ~.r~, ~iort 1.0X Z.0X
1800"F/36 0 ksi 500.719.9 25.2 499.7 19.541 31~.5 360.1 584.2 29.1 25.4 583.9 26.395 37O.0 401.8 505.1 22.6 29,8 503.7 18.212 30-,h 347,3 n 0,9 42,0 42,8 n o.7 40.216 47'.0 516.1 ~60.
428.
1850/36.0 '8L,-i 4 ,0 ~3.~i' 183.2 37.154 82,3 94.5 ''~',' 2-,~ ~.~ 290.2 19.323 191.6 207,8 70. ' 33." .; 278.1 29.054 155 3 180,5 , ~3,~t 3~ 322,9 29,218 194 1 217,1 ~ ,,;, ~, ~;t . ~ 3 .3 ,i_, - - _ 1642 ~ 3 300.11 22.8 22,4 - - - -1976/28.1 8~,0 ~ ' ~~ ~'' 3~7 ~8,~t 1 0 , ~ t~ t ~ n~, ~ r ,3,~t o .3 lo~,n ,,, , ,~. 1'1',0 ''3.0 ~ . O".
3,,''. ' .i' .n -. io o.o ,O.n a', ~ , ,, .- a~.. 4 ~.~c3 ~.~ ~.b,L
~, 3L, Ii4............ oJ,L o, - ~ 3n,3 ~ -~ . o.31 ,.ll~,r~L~ .' ~~
1' .3 8,3 ~,i l~O,~~, 'LO'O '; ~D.I' 1 , ,,~ ~,o 1~ -,'84 7~ 0 8 ,, (INTERRUPTED TESTS) 40,2 1=036 39.9 43.4 1,187 42.3 c~jt,3~ O0, ~ ,j ~7,0 L', ~4 127.5 37.493 51 2 62.6 6,i '',~ ~,' 96.5 20.124 45 9 54.4 l 8,n , ,3 7 . 118.0 24.603 49,5 61.3 1 . ~ n -.~ 110,2 21,521 46,4 58,0 nD. 1~ L, ,n _ _ _ _ 1 o, ~ ,8 ~,~ - - _ i.O .~ o,, 1976/18.85 (INTERRUPTED TESTS) ''c'-',', '.o'5 ''~0.3 n~, ,o~7 o~
592,1 25.822,4 "o,-. 2,.'~'6 Il, 305.9 570.7 27.226.9 ; o, 2D, as n, ,3 332.6 535.5 19.323,9 ~, ,'' 1'. '3 0fi.' 344.2 4~1, 0-.6 2050/15.0 '~36.8 ~y~5 ''7~ 535.6 20,662 232.3 321.3 ~'7.o ,,73.~t 496.2 17.600 260.3 317.9 ~ 4,8 3,4~.,4 513.1 12,500 230.4 340.4 4'-4, ,6~,~' 453,7 15.476 263,2 317.1 4 0.3~ _,,7 3c,~
(INTERPJPTED TESTS,) - - - 239.1 - - - 189.6 ~ ~ - 280,3 560,1~ - 22.9 - - - -2012/14,5 536 6~ 7 3 8 1 2100/12,0 354.1 14,836,5 353.8 12.646 91.2 219 1 343.4~ - 27 2 91.4 147.2 491.0~ - 16,7 1700/50,0 + M~chined From sl~tde Specimen S~ t SHET

WO 94/00611 - . PCr/US93/06213 1% creep strength is a significant property. T imi~in~ creep strains to 1.0% and 2.0% is extremely important to gas turbine component design, since a component's usefulness is generally measured by its resistance to creep to an approximate 1-2% level7 not its ultimate rupture ~ Lh. Many prior art alloys may exhibit attractive rupture strength at the > l900oF level. however, they lack the level of useful strength7 i.e.7 creep strength to 2.0%7 that this invention provides in tandem with its far superior strength in test conditions below 1900oF.
The CMSX-lOIa specimens also provided signi~lcantly increased creep strength at the higher temperature extremes7 but it did not appear to develop strength as good as the CMSX-lOGa specimens in lower le~lllpel~ture tests7 as inflic~ d by the results in Table 19 below.

CRSX- 10 5 ~I CREEP RUPTURE
Tl11E 111 HOURS
RWTURE TIRE X X FINAL CREEP READIIIG TO REACH
TEST WIIDITIOR HWRS ~~ R~t, hours X ~f~.. ~.on l.OX Z.0%
1800~F/36.0ksi 532.0 34.8 3Z.7 530.733.000 259.1 312.5 474.6 23.8 29.2473.1 22.886201.0 269.Z
374.3 20.0 21.0372.8 19.238171.1 214.7 1850/36.0 256.0 28.7 28.5 256.027.867 135.4 157.1 Z51.4 34 4 30.3250.7 33.055121.6 144.6 217.8 30.5 2Z.4Z17.Z Z7.00094.Z 117.9 1976/Z8.1 85.7 Z7.5 28.9 83.8Zl .754 36.9 46. Z
81.9 33.6 31.881.0 Z4.3843Z.1 4Z.l 68.9 Z6.1 25.867.6 Z0.960Z3.1 3Z.4 2012/14.5 930.Z 10.0 14.4 9Z8.49.649 104.6 455.7 844.4 17.7 23.284Z.8 16.132339.7 50Z.3 864.Z 15.3 11.986Z.8 14.558179.9 453.4 2050/15.0 510.Z 17.8 19.7 508.415.703 187.Z 312.7 528.6 17.9 24.Z5Z7.0 14.873Z93.7 364.3 438.8 14.3 11.3436.4 13.55656.0 136.9 2100/12.0 616 4 19.0 19.1 616.314.11Z 60.0 42Z.5 467 7 19.1 Z6.1466.0 11.373Z73.6 374.8 S~BSTITUTE SHET

W0 94/00611 ~ 7 ~ PCI/US93/06213 "

Similarly, CMSX-12B, with NV3B at 1.80 level and additional chemistry balance as presented in Table 1, provided attractive creep strength at test condition greater than l900oF, but did not perforrn quite as well as CMSX-lOGa in lower le~ >el~ture tests, as in-lic~t~d by the results reported in Table 20 below.

C~SX-12B L~r r ~u~
T}RE IH HCURS
RUPTURE TIRE x x FIRAL CREEP READIWG TO REACH
TESr COUDITIOHH0URS ELOUG. RAt. hOUrS x JLr~, t;On 1.0X Z OX
1976~F/28.1 kS;91.7 15.3 17.Z 91.214.070 43.9 56.2 72.6 19.4 23.2 72.617.39627.4 3~.8 14.1 5.0 1.3 12.72.300 8.~ 1'.9 98.1 16.9 17.6 96 413.67017.~ 3~.9 108.2 25.2 24.1 108.022.79443.E 58.7 106.9 24.7 24.2 106.321.02446.' 60.1 104.8 24.0 26.8 104.320.09445.a 58.7 104.3 26.8 21.4 103.222.34748.~ 60.8 1800J36.0 515.0 24.7 24.2513.319.468320.1 358.0 536.4 23.2 21.1 530.822.184318.3359.5 3~4.7 ~3.~ ~9.9 302.9~2_582166.0200.8 1850/36.0 262.6 18.4 23.126Z.417.660 12.5 142.2 2012/14.5 1031.3 17.2 18.51029.515.1134Z8.0 703.7 1078.7 15.6 Z0.0 1076.7 15.217 704.2 819.2 839.4 14.9 22.8 839.29.282607.6~77.7 836.9 23.2 21.0 834.818.024591.1658.5 722.0 16.4 21.1 721.915.913170.8~33.6 711.3 14.5 18.8 710.812.490381.9~31.5 711.9 18.3 Z0.0 711.416.201447.730.7 2050/15.0 507.5 10.0 10.1507.29.394 70.4 360.4 434.0 17.5 16.8 434.013.847241.7309.0 2100/12.0 487.5 25.3 20.3486.620.986 18.2 224.7 444.9 7.8 11.0 442.23.884347.3413.6 Alloy composition has the greatest effect on l~ltim~te creep strength. However, some of the variation experienced between alloy derivatives, and particularly for tests exhibiting inconsistent results for a given alloy, can be caused by variation in casting process condition. Casting process thermal gradient variation affects the cast specimen dendrite arm spacing and ~ im~t~ly, its response to solution heat treatment and primary gamma prime aging treatment. It must, therefore, be recognized that much of the creep-S~STITUTE SHEET

WO 94/00611 i - , PCr/US93/06213 ~&~72 ~

rupture results reported herein may have been gc~cldled under non-u~.l;.,.i~.~l con~lition.c and may be capable of i~ lu~Cll~. Illlpluv~,d casting process control may provide casting miclu~Llu~;Lul~s more amenable to solution Lle~ .1 and study to delclluhle the a~>plU~JlidLC plillldl,y gamma prime aging tre~tm~nt to provide the ol,Li uulll garnma prime particle size, which may result in further ",rcl~ ir-~ lupclLy e~hA~rf~.,....l The CMSX-12C colu~o~iLion was ~le~ignPd to provide a c~-1r llAtr-l NV3B number of 1.70. The alloy Cr content was ~leiign~l at 2.8% and Co set at 3.5% aim for this alloy. An attractive Ta/W ratio was m~int~in.o~l while Re content was moderate at 5.8%.
The alloy's Al+Ti content was reduced, in C.~ p~ Oll to the CMSX-12A and CMSX-12B specimens, to provide i u~lo-ved alloy le;,l,ollse to solution procedure.
Similar to the CMSX-lOGa ~ec;---~ , the CMSX-12C ~eci ue~ e~ibiLcd an i u~luvcd balance of creep ~L~cn~,Lh for test condition ranging 1800-21000F, as reported in Table 21 below.

~l~BS~ t SHEET

WO 94/0061 1 ~ ~ ~ 8 ~ ~ 2 PCI'/US93/06213 ~~
.

C~SX~ 1 ZC ~ u2t T I~IE I N HOURS
RUPTURE TI~E X X FIIIAL CREEP READIIIG TO REACH
TEST CO~DITIONHOURS ELouG- RA t. hoursX J.rc,.. n tia~ 1.0X 2.0X
1800~F/36.0 ksi 465.2 31.8 21.0 464.5 30.543173.0 262.4 518.0 26.1 31.Z 517.9 24.947 288.1334.3 480.9 28.3 33.6 480.0 27.715 239.7297.5 713.3 30.0 28.0 713.2 28.899 455.0503.7 1850/36.0'3'.' Z8.Z Z6.8 Z37.7 Z7.054 114.4145.3 .' 2Z.9 27.3 ZZ0.7 22.491 111.3135.Z
.'. 23.3 Z4.7 Z31.0 ZZ.614 1Z1.0144.7 38,0 Z6.Z Z7.0 337.5 Z3.Z56 Z16.0Z36.3 "~o, ~. + 33.3 33.5 1976/28.173.' Z0.8 Z9.1 7Z.Z 17.768 Z9.3 38.9 '~. Z8.1 31.8 77.4 Z1.533 31.4 41.4 ~3.8 21.6 26.5 82.3 17.860 34.2 43.8 ~~,n 31.Z Z9.8 67.5 Z4.177 25.5 34.6 1' ~.nl ~~.~ 30.8 ~6. 32.8 68. 29.3 1'8. 26.0 28.0 116.Z Z3.8ZZ 49.3 6Z.0 ~ ~ 29.0 ~INTERRUPTED TESTS) - - 29.4 _ 32.9 1976/18.85 ksi n .4 '' ..0 ~ _ ~NTERRUPTED TESTS) - - ~ D ~. _ 411 ., 2012/14.51001.8 23.6 20.01000.7 23.348 249.654Z.8 865.5 Z0.7 26.1 864.8 18.807 418.2569.3 61.9 267.1 Z050/15.0509.4 13.7 ZZ.3 508.0 1Z.860 1 ~.1315~1 546.4 15.6 23.6 546.4 14.044 3 _.0404.0 1~0 8 2~0.
1~0.~
Z100/12.0404.3 11.Z Z1.6 404.3 8.438 290.1326.4 3Z1.7 9.5 15.0 3Z0.4 7.671 156.6Z54.1 545.1 8.Z ZZ.1 54Z.Z 5.351 236.0452.9 457.4 8.6 23.4 455.8 6.61Z 309.3380.9 Z100~F/1Z.0 371.4l 14.Z 17.1 1750~F/50.0 446.9~ 16.8 Z0.4 - - - -1976~F/18.85 476.6+ 19.Z 27.1 459.9l 30.6 30.Z
1976~F/Z8.1 ksi1Z0.51 Z4.1 22.9 99.6~ 25.8 Z9.4 Z050~F/15.0 ksi 469.8 - 30.8 485.4 - ZZ.7 2012~F/14.5 ksi 6_8.
5 ' .
2~ .
3~~ 7 Sl~ SHEE~

WO 94/00611 PCr/US93/06213 With improved casting process controls, this specimen has shown the following 1.0% longih--lin~l creep strengths, as reported in Table 22 below.

Test Condition Time to 1.0X Strain Hrs 1800~F/36.0 ksi 455 2100~F/12.0 ksi 309.3 Both alloys provide similarly greater rupture ~ n~Lh than CMSX-4 alloy at condition to 19760F. Respective improvements to metal telllpel~tule capability are reported below in Table 23.

Approx. Strength A '~. .'. _ Teml~ert~ture Relative to CMSX-4 1800~F 40~F
1850~F 45~F
1976~F 43~F
Brsed on 1.0X creep strength, the respective approximnte ~d~ s~s ~re:
1800~F i46~F
1850~F ~60~F
1976~F ~55~F

Note that the comparison is not density corrected.

S!~BS~llllt SHEFI

Wo 94/00611 ~ ~ ~ g ~ 7 2 Pcr/US93/06213 ~ 1 - ~ , , For test Lt;~ dLule above 19760F, the test results inAir~tt: that the CMSX-lOGa and CMSX-12C specimens provided slightly lower ~Lle~Lll than CMSX-4 alloy. The reduction in ~Ll~n~Lll advantage for these alloys is believed to be the result of TCP phase formation. To address this issue, the alloys CMSX-lOGb, CMSX-lOL, CMSX-12Ca, and CMSX-12E, are ~lesi~nf~-d with NV3B llulllbel as low as 1.50 (see Table 1) to provide greater phasial stability, and effect much i~ luvt;d high temperature creep-strength while m~i.,li1;..;..g most of the creep advantage demol~LldLtd for the 1800-19760F test regime.
The CMSX-lORi and CMSX-12Ri compositions were Ae~i~n~cl at the 1.91 and 1.92 NV3B levels, l~ e~;Liv~ly. These ~e.;i.llells were subjected to the most extensive testing of plo~lLies. They were A-oci nPcl with 2.65% and 3.4% respective Cr levels, with other features remzlining similar to the arure--~ ned alloy design considerations.
The properties gellt;ldL~d for these two materials co--li---- the overall invention design concept with the other m~teri~l iterations able to provide similar physical ~lu~c:lLies and relatively better blends of mechS~ni~ lopelLies.
The CMSX-lORi and CMSX-12Ri specimens' lc~e~;Liv~ creep-rupture capabilities are reported below in Tables 24 and 25.

S~ T~TUTE SHEr W O 94/00611 PC~r/US93/06213 ~3~72 -42-CRSX-10~Ri~ CREEP-RUPTURE

RUPTURE TI~E X X FIRAL CREEP READI~G TO RE~CH
TEsT OONDITION HoURs ELONG. RA t. hours X ~r~. Jtion 1.0X Z.0X
1675nF/75.0 ksi 227.3 21.2 33.8 225.4 14.359 52.8 131.5 231.6 19.3 31.0 231.316.671 51.0 125.1 223.4 17.0 22.3 223.315.360 68.5 126.6 1750/50.0425.9 18.3 33.7 425.616.047 303.4 334.7 428.0 18.4 29.7 427.316.229 309.2 343.0 460.8 17.1 25.7 459.015.308 314.7 360.3 1800/36.0698.5 39.9 34.3 696.836.980 492.8 521.5 676.3 28.3 33.3 674.527.221 479.0 513.8 692.9 38.5 31.3 692.236.494 469.3 504.9 1850/36.0291.2 34.1 33.1 291.131.774 194.1 210.4 260.0 29.3 32.1 Z58.8Z5.3Z1 170.Z 186.4 272.3 34.5 31.8 271.130.940 169.3 187.1 1850/27.56614.0 52.0 42.0 613.550.482 365.8 415.5 576.3 49.7 39.0 575.949.183 345.1 368.2 481.1 40.4 35.4 480.738.294 309.3 335.4 1976/28.176.2 Z3.5 31.7 75.922.130 38.6 46.7 80.5 19.0 26.3 79.814.665 44.3 51.3 99.7 26.2 28.1 98.923.480 40.4 54.0 41.4 (INTERRUPTED TESTS) 37-0 40.5 1976/18.85 265.6 29.535.7 264.7 29.010 158.7 184.8 278.8 51.4 38.8 278.1 46.0Z6 8Z.0 155.0 139,7 UPTED TESTS) 1Z8.8 100.1 2012/14.5 490.8 40.233.5 490.5 37.678 286.5 335.3 447.0 37.0 41.5 445.0 3Z.814 Z91.4 319.9 - - 113.5 (INTERRUPTED TESTS) - - Z05~7 ~ 202.z 2050/15.0 251.9 33.635.9 250.0 25.559 100.0 149.5 318.9 27.1 30.0 318.2 23.149 177.5 221.2 - - 181.0 - 95.5 INTERRUPTED TESTS) - 34 5 2100/12.0 400.3 17 9 27.2 400.117.877 10Z.8 225.0 362 1 15 3 ZZ.9 361.814.986 1Z5.7 217.2 389 5 19.9 24.0 388.219.510 41.1 180.7 ~U~STITUTE SHEET

WO 94/00611 2 ~ 7 ~ PCI/US93/06213 ~ SX--lZ~Ri) Ch~ J. lUhC
TIRE IN NUUQS
PUPTUQE TlRi X X FI~AL CREEP UEADIUG TO REACH
TEST COUDITIONHOURS~Q~~ ~A t. hours X ~r~-~tion l OX 2.0X
1675'F/75.0 ksi 209.8 22.3 23.1 209.3 19.958 2.6 46.3 191.4 14.3 17.4 189.7 12.483 1.6 42.5 189.6 22.0 22.8 188.3 19.080 1.5 Z2.3 1.'50/50.0 448.1 26.7 26.6 447.9 26.054 302.3 335.5 403.1 19.0 26.9 401.9 18.566 210.0 290.2 435.0 19.4 26.9 434.4 18.503 89.1 284.1 1800/36.0 604.5 34.7 29.9 604.3 34.170 349.4 407.1 583.6 37.0 32.0 581.3 30.443 391.3 420.6 627.0 25.3 29.7 627.0 24.417 412.4 455.8 1850/36.0 302.9 33.1 31.3 301.7 29.034 198.9 215.1 314.4 32.0 27.1 312.7 27.479 201.4 220.2 1976/Z8.1 90.0 19.7 29.2 88.5 16.6Z7 33.9 48.8 91.5 30.3 31.9 90.6 29.001 3'.3 47.9 68.6 35.3 32.2 68.4 28.869 4' 37 27.6 (INTERRUPTED TESTS) 4 .4 3~.7 2012/14.5 324.1 31.4 30.8 323.9 24.403 160.1 207.7 481.4 30.9 31.9 481.1 29.581 129.9 299.6 551.7 29.9 31.1 549.2 25.622 304.4 375.5 256.1 (INTERRUPTED TESTS) 182.8 101.5 2050/15.0 243.4 36.1 35.0 243.3 20.614 143.1 174.2 2100/12.0 374.8 12.1 20.3 374.7 11.743 166.6 280.4 463.6 15.4 25.9 463.3 13.594 245.7 363.3 488.0 20.3 25.9 487.1 19.550 25.7 118.9 The method and results of W and Re microstructural segregation investigation undertaken on fully solutioned and partially solutioned CMSX-12Ri test specimens are reported in Table 26 below. The investigation indicated that it is desirable to minimi7e the amount of microstructure-contained residual eutectic and that for fully solutioned specimensT the solution treatments developed for the invention are successful in minimi7.ing elemental segregation, which is important in ~tt~ining optimized mechanical properties and microstructural stability.

S~IBS 1~ S~EEr -WO 94/00611 PCr/US93/06213 ~ 38~2 ~

Alloy: OMSX-12 Ri Test Specimen: 3/8" Diameter sOlid Bar Specimen Condltion: Fully Solutioned Solutioned ~ith 2.0% Residual Eutectic AnDlyses Method: Microprobe Analyses + Random array of 350 points across a section at right ~ngles .
to the gro~th direction I Seven line scans, 51~ apart, 50 point analyses per line The standard deviation of the U and Re measurements are the measure of homogeneity Results:
ÇMSX-12 Ri Standard Deviations U Re Fully Solutioned 0.27 0.50 2% Residual Eutectic 0.36 0.90 Comsarison Typical ~MsX-4 0.57 0.60 Table 27 below reports results of burner rig hot corrosion test undertaken with tlle CMSX-12Ri ~ech~,ell. The measurements were taken at the bar location which experienced the maximum attack, i.e., 16520F location, with the results showing the DS
MAR M 002 alloy experienced approximately 20X more metal loss than the CMSX-12Ri specimen. Visual observation showed a similar result for the CMSX-lORi alloy. Both CMSX-lORi alloy and CMSX-12Ri alloy showed similar reSict:lnre to attack as CMSX-4 alloy based on visual specimen review at 60, 90 and 120 hours.

~E~ t~ S~Ei WO 94/00611 PCI/US93~062I3 TABLI~ 27 HOT CORROSIO~
METHOD
Surner Rig 1742'F (550-C) 2 pp~ rJlt, ~trndbrd fuel H ~ ~ t~ken et point of msximum ~tt~c~
uhich u~s et 1652'F <900'C~
H ~ reported uere t~ken nt the ~verrge ~inimum di-~eter of useful mctel RESULTS
90 Hour Tert Post Test ffetsl Loss ~lloy ~niti~l DjA. Useful D;a. Per Side DS H~r H 002 6.88 mm 5.14 ~m .87~m ~_034") CHSX-12RI 6.86 ~m 6.78 mm .04 wm <.0016") Table 20 below reports the results of cyclic oxidation tests underta1cen at 2012~F
witn -~h I ~as vel~lt~ The CMSX-~Ri ~ as simi!ar!y; ~ial Ult to oxidation attack at 20120F. Ilo~ e., it was not as good as CMSX 1 at a~o~il"~l~,ly 18860F ~A~)O~UI~.

~;,,...~ ~

. ~

W o 94/00611 PC~r/US93/06213 t;~ 2 ~

CYclic Oxidation Test 15 Minute Cycles to 2012~F (1100~C), Cooled To Ambient Bet~een Cycles Mach 1 Gas Velocity 89 Hours Tot~l ~ith 77 Hours at 2012~F

CMSX-lZ Ri RESULT: at 1100~C Approx. 0.1 mm loss per side for every 300 cycles Approx. 0.1 mm loss per side for every 380 cyctes nt 1030nC CMSX-1Z Ri Approx. .105 mm loss per side nfter 355 cycles Approx. .03 mm loss per side sfter 355 cycles CMSX-12Ri elevated temperature tensile data is reported in Table 29 below, while the results of impact tests are reported in Table 30 below. The CMSX-12Ri elevated temperature impact strength minimum is similar to CMSX-4 and its maximum occurring at 17420F, is better.

~j ' ~t ~~ 4~ t~ tA $~

S~ t SHt~l WO 94/00611 2~ 1 3 8 ~ 7 2 PCI~/US93/06213 ~ .
~7 -TENSILE DATA
CMSX-12 Ri Alloy Test Temp LAUE 0.1% Yld 0.2X Yld UTS Elong RA
'F ksi ksi ksi % %
1382 2.3~ 150.0 160.8 188.7 13 14 1382 Z.3~ 153.6 165.1 190.0 13 15 1562 6.2~ 136.5 130.8 15Z.3 27 24 1562 6.2~ 135.0 128.9 160.1 Z5 23 1742 5.6~ 92.7 89.2125.3 24 30 1742 5.6~ 99.9 106.2 129.2 24 32 1922 3.8~ 69.5 74.3104.1 19 36 1922 3.8~ 72.4 77.6106.0 19 36 IMPACT DATA
CMSX-12 Ri 0.35 Inch Diameter Ploin Cylindrical Specimens Test Temperature, ~F

CMSX-12 Ri (1 only) 26 J 20 J60 J 32 J
CMSX-4 (Ave. of 4) 26 J21 J 42 J45 J

Further Impoct Property Comparison CMSX-2 -- Min. Impact Strength 16.5 Joules . SRR 99 -- Min. Impact Strength 20 Joules TE SHEEr WO 94/00611 PCr/US93/06213 7 2 ~
~8-The results of CMSX-12Ri low cycle fatigue tests undertaken at 13820F and 17420F test conditions, with R = 0, are reported in Table 31 below. The data indicates that CMSX-12Ri performance is similar to CMSX-4 at 13820F condition, while the alloy exhibits approximately 2.5 times the typical CMSX-4 life at 17420F condition.

LOU CYCLE FATIGUE

CMSX-12 Ri Alloy R = 0 (zero to maximum stressing) 138Z~F (750~C) 1742~F (950~F) PEAK STRESS PEAK STRESS
ksi (MPn) Cyclesksi (HPa~ Cycles 142 (980) oo86 110 (760) 4427 130 (900) 11950 99 (o80) 15510 125 (860) 20810 87 (~00) 37430 119 t820) ~100000 75 (520) 92580 R~, rO.. ~.e is similar to CMSX-4 ~t 1382~F (750'C) Compnred to CMsX-4, nt 1742~F (950~C) and in the 20000 cycle region, CMSX-12Ri exhibits 2.5 times life or 15X on stren9th.

Notched low cycle fatigue test results show the CMSX-12Ri is 2-1/2 times better than CMSX-4 out to about 30000 cycles, while at 50000 cycles and above, the alloy performance is similar to CMSX-4. The results of these tests performed at 13820F, Kt = 2.0 and R=0 test condition, are reported in Table 32 below.

S~TIT~TE SHEET

, W0 94/00611 ~ ~ 3 8 ~ 7 2 PCI~/US93/06213 ~
-49- . .

UOTCHED LOU CYCLE FATIGUE
CMSX-12Ri Alloy .

138Z-F (750nC) Kt = 2.0 R ~ O

PEAK STRESS CYCLES
ksi (MPn~

113.13 (780~ 4879 107.33 (740) 9784 95.7Z (660) 28470 84.12 (580) 49810 81.22 (560) 78.3Z (540) ~ 115 000 75.42 (520) ~ 115 000 Results are 2-1~2 times better thDn CMSX-4 out to ~bout 30000 cycles.
Results are similar to CHSX-4 nt 50000 cycles nnd above.

High cycle fatigue test results for the CMSX-lORi alloy are reported in Table 33be10w. For 17420F, 100 Hz, R = 0 test condition, the alloy exhibited about 2-1/2 times the typical CMSX-4 lives.

S~g~TUTE SHEET

-WO 94/0061 1 PCr/US93/06213 3 ~

HIGH CYCLE FATIGUE
CMSX-10Ri Alloy 1742~F (950~C), 100 Hz., R = 0 PEAK STRESS CYCLES
ksi (MPa) ~Nf) 81.22 (560) 15.2 x 106 92.8Z (640) 3.59 x 106 104.43 (720) 0.6 x 106 * Lives are 2-1~2 times better than CMsx-4 The CMSX-lORi and CMSX-12Ri test data in~lie~tec that adequate hot corrosion and oxidation resistance can be achieved with extremely low alloy ~;hlu~ lll content.
Additionally, extremely good thermo-mechanical fatigue tensile and impact strengths are apparent with the superalloys of this invention.
The results of alloy specimen density measu~ llt~ are reported in Table 34 below.

S~TIT~JT!~ SHET

WO 94/00611 2 ~ 3 g 6 7 2 PCr/US93/06213 -SINGLE CRYSTAL ALLOY DENSITY DATA

DENSIT
~I-~Y l bs/ i n CMSX-lOA .324 CMSX-10B .324 CMSX-lOC ,, 5 CMSX-lOD ~3 5 CMSX-1OE ~ 5 CMSX-10F ,3 3 CMSX-10G .3~2 CMSX-10Ga .3 2 CMSX-1OH .324 CMSX-101 .322 CMSX-101a .322 CMSX-10J .327 CMSX-1OGb~1OK) .329 CMSX-12A .323 CMSX-12B .325 CMSX-12C .326 -CMSX-12Ca~12D) .326 CMSX-lORi .326 CMSX-10 Ri .323 The alloys of this invention are amenable to HIP processing. Specimens HIP
treated as reported in Table 35 below, showed nearly complete pore closure and absence from incipient melting.

U~E SHEET

W O 94/00611 PC~r/US93/06213 ~ 2 -52-T~BLE 35 HIP condition 1. Heat Specimens in the HIP vessel to 2455~F at ..,i..i.,~l" Argon pl~ iUl~
(approximately 1500 psi) and hold for 4 hours while m~int~ining 2455~Ftl500 psi condition.
2. While m~int~ining the 2455~F ~J.,~dlill~ lelll~)cldlul~7 increase the Argon ~l.,S~UlC~ over 1 hour to 20 ksi. Soak ~e~; ells at 2455~F/20 ksi condition for 4 hours.

5~ UIE SNEE~

WO 94/00611 2 ~ 3 ~ ~ ~ 2 Pcr/Us93/06213 .

--5 3 - -~

Further evaluation of the CMSX-lORi and CMSX-12Ri alloys was undertaken. The data reported below further shows the unique capabilities ~x~hibiL~d by the alloys of this invention. More specifically, very attractive hot corrosion and dynamic oxidation lcx;~ re are exhibited by these alloys in tandem with exceptionally high creep-rupture, thermo-mrrh~nir~l fatigue, tensile and impact ~ u~ s, despite the extremely low level of Chlvllliulll content employed, thereby providing a unique blend of desirable ~lupellies.
Additional tensile data is reported in Table 36 below for the CMSX-lORi and CMSX-12Ri alloys. These alloys were evaluated at Ir...pv.,.l...c,s ranging from Room Temperature (RT) to about 2100~F. This data complements the data reported in Table 29 above.

Tensile Data CMSX-10Ri ALloy TEST TEMP 0.1X PS0.2% PS TS ELONG RA
~F ksi ksi ksi % X
68123.3 123.9124.0 13 18 1202146.Z 147.2173.2 7 2 1202145.8 146.5171.6 9 13 1382144.6 147.8174.8 6 7 1382141.3 144.2172.6 6 5 1562134.7 132.3158.1 27 32 1562135.8 132.0163.0 27 28 174295.6 90.5136.223 27 174293.5 90.1134.223 43 192271.8 76.0115.422 34 192272.4 73.2114.620 26 S~F~S~ E SHEE~

WO 94/0061 1 ' . ~ ' PCI /US93/06213 7 ~ -~4-TA~3LE 3 6, CONTINUED
CMSX-1ZFi Alloy TEST TEMP0.1% Ps0.2% PS UTS ELONG RA
~F ksi ksi ksi X %
lZOZ 132.4 13Z.4 154.6 lZ ZO
lZ02 133.6 133.7 157.7 13 Z3 1382 150.0 160.8 188.7 13 14 1382 153.6 165.1 190.0 13 15 1562 136.5 130.8 152 3 Z7 24 156Z 135.0 128.9 160.1 25 23 1742 93.1 89.3 125.3 24 30 1742 99.9 106.2 129.2 24 32 192Z 73.5 76.6 104.1 19 36 1922 72.4 77.6 106.0 19 36 2102 37.7 41.5 6Z.9 31 52 2102 36.5 40.6 62.4 28 47 Further results of impact tests, in addition to the results reported in Table 30 above, are reported in Table 37 below. Both the CMSX-lORi and CMSX-12Ri compositions were evaluated at temperatures ranging from 1382-1922~F.

Impact Data ALLOYTEST TEMP ~F IMPACT ENERGY, JOULES
CMSX-lORi 1382 31 CMsX-1ZRi 1382 Z6 S-~BSTIT~TE SHEET
-WO 94/00611 ~ ~ 3 ~ ~ 7 2 Pcr/US93,062l3 Plain low cycle fatigue data for the CMSX-lORi and CMSX-12Ri specimens is reported in Table 38 below. This data complements the data reported in Table 31 above.
The tests were ~elÇc,lllled at 1382~F and 1742~F, with R=O and 0.25 Hz test conditions.
TAsLE 3 8 Plain Low Cvcle Fatique Data CMSX-1 'Ri Alloy; 1742~F, R=0, 0.25 Hz PEAK STRESS, ksi LIFE, CYCLES BROKEN?
98.6 5,403 Y
92.8 21,123 Y
87.0 39,811 Y
81.2 47,942 Y
75.4 63 454 Y
72.5 67 009 Y
69.6 101,019 N

CMsX-12Ri Alloy; 1382~F, R=0, 0.25 Hz PEAK STRESS, ksi LIFE, CYCLES BROKEN?
150.8 6,940 Y
147.9 5 284 Y
142.1 8 686 Y
'30.5 '1,950 Y
' 4.7 -'0,810 Y
' '.8 ~ 2,950 Y
'' '.9 106,600 N

CMSX-1 Ri Alloy- 1742~F, R=0 0 25 Hz PEAK STRESS, ksi LIFE, CYCLES BROKEN?
116.0 1,2 '0 Y
110.2 4,4 7 Y
98.6 15,5' 0 Y
87.0 37,4,0 Y
75.4 92,5~0 Y
72.5 123,100 Y
69.6 130,070 N

The results of notched low cycle fatigue tests (K, = 2.2) undertaken with CMSX-lORi and CMSX-12Ri specimens is reported in Table 39 below. The tests were performed at 1382~F and 1742~F, with R=O and 0.25 Hz test conditions.

SU~ U~~ SHEE~

WO 94/00611 ' PCr/US93/06213 2 ~ 7 2 KT = 2.2 NOTCHED LOW CYCLE FATIG~TE DATA
CMSX-10Ri AlLoy; 174Z~F, R=0, 0.25 Hz PEAK NOMINAL STRESS LIFE, CYCLES BROKEN?
KSI
87.0 5,103 Y
75.4 28,34Z Y
69.n 83,687 Y
63., 66,054 Y
60.~ 41,720 Y
58.' 101,Z63 N

CMSX-1 Ri AlLoy; 1382~F, R=0, 0.25 Hz PEAK NOMINAL STRESSLIFE, CYCLES BROKEN?
ksi 113.1 4,879 Y
107.3 9,784 y 95.7 28,470 y 84.1 49,810 Y
81.2 125,900 N
78.3 115,200 N
75.4 118,200 N

CMSX-1''Ri AlLoy; 1742~F, R=O, 0 Z5 Hz PEAK NOMINAL STRESSLIFE, CYCLES SROKEN?
ksj 116.0 1,220 Y
110.2 4,427 Y
98.6 '5,510 Y
87.0 37,430 Y
75.4 ~2,580 Y
72.5 1'-3,100 Y
69.6 1 0,070 N

High cycle fatigue data, which complements the data reported in Table 33 above, is reported in Table 40 below. The data is reported for tests undertaken with CMSX-lORi and CMSX-12Ri specim~ns at the respective test conditions of: a)1742~F, R=O, 100 Hz;
and b) 1022~F, R=-1, 100Hz.

S~ lJ l t SHEET

WO 94~00611 2 ~ ~ ~ & 7 2 PCI'/US93/06213 -57- :.

HIGH CYCLE FATIGUE DATA
CMSX-10Ri ALloy; 174Z~F, R=0, 100 Hz PEAK STRESS, ksi CYCLES X 106BROKEN?
121.8 0.063 r 116.0 0.364 Y
113.1 0.117 Y
104.4 0.600 Y
9Z.8 3.590 Y
81.2 15.194 Y
72 5 53.485 Y

CMSX-12Ri Alloy; TESTED AT 1022~F, R=-1, 100 H~
PEA~ STRESS, ksi CYCLES X 106BROKEN?
+- 63.8 0.260 Y
+- 58 0 0.216 Y
+- 52 2 1.566 Y
+- 47.9 0.316 Y
+- 42.1 1.185 Y
+- 39.2 21.75 N
+- 36.2 27.66 N

Bare alloy oxidation data are ~l~,s~,~Led in Figures 3 and 4. Both Figures compare the test results for CMSX-lORi and CMSX-12Ri alloys to results from i-l~nti- ~1 tests rol.l.ed on the DSM002, CMSX-4 and CMSX-4+Y (120 ppm) alloys. The data ~ ,sellLed in these Figures complements the data reported in Table 28 above. Figure 3 ilhlctr~t.os the results of tests performed out to about 375 cycles at about 2012~F, while Figure 4 illustrates the results obtained at about 1886~F.
Figure 5 illustrates a similar alloy capability colllpalisoll, except for bare alloy hot corrosion resistance. The burner-rig tests were performed to about 120 hours duration at about 1742~F with ingestion of 2 ppm salt.

S~TiT~T~ SHEET

WO 94/0061 1 ~ ~ PCr/USs3/06213 21~72 Additional alloy compositions were defined in accordance with this invention forthe purpose of further optimi7in~ alloy solution heat ~ l rh~r~rtrri~ti~s, alloy stability, and creep-rupture ~ 11, while m~int~ining the extremely good oxidation, hot corrosion and thermo-mf rh~nir~l fatigue strengths already achieved with the invention.
Table 41 below reports the aim rll_."i~l. ;Fs for ~ ition~l m~tlori~l~ tested, which provide an even better blend of useful r~ f - ;--~ prope.ly rh~ ct~ Lics than the above-~lesrribe~ alloys. These op~illli~ed compositions typically contain lower ch.u Ulll and cobalt contents than the materials described in Table 1 above. Fu~ ore, these ~ L;...;~ecl alloys typically contain higher .l..i.;.--.., lower l..~ - and lower phasial stabilitY number NV3B

U~ SHEET

~, ALLO~ C B Cr Co Mo ~I Cb Ti Al Ta Re Hf Ni Nv3B* 1 2 3 4 ~' CMSX-lOM - - 2.0 1.75 .40 5.4 .08 .24 5.78 8.2 6.5 .03 BAL 1.50 11.9 6.02 14.3 20.5 G -lOK Mod - - 1.9 2.0 .35 5.3 .05 .lS 5.83 8.3 6.5 .03 BAL 1.49 11.8 5.98 14.33 ZO.45 -lOM Mod - - 1.8 1.6 .30 5.3 .05 .12 5.90 8.2 6.6 .03 BAL 1.47 11.9 6.02 14.27 20.4 E~ CMSX-12F - - Z.O 1.8 .40 4.5 - .3S 5.80 8.8 6.5 .03 BAL 1.50 11.0 6.15 14.95 20.2 ~i -12D Mod - - 1.9 2.0 .40 4.8 - .40 5.75 8.6 6.5 .03 8AL 1.49 11.3 6.15 14.75 20.3 CX:
~5~
-12F Mod - - 1.8 1.6 .35 4.4 - .12 5.92 8.7 6.6 .03 BAL 1.44 t1.0 6.04 14.74 20.05 _~

Key: 1 - 11 + Re 2 - Al + ti 3 - Al + Ti + Ta + Cb 4 - ~J + Re + Ho + Ta * Calculated using PUA
Y-35 Method WO 94/0061 1 ~ 7 2 PCr/US93/06213 Table 42 below reports the chPmi~triPs for additional alloy heats (200-320 lb.
qll~ntitiPs) As with the alloys reported in Table 1 above, the alloys having ~Liuli~d compositions were produced using production-type procedures, and were made into test bars and test blades by Vd~;UU I iuv~~ casting.

V-l VIM FURNACE HEAT CHEMISTRIES

ALLOY HEAT NO. C B Cr Co Mo U Cb T; Al Ta Re Hf Ni CMSX-12D VG 30 .001 <.001 2.34 3.2 .46 4.5 <.05 .50 5.60 8.8 6.3 .03 BASE
CMSX-lOK VG 31 .002 <.001 2.Z 3.3 .40 5.4 .10 .31 5.68 8.5 6.3 .03 BASE
CMSX-12D VG 35 .001 <.002 2.5 3.2 .46 4.7 <.05 .49 5.65 8.7 6.2 .03 BASE
CMSX-10I VG 36 .001 <.002 2.3 3.2 .40 5.5 .10 .31 5. n 8.3 6.3 .03 BASE
CMSX-10M VG 37 .001 <.002 2.0 1.7 .41 5.4 .09 .26 5.80 8.2 6.5 .03 BASE
CMSX-12F VG 38 .001 <.002 2.0 1.8 .42 4.5 <.05 .35 5.81 8.8 6.5 .02 BASE
CMSX-12D VG 44 .D07 <.003 2.5 3.2 .47 4.6 <.05 .50 5.62 8.8 6.2 .0Z BASE
CMSX-12D VG 45 .001 <.003 2.5 3.2 .47 4.7 ~.05 .50 5.6Z 8.8 6.3 .0Z BASE
CMSX-lOK VG 46 .OO1 <.002 2.3 3.3 .40 5.5 .10 .31 5.67 8.3 6.3 .03 BASE
CMSX-10K VG 47 .001 ~.002 2.3 3.3 .41 5.5 .10 .30 5.72 8.3 6.3 .03 BASE
CMSX-lOK VG 76 .001 <.002 2.0 3.0 .36 5.3 .08 .22 5.75 8.2 6.4 .03 BASE
CMSX-lOK VG 77 .001 ~.002 1.9 2.0 .36 5.3 .05 .17 5.81 8.4 6.5 .04 BASE
MOD
CMSX-10M VG 78 .001 ~.002 1.8 1.5 .33 5.3 .06 .12 5.92 8.2 6.6 .03 BASE
MOD
CMSX-12D VG 79 .001 ~.002 1.8 2.0 .40 4.9 ~.05 .21 5.78 8.6 6.5 .03 BASE
MOD
CMSX-12F VG 80 .002 ~.002 1.8 1.6 .38 4.5 ~.05 .14 5.92 8.8 6.6 .02 BASE
MOD
CMSX-10K VG 81 .001 ~.002 2.1 3.1 .36 5.3 .08 .22 5.70 8.2 6.4 .03 BASE
CMSX-10K VG 91 .001 ~.003 2.0 3.1 .37 5.4 .08 .21 5.76 8.2 6.5 .03 BASE
Table 43 below reports heat Llc<~ detail for the o~Lu~ d alloy compositions.
They typically require solution heat Ll~ .l to 2490-2500~F peak process L~ dLul~, which generally results in complete ~y' solutioning without the oc-;ul~ ce of incipient melting. A three-step aging Lle~ was lltili7P-l S~ SHEET

WO94/00611 ~ 3 ~ ~ 7 2 PCT/US93/06213 Heat Treatment Detail PEAK SOLUTION TEMP. Xy SOLUTIONED~ PRIMARY V AGING+ SECONDARY V AGING+
ALLOY ~F C
CMSX-10K 2490 1365 100 Z106~F/6hrs 1600~F/24+1400~F/30 CMSX-12D 2490 1365 100 2106~F/6hrs - 1600~F/24f1400~F/30 CMSX-10M 2499 1370 100 2106~F/6hrs 1600~F/24+1400~F/30 CMSX-12F 2499 137099.0-99.5 2106~F/6hrs 1600~F/24+1400~F/30 -10K MOD 2490 1365 100 2106~F/6hrs 1600~F/24+1400~F/30 -10M MOD 2499 1370 100 2106~F/6hrs 1600~F/24+1400~F/30 -12D MOD 2490 1365 100 2106~F/6hrs 1600~F/24+1400~F/30 -12F MOD 2499 1370 99.5-100 2106~F/6hrs 1600~F/24+1400~F/30 ~Determined by visual estimation +Specimens air cooled from aLL a~ing tre~i ,L~

The optimized alloy coll~osiLiorls were eva~ t~cl However, signifir~nt data was generated for the CMSX-lOK and CMSX-12D compositions, while some test results were gcllcl~cd for the r~m~ining compositions reported in Table 41 above.
Table 44 below reports the results of stress- and creep-rupture tests undertakenwith CMSX-lOK specimens. Variously sized test bar and blade ~eciul~ s, which were cast at hl~u~llial sources, were utilzed for these tests. The test results show c~ llely good stress and creep-rupture ~ pcl~ies for these alloys.

T~T~ SHEEI

CMSX-101C ALLOY STRESS- AND CREEP-RUPTURE ~ATA TIME IN HRS
RUPTURE TIME FINAL CREEP READING TO REACH
TEST CONDITION HRSX El X RA t, HRS % DEFORHATION 1.QX 2.0X
1675-F~75.0 ksi 153.12Z.028.2 148.6 15.868 2.6 26.9 t913-C/517 MPa) 174.221.329.9 173.0 19.471 4.1 30.1 177.1 28.032.1 176.6 22.934 3.224.9 144.6 25.928.7 144.0 22.431 4.923.5 166.7 28.030.0 166.3 23.971 7.528.6 1750FX50.0 ksi L1D~426.0 J - 41D~4 4.749 1 i. 59.5 954 C~345 MPa) ~78.126.0 ,4. 37*.8 4.783 0 i.~ 96.9 1 0 .4 26.0~5. 400.8 3.538 9 i.3 37.9 39h.8 36.53 . i396.6 2.691 60. ' 19.4 37V.8 22.5 . 37h 6 9.364 9 40.6 1800-F~36.0 ksi 746.330.732.0 744.7 28. 28 402.0 466.6 ~982-C~248MPa) 7E .6,0.0i4.1 78 .2 27.,14 L41.; 505.2 5 D.1 4.230.0 53L.6 1 . 94 37.303.6 6 ,.8 8.9 8.1 67-.6 1 .322 ,89.450.9 6~n.0 6.8 0.2 69X.4 Z4.839 ,04.D 412.6 *77;.5 27.7 7.0 774.2 2-i. 77 ':36. 505-7 * *~ _ D05.~; ~
*809.6 29.732.1 807.7 27.896 519.8 568.1 1850~F~36.0ksi 303. i32.9 7.1 308.3 ,1.302 75.3 1_0.0 (1010~C/248 HPa) , .'.22.4 6.2 311.1 2. 4 155. 3 1~3.
3 .' 17.8 4.8 313.1 7. -2 186., 2 2.-: DO., 24.5 7.6 359.8 -2.3*0 203.4 2,3."
3~~. ~ .4 8.2 290.7 ~1.. 8 165.3 1X8.3 3 D. i 7 4 8.2 325~0 S v1 144 3.8 ;.51 .4 6 .6 ~.51 .0 0~.0 ,.4i0.4 30~.6 21.833 ~L ;, 9 .0 8D.4 .9 9.728 i.4 19.817 _i~.X 6n.5 _ 20.o -----96.332 i. 1 21 ~X4D , 7.8 93.
'5 .8 n 4 9 3 25 .8 16.~ 1~ ,X. 6-i.
329.8 9.5 5.8 32V.0 17. 3 O,L14.3 * _i63.4 5.3~1.0 36 .8 13. ;6U '' .7 5 '. i * 339.9 21.431.4 33~.3 21.42 1:~0.2 1 .
* ** - - - - 2 4.1 * 338.1 14.026.2 337.2 12.981 232.6 260.2 1976 F/28.1 ksi108.522.8 30.4 107.8 19.41 39.4 6.2 (1080 C/194 MPa) 105.727.7 29.2 105.6 26.81 44.1 i8.0 112.7 27.531.1 112.5 24.06: 44.5i9.6 101 .2 29.037.6 100.8 20.43' 30.7' 8.3 90.8 31.43 .2 90.3 24.77- 10.9~i3.1 81.2 35.73 .7 - - - -72.6 - 23.5 97.0 25.53:~.295.0 20.800 33.147.8 100.6 28.03 .3 100 L 24.890 37.8i2~
93.4 29.13 .1 93 28.746 30.345.~
95.3 27.538.5 94. 21.202 37.5~0.3 94.6 25.540.2 93.~ 19.415 41.74.
*109.3 29.635.1 109.1 25.613 39 7-5 L
*105.8 30.433.8 105.5 26.232 42. 5.8 ** * -- -- 5 *109.8 25.933.9 109.3 19. '47 5~.~ 65.7 *83.1 20.029.3 82.1 16. 71 2 i.3 42.7 *76.1 15.924.3 76.0 14.X84 2 .738.1 *73.2 15.929.4 71.5 13.r36 25.139.1 *97.1 25.1Z3.5 96.0 20. 00 2r.544.4 T~l~UTE SHEET

WO 94/00611 ~ 7 2 PCI'/US93/06213 TABLE 44. CON.TINUED

TIME IN HRS
RUPTURE TIME FIUAL CREEP READING TO REACH
TEST CONDITION HRS X El % RA t. HRS% DEFORMATION 1.0X 2.0X
1976~F/18.85 ksi 751.221.7 28.3 750.4 19.963 352.7 469.5 (1080~C/130 MPn) 598.828.3 28.4 597.4 26.745 85.6 267.1 5 n .2 23.2 24.2 572.6 21.393253.9 340.2 528.8 22.4 25.6 526.6 19.46257.4 213.2 787.6 22.7 32.6 787.3 20.841265.8 498.1 70'.1 27.0 33,7 39 .3 17.9 26.0 76L.0 22.6 27.9 763.7 22.044326.1 447.3 648.0 16.6 17.~ 647.2 15.384258.5 387.0 52-.3 26.9 34.~ 526.4 18.976166.8 294.3 48~.~ 16.1 28.' 486.6 13.975175.5 284.7 714.3 25.5 39.~ 713.8 23.576309.0 552.9 * 742.~ 27.2 33.~ 74Z.6 25.578344.7 450.5 * 707.4 22.5 30.6 707.2 21.315290.8 414.7 ~ 618.' 21.2 18.8 * 562.8 17.3 24.4 * 436.4 15.7 16.9 433.1 15.580 * 411.6 10.7 17.1 411.Z 10.64881.5 238.5 * ** - - - -236.5 595.8 21.8 ~0.7 595.0 21.61263.9 '9Z.O
632.1 18.6 '8.9 631.3 17.166188.8 _i62.6 646.6 23.9 ~'7.4644.6 20.277258.6 376.5 706.9 29.6 ~1.4 704.9 24.728211.9 ,85.4 699.2 21.8 ~0.7 698.8 19.584110.5 356.0 * 726.2 23.9 ~7.1 725.3 21.555360.5 440.4 1995~F/27.5 ksi 81.1 30.6 34.6 80.8 26.770 29.1 40.9 (1090~C/190 MPn) 2012~F/14.5 ksi 923.726.7 ''7.5 921.7 20.433 154.3 530.7 (1100~C/100 MPa) 80'.225.1 5.9 800.2 17.830 92.9 430.7 87~.4 18.4 '0.5 873.7 17.249204.2 440.5 100i.4 19.5 9.2 9 n .3 23.9 ''7.2971.9 21.91285.5 451.8 99-.8 22.6 8.5 990.2 18.238497.0 646.5 2030~F/18.85 ksi ''6,.918.3 26.7 262.8 16.085 115.6 ' 152.9 (1110~C/130 MPn) 348.724.8 30.0 374.4 20.774 111.6 207.8 * ~8'.3 30.0 34.3 280.7 26.564116.7 169.8 * ''9".1 17.6 29.6 290.5 15.035131.1 189.4 -5 8.5 * ' 2.5 14.9 13.6 * ' 9.5 - 8.5 * '~7.9 - 13.8 196.0 13.386 3.5 59.3 * '79.4 14.1 19.5 178.1 13.013 5.5 38.1 * ** - 98.9 * 311.4 21.7 25.7 311.1 20.961144.2 190.4 2030~F/23.93 ksi 87.4 21.9 27.0 87.3 21.802 35.1 47.5 (1110~C/165 MPn) 80.6 18.4 2Z.9 79.3 15.Z86 34.3 44.9 96.1 Z1.5 31.2 95.0 15.68717.4 40.8 ~9.6 24.1 34.7 99.6 20.67634.1 53.9 73.5 22.9 33.9 73.0 19.34123.2 37.4 3.2 31.' 86.6 20.50223.8 42.2 ,S'.' '5.1 39.
.~ 3.9 31.7 ~,.~ ,0.2 41.0 92.8 2'.60529.2 47 0 '2.2 31 7 82.1 1-.867 18.4 29.4 8L,3 ' 7.041.0 82.7 1~.00326.6 42.7 77.1 26.2 36.0 76.7 17.47836.6 46.1 89.1 25.7 33.8 87.7 17.16630.8 46.4 82.8 38.3 39.2 82.5 3,.07521.8 37.3 ~ 80.6 28.1 31.5 79.6 24.158 8.6 24.1 ~USSTlTUTE SHET

Wo 94/0061 1 . ~ ' PClr/US93/06213 TABLE 44. CONTINUED

TIME IN HRS
RUPTURE TIME FINAL CREEP READIUG TO REACH
TEST CONDITION HRS X E~ X RAt. HRSX DEFORMATION 1.0X 2.0X
67.1 ''7.035.5 66.30.~'4 '7.5 29.8 74.5 ''3.838.3 n .3'7.~~7 ''2.1 37.8 66.6 '9.2 34.5 65.5'~.-i~7 3.1 36.8 77.9 3 .6 i7.2 77.5~''.~'7 '9.1 34.6 * 100.2 ' .1 _5.7 96.3'~.'34 ''7.8 51.0 104.8 ,',.5~7.4 102.0''.886 ,8.3 57.1 74.6 ''.3 '5.1 56.0 .3 '5.7 74.6 i.2 '0.4 - - - -- 47.3 ~ 104.5 18.4 29.7 101.412.862 44.9 61.19 Z050~F/15.0 Ksi n 2.819.5 25.7n 1.0 17.012330.4 525.7 (1121-C~103 MP~) 551.420.3 27.5 524.4 15.8 1n.2 523.013.524 266.2356.5 3'8.3 6.8 '~.3 316.43.986 262.9295.5 i~i7.4 18.4 ''~.0 557.015.720 250.1381.3 ''i5.3 16.3 ~''.5555.014.471 204.3372.7 i'1.1 15 6 '.3 ,'8.8 8.4 '2.1 ~75.7 19.0 ''9.1675.318.076 166.6424.6 600.7 '4.6 ''5.7600.013.074 232.9425.7 573.6 ~2.4 7.9 573.320.727 109.0328.0 542.0 '1.7 -5.9 540.516.646 '92.4344.6 521.4 '7.5 ' 7.0521.212.517 327.9398.2 619.2 '4.9 ''9.1619.114.395 '80.8396.4 646.3 '7.7 1.0 645.515.110 ''03.8419.7 582.9 9.5 ''7.6580.87.222 '55.7406.0 415.8 14.2 3.5 429.0 22.3 Z5.1 - - - - 320.4 ~ ~ ~ - - 17.718,i.7 666.3 20.8 ''8.4665.0'8.694 9.1 8 .4 597.3 14.6 ~7.9 595.8'1.641 75.0344.6 597.3 14.6 7.9 595.8'1.641 75.034~.6 683.9 26.6 .1.4 683.0"5.604 9.512~.6 670.9 17.9 '8.1 670.5'6.094 70.5 28~.0 ~ 454.6 21.5 30.3 454.421.210 168.127'i.7 2100DF/12.0 ksi 666.011.5 24.5665.6 10.469100.7 448.5 (1149'C/83 MPa) 597.920.0 32 0597.2 19.80914.3 76.0 662.1 24.6 ''5.1662.118.709 33.3188.7 575.0 17.1 '5.1 573.516.194 15.1116.1 4 n .2 20.6 33.7 472.419.563 0.6 22.5 543.4 23.1 ,5.3 542.321.563 24.7171.3 * 484.0 14.0 48.0 483.12.370 227.7452.5 - - - - 104.2 590 0 plus - - 590.88.070 22.5104.2 791.0 17.4 31.1 789.619.722 40.7145.2 746.9 16.5 31.2 745.915.607 61.2192.3 359.1 p~us - - 359.17.643 26.1 82.6 ~ 423.2 25.0 34.7 421.623.157 76.8209.5 2100~F/10.0 ksi 839.618.0 24.0 ~1149~C/69 MPa) 868.112.7 15.2 2150~F/10.0 ksi 566.110.6 18.33564.1 8.579193.6 443.1 (1177~C/69 MPa) ~00.615.6 25.Z399.8 15.5459.8 88.0 399.7 18.8 27.8 '63.7 10.7 22.0 493.7 23.5 31.4 491.922.850 2.6 25.2 L41,3 21.6 31.7 440.519.291 38.9124.6 427.6 14.2 25.1 426.59.801 258.2351.8 TITUTE SHEET

WO 94/00611 ~ 2 PCI~/US93/06213 . ;

TABLE 44~ CONTINUED
CMSX-lOK ALLOr STRESS- AND CREEP-RUPTURE DATA
TIME IN HRS
RUPTURE TIME FINAL CREEP READING TO REACH
TEST CONDITION HRS % EI X RAt. HRS % DEFORMATION 1.0% 2.0 * 472.3 19.4 33.5472.0 17.482 42.6 271.4 * ** _ _ _ - 135.8 * 426.6 21.2 39.2423.7 16.940 184.1 299.2 2150-F/12.0 ksl 264.1 8.0 27.3264.0 5.097 185.5 238.2 ~1177~C/83 MPa) 236.2 18.5 29.4234.8 16.343 '7.7 74.3 225.8 22.7 40.7223.8 12.435 '4.4 147.1 * 265.2 11.8 30.9264.0 8.747 ~8.0 193.8 * ** - - 4.4 * 215.9 26.8 28.6215.9 25.00 ~6.7 155.4 2200~F/10.0 ksi 163 2 14.7 41.9161.8 7.2n 70.7 139.9 (1204~C/69MPa) 110.6 13.0 43.1109.4 10.~ 7 16.1 42.5 136.1 9.4 42.1135.7 7.305 22.5 99.7 136.5 15.2 21.8 213.9 18.8 20.6 - - - -*) 205.1 17.8 39.4204.6 14.341 72.0 164.6 * ** _ _ - 4.1 * 2106~F/6 Hr/AC Primary Age ~* Interrupted Creep-rupture Test.
All resuIts ~ith 2075~F/6 Hr~AC Primary Age.
CMSX-lOK alloy tensile data are reported in Table 45 below. The tests were performed at te~ el~tures ranging from RT-2012~F. The test results show improvement relative ~o earlier alloy test results ~ senl~d in Table 36 above.

Tensile Data CMSX-1OK AIIoy TEST TEMP. o.lX PS 0.2% PSUTS ELONGRA STATIC MODULUS
~F ksi ksi ksi % XE, psi X 106 68 135.0134.7 136.6 10 9 20.3 135.3134.9 139.8 11 12 19.0 842 136.3136.0 139.7 17 14 18.8 133.9134.4 136.8 11 9 18.3 1202 137.2137.6 157.4 13 18 17.1 136.9136.9 157.4 15 28 17.2 1382 143.6144.6 177.7 15 8 16.4 140.7141.4 173.2 11 11 15.4 1562 143.7142.1 166.6 24 24 15.5 144.2141.7 168.5 22 20 14.9 1742 96.291.4 133.6 26 31 14.9 94.690.4 131.8 26 29 14.4 1922 74.778.0 107.6 28 34 13.0 73.777.4 107.030 35 12.8 Slle~ t SHEE~

WO 94/0061 I PCr/US93/06213 Dynamic elastic modulus data are reportcd in Table 46 below. The CMSX-lOK
alloy data are reported for test conditions ranging from RT-2012~F.

Dynamic Elastic Modulus, E
CMSX-lOK AL~oy E 19.2 19.1 18.9 18.7 18.2 psi X 106 E 17.3 16.8 16.3 15.3 14.4 psi X 106 E 13.1 11 6 psi X 106 Elevated Lcmycldlulc (1202-1922~F) impact data for CMSX-lOK and CMSX-12D
~.~echllcl~c are reported in Table 47 below. G)~1)A~ ;.con to other material capabilities can be made by review of the l~,s~ccLive tables 30 and 37, above.

~UB~ SHEET

WO94/00611 2 ~ $ ~ ~ ~ 2 PCT/US93/06213 .

Impact Data ALLOY ALLOY

~F IMPACT ENERGY, JDULES IMPACT ENERGY, JOULES
1202 21, 28, 29 22, 24, 29 1382 30, 28, 26 32, 30, 29 1562 21, 23, 18 23, 25, 21 1742 28, 20, 17 19, 44, 38 1922 63, 54, 50 34, 33, 53 Plain low cycle fatigue data for CMSX-lOK and CMSX-12D specimens is reported in Table 48. The tests were pc.rol led at 1382~F,1562~F and 1742~F, respectively, with R=O and 0.25 Hz test conditions. C~ )dldLive results are found above in Tables 31 and 38"~e~;lively.

Plain Low Cvcle Fatique Data CMSX-10K Alloy; R=0, 0.25 Hz TEST TEMP ~F PEAK STRESS, ksi CYCLES BROKEN
1382 150.8 8088 Y
137.8 11,120 Y
137.1 21,490 Y
123.3 45,460 Y
119.0 122,111 N
1562 150.8 912 Y
1~2.3 1688 Y
1,7.8 5101 Y
1-3.3 10,640 Y
1~8.8 54,270 Y

1742 101.5 9227 Y
84.1 *22,487 N
* Test stopped: Specimen pul led out of threads SU~S~illll~ SHEET

WO 94/0061 1 - ' - PCI-/US93/06213 ~3~2 -68-TABLE 4 8, CONTINUED

CMSX-1ZD ALLOY; R=0, 0.25 Hz TEST TEMP ~FPEAK STRESS, ksi CYCLES BROKEN ?
138Z 150.8 18,197 r 137.8 '5,290 Y
127.6 48,450 y 121.8 35,886 Y
116.0 1~6 893 N
110.2 101 81Z N

CMSX-lOK notched low cycle fatigue (K~ = 2.2) data is reported in Table 49 below. The tests were pclr lllled at 1742~F, R=O and 0.25 Hz test conflition~.
ColllpaldLive results are found above in Tables 32 and 39, lci,~c~ivcly.

K=2.2 Notched Low Cycle Fati~ue Data CMSX-10K AlLoy; 1742~F, R=0, 0.25 Hz PEAK NOMINAL STRESS, LIFE, CYCLES BROKEN ?
ksi 87.0 11,070 Y
75.4 41,660 Y

Bare alloy oxidation data for CMSX-lOK and CMSX-12D ~c~ ..clls are reported in Table 50 below. The tests were pclr~ lled with test conditions of 2012~F, 0.25 ppm salt and cycled four times per hour. Test duration was 200 hours, or 800 cycles. The test results intlir:~te that both alloys exhibit extremely good resi~t~n~e to oxidation.

S~BS I ~ SHEET

, $ ~ 2 Bare Alloy Oxidation Data CONDITIONS 2012~F; 0.25 ppm Salt; Cycled 4 times per hour TEST DURATION 200 hours (800 cycles) CMSX-lOK - 0.2 mrn Loss on RESULTS Diameter CMSX-12D - 0.44 mm Loss on Diameter Both alloys ~elro,Lued as good or better SIGNIFICANCE than CMSX4;
CMSX-10Ri and CMSX-12Ri results illustrated in Fig. 3 Figure 6 ill~ rs the results of initial mea~.urt~ ,.lL~. taken on corrosion pinshaving CMSX-lOK and CMSX-12D compositions, which were run at 1742~F, 2 ppm salt conditions out to about 200 hours.
CMSX-12D stress- and creep-rupture data are reported in Table 51 below, while this alloy's l~ ecLive tensile ~lupelLies for tests con-h~rt.ocl at RT-2102~F conditions are reported in Table 52 below.

S~8~ SHEr 213~72 ~

CMSX-1ZD ALLOr STRESS- AHD CREEP-RUPTURE DATA
TIME IN HOURS
RUPTURE TIME FINAL CREEP READING TO REACH
TEST CONDITSON HRS % El % RA t, HRSX DEFORMATION 1.0% 2.0%
1675-F/75.0 ksi llZ.Z Z0.1 Z3.8 lll Z18.Z3Z 1.6 1Z.0 (913-C/517 MPa) 109.6 19.8 22.8 108.616.246 2.1 9.9 1750-F/50.0 ksi 394.4 28.5 31.0 393.124.805 178.2 231.3 (954-C/345 MPa) 374.9 28.1 30.9 373.323.876 175.7 225.1 '1800-F/36.0 ksl 611.9 26.0 35.2 611.825.725 306.9 369.5 (982-C/248 MPa) 592.3 29.7 31.7 591.627.977 308.4 366.5 693.1 25.122.8 692.723.926378.5441.6 ~" ~ _ - -459.9 1850-F/36.0 ksi 237.5 ''0.529.9 36.61~ 77 ' '5.h 15h.4 (1010~C/248 MPa) 264.0 3.9 26.2 ' 62.52' . 62 '' 3.~ 15' .8 5~.~ '4.824.6''51.12 '.n49'~'5 ~15' 1 O . '~8.833.105.02~.'00 ' 7,18'~ 8 ''5;.;' 9.6~.7''54.4' 8.3 8';9.''163.1 ~i. ' ~1.3_3.~ 64.8 .~.~6 '~6.169.6 '''~,.,-5.8''~.~''78.0'4.~'~1''7.7164.6 ~ . '~5.1. ~.~'45.54. '2 5.'141.7 *2~'.029.9,~.~ 284.6'~7.9~7' 49.~174.5 2~'.3 24.6,'.0 291.9''4.2~9'01."149.2 260.4 27.1~'.2 264.9''4.3''397.'146.5 23".1 23.5b.4 238.7' 9.7 8122.3147.3 ~~* - - - 139,L
~ 320.5 22.829.5 319.420.654194.~216.8 1922-F/32.63ksi 105.020.132.0 103.516.10739.0 55.9 (1050~C/225HPa) 105.832.537.5 104.924.88742.2 56.9 1976"F/28.1ksi 75.''4.4 19.6 7~.8 11.76538.1 46.4 (1080-C/194HPa) 101."'5.025.5 98.7 20.43340.7 52.7 100.8 '-7.826.6 9,.. 9 21.65845.0 54.0 95.R ''9.936.09' .825.347 37.150.4 86.a Ø030.8 a,.924.506 3.619.7 95.~ .4.738.6 93.423.003 41.454.Z
93.7 Z5.337.0 93.6' ~.7Z1 35.~48.1 97.7 Z4.037.6 97.5"'.918 35._49.5 100.828.73-.4 100.4''~.1644' .'~54.1 ~8.~ 30.536.Z 88.8'~.500 "8.;49,9 86.r 24.635.4 85.3 ~.215 _.~45.Z
~4 .639.037.5 83.4''4.246 '~.039.9 '9.0 26.364.8 76.617.737 ,~.143.5 *,~* _ _ -- -- ~ O
101.125.428.8 99.119.064 45.957.8 85.4 25.735.3 84.321.4Z4 27.142.9 1976-F/18.85 ksi 576.0 Z3.9 ~8.0 575.522.40 Z40.1 34' .8 (1080-C/130 MPIl) 653.6 27.1 ,0.0 653.524.514 205.0 35~.7 618.624.4'8.7 618.024.047141.0294.3 687.228.1,2.5 685.524.805353.343~.9 544.314.7_2.3 54Z 712.314319.138 .2 594.1Z5.034.8 593.7Z4.809 30.4Z04.6 6Z5.716.925.6 6Z7.716.868Z58.0377.3 6Zl.320.0Z8.0 619.718.805ZOZ.2359.2 ~ 6Zl.5 ZZ.ZZ9.7 6Zl.521.49Z263.9377.8 * 591.6 28.732.8 591.326.922276.0356.3 _ - - 300.5 ~JB~I~IUIt S~IEET

TABLE 51. CONTINUED

TIME IN HOURS
RUPTURE TIME FINAL CREEP READINC TO REACH
TEST CONDIT~ONHRSX El X RA t. HRSX DEFORMATION 1.0X Z.0%
1995-F~27.5 ksi77.027.8 37.0 75.915.867 25.3 36.4 (1090~C/190 MP~) 2012~F/14.5 ksi816.117.9 Z5.5 836.6 16.222 115.0 498.4 (1100~C/100 MPn)644.2 19.325.4 643.1 15.538 410.0 482.5 1014.7 11.412.4 1012.810.43390.3 486.2 Z012~F/25.38 ksi66.430.4 36.5 65.622.45726.1 34.9 (11oo-c/1T5 MP~)70.433.0 40.1 70.225.29421.6 33.6 2030-F/23.93 ksi74.629.3 32.5 72.820.31226.9 37.9 74.6 25.531.3 72.9 17.439 32.942.2 82.0 28.029.8 80.9 22.297 21.737.2 89.0 24.133.1 86.9 15.458 28.445.4 V0 1 26.634.9 89.1 17.031 44.155.3 89.4 27.334.9 87.6 19.087 30.546.3 '5.7 ~.333.2 74.3 11.315 33.346.3 '4.7 '~.034.1 74.6 15.939 21.736.8 39.3 .928.4 O5.~ .524.7 18 , '~.'16.2 8.3 16.~15 3.77.7 86. 3 .838.6 B5.8 28. 07 12.931.1 7'.' ~~.,32.9 '6.~ 19.-66 11.9'7.2 77., 3 .O36.7 77.~ 21.250 6.2'4.6 7~.9 ,5 L40 0 79 , 27.o91 0.9,4.8 ~ .0 3.040.5 70.; 17.~31 4.837.0 * R' .8 7.736.6 81.3 15. 15 '2.7L6.0 * ~3.9 34.3,8.6 83.3 26.080 5.942.3 '5.9 40.0,8.0 74.9 24.783 31.841.9 71.5 32.0,4.9 68.9 18.452 '1.735.4 ~2.4 22.2 8.0 71.2 21.872 1.0Z2.9 * ** - - 9.3 * 94.6 25.529.9 94.4 23.742 39.252.0 65.7 35.539.0 65.2 23.050 24.133.4 47.7 27.940.2 46.9 13.700 9.621.3 * 56.0 14.223.5 2030-F/18.85 ksi '54.5 11.3 30.6254.1 11.229 94.0 165.4 (1110~C/130 MPa) '92.1 22.7 30.9291.8 21.808 47.3 151.7 * 48.821.8 28.2 346.918.201159.4 226.7 ~ 41.826.9 55.6 241.86.47499.1 167.8 * 12.514.9 13.6 * *~ - - - - 130.2 2030~F/17.40 ksi332.1 22.Z Z7.Z 330.4 20.391 54.2 144.5 (1110-C/120 MPa) 2050~F/15.0 ksi515.1 18.8 23.8 513.1 15.217 21'.5 355.9 (1121~C/103 MPA)587 2 16.8 20.7 585.4 12.33~ 3T~.5 448.5 5P.9.4 12.315.9 589.0 11.0T-20~.5 403.3 6 5.4 '0.820.4 614.719.36~5~.5 222.6 5O5.1 8.528.5 564.3 16.59~35,.4 418.0 6,1.9 7.J28.4 631.915.830403.4 477.7 4~2.6 ~.~20.5 4~7.7 '.' 8.3 5~1.5 ~.~ -8.5 561.1 9.113129.3 391.7 4h3 1 ~.~ 4.2 461.4 7.376316.6 388.4 * 6~4.2 2 .~'6.9 623.721.386171.3 262.8 * 587.3 19.- 3.5 586.316.712236.9 403.3 *

SUB~lllllt SHEEr 7 ~ --TABLE 51. CONTINUED
CMSX-12D A~QY STRESS- AND CREEP-RUPTURE DATA
TIME IN HQURS
RUPTURE TIME FINAL CREEP READING TO REACH
TEST CONDITIONHRSX EL X RA ,t. HRS % DEFORMATIQN 1.0% "2,.0%
482.9 23.730.2481.220.389 28.4 169.4 336.7 13.337.9335.010.433 38.3 173.6 24.3 7.114.522.8 3.02113.0 19.4 * ** - -316.9 2050-F/19.58 ksi145.1 28.0 31.2143.9 i9.913 12.0 68.2 (1121~C/135 HPa~
2100~F/12.0 ksi L54.2 12.1 '4.3 (1149-C/83 MP~) '84.3 12.5 _2.6382.1 5,913 95.2 304.6 r74.6 16.6'6.1673.314.670 165.2 469.7 ,02.0 13.3,2.7 ~53.1 - '3 2 * ~31.8 16.0 5 4630.813.560 4'4.4 516.4 85.5 13.0'7.1584.29.4842,3.2 462.3 34.1 22.9 8.8532.217.201 ~4.2 102.1 667.8 17.9:3.8667.215.477 3~1.5 454.4 * ** - -'3.7 2150~F/10.0 ksi 169.0 24 6 59.1168.2 5.338 6.9 35.3 (1177~C/69 MPs) 356.5 11 6 42.1356.4 9.793 132.6 267.6 'h4.9 16.742.2 87.4 - 35.9 * 367.7 10.752.6366.94.01811.9 171.6 ,S2.6 - - 382.6 5.58830.2 92.2 ~1.9 14.544.1461.712.483 63.8 160 5 ~~7.2 25.935.9453.613.854 13.3 110 9 * ** - -177.5 2150~F/12.0 ksi 222.0 14.2 54.4219.5 2.024 58.6 218 6 t1177'C/83 MPa)* 301.9 18.339.2 300.2 12.751 102.9 236.6 * ~* , _ _51.7 2200~F/10.0 ksi 102.3 8.9 22.7100.1 6.302 8.0 43.6 (1204~C/69 MPa) 178.7 10.0 40.1178.6 9.854 20.5 61.0 76.9 8.923.1 - - - -133.7 14.720.4 * 196.0 9.931.1195.98.65130.5 82.3 * 199.4 17.440.2199.016.811 16.7 128.6 , _97.1 * 2106~F/6 Hr/AC Primary Age ** Interrupted Creep-rupture Test.
All results ~ith 2075~F/6 Hr/AC Primary Age.

S'~ SHET

-73~

Tensile Data CMSX-lZD AIloy TEST TEMP O.1X PS 0.ZX PS UTS ELONG RA STATIC MODULUS
~Fksi ksi ksi X %E, psi X lo6 68 137.4 137.Z148.8 11lZ 19.9 133.6 13Z.6 154.6 17 18Z0,3 84Z 138.7 138.7146.9 1415 18.6 139.8 140.1 145.3 13 1519.4 lZOZ 14Z.6 14Z.7163.0 1313 16.8 139.7 139.8 16Z.4 13 1317.0 1382 137.5 137.5161.0 1419 15.7 156Z 140.2 138.5168.5 Z4ZZ 15.Z
138.4 140.0 158.8 Z4 Z715.7 174Z 94.6 90.8 138.1 2835 14 5 95.1 90.8 136.0 27 3515.2 1922 69.8 7Z.5 100.4 2840 13.6 70.6 73.Z 101.8 Z8 3913.6 Z10Z 41.0 43.5 66.0 Z95Z 11.6 41.3 43.5 66.6 37 5411.7 Initial creep-rupture test data for CMSX-lOM and CMSX-12F specimens is reported below in Tables 53 and 54, respectively.

RUPTURE TIME FINAL CREEP READING TO REACH
TEST CONDITION HRS % EL X RA t, HOURS % DEFORMATION 1.0X 2.0%
1675~F/75.0 ksi * 241.4 Z5.Z 3Z.5Z40.6Z1.4ZZ15.5 56.3 (913~C/517 MP~) 1750~F/50.0 ksi ~ 433.4 23.5 30.6433.422.Z09ZZ4.1 271.1 (954~C/345 MP~
1800~F/36.0 ksi 812.5 2Z.8 Z9.7811.5Zl.8945Z6.4 583.5 (98Z~C/Z48 MP~) ~ 83Z.5 36.3 37.2831.433.464513.3 564.7 ~ 90Z.3 Z5.9 37.4 901.6Z4.806585.5637.Z
1850~F/36.0 ksi ~ 368.9 Z9.1 3~.0368.1-8.043 Zl6.4 ~41.6 ~1010~C/Z48 MP~)~ 338.7 3Z.l 38.8337.5'8.ZZ4197.7 'Z0.8 ,06.6 38.2 3-.1 305.3,4.139110.0'71.9 ''79.Z 40.5 3~.5 Z77.7,4.006lZ9.6'56.3 ;00.4 Z3.Z 3~.3 Z99.5~0.613167.4'94.9 S~TlTUrE SHEET

WO 94/0061 1 . PCI /US93/06213 7 2 ~

l'ABLl~ 53, CONTlNUED
CMSX-10M ALLOr STRESS- AND CREEP-RUPTURE PATA
TIME IN
RUPTURE TIME FINAL CREEP READING HRS TO REACII
TEST CONPITION HRS % EL % RAt, HOURS X OEFoRMATION 1.0X Z.0X
1976-F/Z8.1 ksi * 129 8 23.725.4127.320.141 63.6 77.9 (1080'C/194 MPn) * 120.7 19.829.7120.617 196 55.8 70.0 * 111.2 31.1 33.5110.929.11943.0 57.4 * 91 8 Z2.6 33 791.019.Z57 31.4 47.8 * 107.3 31.4 32.7106.123.85Z61 7 68.3 1976'F/18.85 ksi ~ 628.7 Z1.827.3627.220.507Z68.8 364 Z
(1080'C/130 MP~) ~ 505 1 Z8.834.0504.ZZ7.062 Z3 9 160.5 * 440 9 36.5 33 8439.23Z 847114 7196.7 ~ 8ZS.7 Z5.8 Z7.1825.~Z4.969350 5446.7 Z030'F/18.85 ksi ~ 278.9 13.930 3277.812.367 80 6 160.8 (1110~C/130 MPa) ZO30-F/z3~93 ksi * lZ2 1 25.633 4120.920.097 45.0 62 9 (1110-C/165 MPn) * 109.9 27.329.9109 724.963 41 6 57.3 97.6 30 8 33.597.233.590 2.9 10.1 92.9 28.3 31.392.523.808 33.3 46.9 * 101.8 29 4 32.9100.821.88321 9 43.2 2050-F/15.0 ksi ~ 447.2 21 830.1446.919.430 88.4 Z52.1 (11Z1-C/103 MPn) * 426.4 Z6.332 64Z5 5Z3.53217Z.3 272.4 * 401.5 29.6 30 2400.225.848167.5236.6 * 3n9 5 25.8 35.3388 318.53826Z 0Z93.3 502.7 21 6 30.9503.320.013162.5Z91.2 616 7 25.6 3Z.8616.025 199131.5347.3 Z1oo-F/1z~o ksi * 581.5 ll.Z23 0581 510.455297.7 393.6 ~1149~C/83 HPn) * 439.3 26.3Z4 8439.125.869140.3 251.9 * 396.4 26.1 34 6395.021 64170 1203.1 * 360.8 Z4.2 24.4359 221.83453.015Z.3 * 612.9 Z2 7 34.2612.421.508281.2395.9 Z150-F/10.0 ksi * 343.5 15.338.5342.911.968151.3 244.8 (1177-C/69 HPn) * 301 3 25 433 8299 418 100 56.3 162 6 * 316.7 27.0 30 4314 226.10139 4105.7 * 214.1 18.0 39 0213.314.42847 1114.8 ~ 536 8 17 2 42 0534 813.419221.3380.5 2150-F/12.0 ksi ~ 224.4 19.937.3222.918.898 8.7 57.7 (1177-C/83 HPn) ~ 192 3 12.328 7190.310.641 7 1 39.8 ~ 172.6 19.7 32.5170 314.187 7.5 42.8 * 168.8 25.6 37.8166.919.50759.1 96.2 * 369 6 8 8 28 9368.48 783118.1267.6 Zzoo~F/lo~o Ksi ~ 186.1 18.244 9185.317 445 15 4 69 4 (1Z04-C/69 MPn) * 2106'F/6 tlr~AC Prim~ry Age.
*~ Interrupted Creep-rupture Test SHEEr WO 94/0061 1 ,,c~ PCI~/US93/06213 TIME IN
RUPTURE TIME FINAL CREEP READING HRS TO REACH
TEST CONPITION HRS % EL X RA t, HOURS % DEFORMATION 1.0% 2.0%
1675~F/75.0 ksi * 199.8Z6.6 34.2197.0 Z1.502 8.1 34.0 ~913-C/517 MPa) 1750~F/50.0 ksi * 457.420.3 37.7457.3 18.056 255.1 306.4 ~954~C/345 MPa) * 519.732.4 34.5517.7 Z8.241 279.2 331.1 *551.7 23.1 32.3551.6 21.854280.4347.5 1800~F/36.0 ksi * 837.832.2 35.1837.3 31.Z08 479.2 565.3 ~982~C/248 MPa) 1850~F/36.0 ksi * 290.3Z8.2 37.6288.6 25.734 151 7 184.8 ~1010~C/248 MPa) * 298.336.2 42.0297.2 32.862 163.9 187.3 * 292.5 31.5 39.5291.0 29.619~32.2167.4 * 345.3 31.3 33.8343.6 27.245220.9236.0 1976~F/28.1 ksi * 128.7 28.8 34.8128.2 25.763 60.5 72.9 1080~C/194 MPa) * 81.3 25.8 37.8 80.1 17.825 40.0 48.6 *109.3 23.4 32.5108.9 22.49650.962.4 *109.2 30.8 35.5107.7 25.24340.055.8 1976~F/18.85 ksi * 782.5 25.3 31.4782.4 22.654 373.3 443.1 ~1080~C/130 MPa) * 567.3 26.2 37.1565.5 20.919 188.5 280.0 *507.8 30.3 39.1507.0 27.958221.0276.6 *538.2 34.8 38.6537.8 31.820222.1291.0 1995~F/27.5 ksi ~1090~C/190 MPa) 2012~F/14.5 ksi (1100~C/100 MPa) 2030~F/23.93 ksi * 56.3 30.4 42.0 55.7 21.806 16.4 24.5 ~1110~C/165 MPa) * 98.3 30.8 37.8 96.9 23.348 21.4 40 9 *81.9 19.8 40.481.5 18.86631.843.1 *88.7 34.9 36.288.0 25.70329.341.6 2030~F/18.85 ksi * 355.426.8 27.1 355.1 26.607 139.7 188.1 ~1110~C/130 MPa) 2050~F/15.0 ksi * 712.2 21.1 27.0711.3 20.870 74,3 325.3 ~1121~C/103 MPa) * 432.4 33.9 38.9430.7 29.991 79-5 211.2 * 442.1 34.5 32.4440.2 32.314206.8261.9 *463.3 34.6 37.7462.5 28.67687.1218.7 2100~F/12.0 ksi * 682.0 13.2 18.9681.9 13.080 367.9 500.3 ~ 1149~ C/83 MPa) 2150~F/10.0 ksi * 573.1 22.4 34.9571.3 Z0.297 159.3 249.3 ~ 1177~ C/69 MPa) 2150~F/12.0 ksi * ** - - - - 40 8 89.7 (1177~C/83 MPa) 2200~F/10.0 ksi (1204~C/69 MP~3) * 2106~F/6 Hr/AC Primary Age ** Interrupted Creep-rupture T~st f ~TUTE SHEET

While this invention has been described with respect to particular embo~im~nt~
thereof, it is a~palellL that llulll~,~ou~ other forms and modifications of this invention will be obvious to those skilled in the art. The appended claims and this invention generally should be construed to cover all such obvious forms and mo~lifir~tions which are within the true spirit and scope of the present information.

S~ I I IJ ~ ~ SHEr

Claims (6)

What is claimed is:
1. A single crystal casting to be used under high stress, high temperature: conditions up to about 2030°F characterized by an increased resistance to creep under such conditions, said casting being made from a nickel-based superalloy consisting essentially of the following elements in percent by weight:
Rhenium 6.2-6.8 Chromium 1.8-2.5 Cobalt 1.5-2.5 Tantalum 8.0-9.0 Tungsten 3.5-6.0 Aluminum 5.5-6.1 Titanium 0.1-0.5 Columbium 0.01-0.1 Molybdenum 0.25-0.60 Halnium 0-0.05 Carbon 0-0.04 Boron 0-0.01 Yttrium 0-0.01 Cerium 0-0.01 Lanthanum 0-0.01 Manganese 0-0.04 Silicon 0-0.05Zirconium 0-0.01 Sulfur 0-0.001 Vanadium 0-0.10Nickel + Incidental balance Impurities said superalloy having a phasial stability number N V3B less than about 1.65.
2. The single crystal casting of Claim 1 wherein said casting has been aged at atemperature of from 2050°F to 2125°F for 1 to 20 hours.
3. The single crystal casting of Claim 1 wherein said casting is a component for a turbine engine.
4. The single crystal casting of Claim 1 wherein said casting is a gas turbine blade.
5. The single crystal casting of Claim 1 wherein said casting is a gas turbine vane.
6. The single crystal casting of Claim 1 wherein said casting is further characterized by increased oxidation and hot corrosion resistance under said conditions.
CA002138672A 1992-06-29 1993-06-29 Single crystal nickel-based superalloy Expired - Lifetime CA2138672C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US905,462 1992-06-29
US07/905,462 US5366695A (en) 1992-06-29 1992-06-29 Single crystal nickel-based superalloy
PCT/US1993/006213 WO1994000611A1 (en) 1992-06-29 1993-06-29 Single crystal nickel-based superalloy

Publications (2)

Publication Number Publication Date
CA2138672A1 CA2138672A1 (en) 1994-01-06
CA2138672C true CA2138672C (en) 1999-07-06

Family

ID=25420866

Family Applications (2)

Application Number Title Priority Date Filing Date
CA002099358A Expired - Lifetime CA2099358C (en) 1992-06-29 1993-06-28 Single crystal nickel-based superalloy
CA002138672A Expired - Lifetime CA2138672C (en) 1992-06-29 1993-06-29 Single crystal nickel-based superalloy

Family Applications Before (1)

Application Number Title Priority Date Filing Date
CA002099358A Expired - Lifetime CA2099358C (en) 1992-06-29 1993-06-28 Single crystal nickel-based superalloy

Country Status (15)

Country Link
US (2) US5366695A (en)
EP (2) EP0577316B1 (en)
JP (2) JP2704698B2 (en)
KR (1) KR0126120B1 (en)
AT (2) ATE157126T1 (en)
AU (1) AU662227B2 (en)
BR (1) BR9302682A (en)
CA (2) CA2099358C (en)
CZ (1) CZ290913B6 (en)
DE (2) DE69313207T2 (en)
DK (1) DK0577316T3 (en)
ES (2) ES2106973T3 (en)
IL (1) IL106040A (en)
WO (1) WO1994000611A1 (en)
ZA (1) ZA934378B (en)

Families Citing this family (77)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5366695A (en) * 1992-06-29 1994-11-22 Cannon-Muskegon Corporation Single crystal nickel-based superalloy
US5688108A (en) * 1995-08-01 1997-11-18 Allison Engine Company, Inc. High temperature rotor blade attachment
US5695821A (en) * 1995-09-14 1997-12-09 General Electric Company Method for making a coated Ni base superalloy article of improved microstructural stability
EP1127948B1 (en) * 1995-10-13 2002-07-24 Cannon-Muskegon Corporation Hot corrosion resistant single crystal nickel-based superalloys
US5735044A (en) * 1995-12-12 1998-04-07 General Electric Company Laser shock peening for gas turbine engine weld repair
EP0789087B1 (en) * 1996-02-09 2000-05-10 Hitachi, Ltd. High strength Ni-base superalloy for directionally solidified castings
US6007645A (en) * 1996-12-11 1999-12-28 United Technologies Corporation Advanced high strength, highly oxidation resistant single crystal superalloy compositions having low chromium content
US5916384A (en) * 1997-03-07 1999-06-29 The Controller, Research & Development Organization Process for the preparation of nickel base superalloys by brazing a plurality of molded cavities
US5925198A (en) * 1997-03-07 1999-07-20 The Chief Controller, Research And Developement Organization Ministry Of Defence, Technical Coordination Nickel-based superalloy
US6332937B1 (en) * 1997-09-25 2001-12-25 Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” Method of improving oxidation and corrosion resistance of a superalloy article, and a superalloy article obtained by the method
FR2768750B1 (en) * 1997-09-25 1999-11-05 Snecma PROCESS FOR IMPROVING OXIDATION AND CORROSION RESISTANCE OF A SUPERALLOY PART AND SUPERALLOY PART OBTAINED BY THIS PROCESS
JP3184882B2 (en) * 1997-10-31 2001-07-09 科学技術庁金属材料技術研究所長 Ni-based single crystal alloy and method for producing the same
US6217286B1 (en) * 1998-06-26 2001-04-17 General Electric Company Unidirectionally solidified cast article and method of making
US6096141A (en) * 1998-08-03 2000-08-01 General Electric Co. Nickel-based superalloys exhibiting minimal grain defects
US6102979A (en) * 1998-08-28 2000-08-15 The United States Of America As Represented By The United States Department Of Energy Oxide strengthened molybdenum-rhenium alloy
US7816403B2 (en) * 1998-09-08 2010-10-19 University Of Utah Research Foundation Method of inhibiting ATF/CREB and cancer cell growth and pharmaceutical compositions for same
GB9903988D0 (en) 1999-02-22 1999-10-20 Rolls Royce Plc A nickel based superalloy
EP1038982A1 (en) * 1999-03-26 2000-09-27 Howmet Research Corporation Single crystal superalloy articles with reduced grain recrystallization
US20020007877A1 (en) * 1999-03-26 2002-01-24 John R. Mihalisin Casting of single crystal superalloy articles with reduced eutectic scale and grain recrystallization
US6343641B1 (en) 1999-10-22 2002-02-05 General Electric Company Controlling casting grain spacing
US6193141B1 (en) 2000-04-25 2001-02-27 Siemens Westinghouse Power Corporation Single crystal turbine components made using a moving zone transient liquid phase bonded sandwich construction
EP1184473B1 (en) * 2000-08-30 2005-01-05 Kabushiki Kaisha Toshiba Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof
GB0028215D0 (en) * 2000-11-18 2001-01-03 Rolls Royce Plc Nickel alloy composition
US20020164263A1 (en) * 2001-03-01 2002-11-07 Kenneth Harris Superalloy for single crystal turbine vanes
US7011721B2 (en) * 2001-03-01 2006-03-14 Cannon-Muskegon Corporation Superalloy for single crystal turbine vanes
DE10118541A1 (en) * 2001-04-14 2002-10-17 Alstom Switzerland Ltd Assessing life of thermal insulation layers subjected to temperature cycling, takes into account boundary layer stressing and growth of oxide layer
US6966956B2 (en) * 2001-05-30 2005-11-22 National Institute For Materials Science Ni-based single crystal super alloy
US20030041930A1 (en) * 2001-08-30 2003-03-06 Deluca Daniel P. Modified advanced high strength single crystal superalloy composition
US6986034B2 (en) * 2002-04-11 2006-01-10 Dell Products L.P. Setting a system indication in response to a user when execution of the system setup program is desired
US20040042927A1 (en) * 2002-08-27 2004-03-04 O'hara Kevin Swayne Reduced-tantalum superalloy composition of matter and article made therefrom, and method for selecting a reduced-tantalum superalloy
US8968643B2 (en) * 2002-12-06 2015-03-03 National Institute For Materials Science Ni-based single crystal super alloy
JP3814662B2 (en) * 2002-12-06 2006-08-30 独立行政法人物質・材料研究機構 Ni-based single crystal superalloy
JP4157440B2 (en) 2003-08-11 2008-10-01 株式会社日立製作所 Single crystal Ni-base superalloy with excellent strength, corrosion resistance and oxidation resistance
US20050224144A1 (en) * 2004-01-16 2005-10-13 Tresa Pollock Monocrystalline alloys with controlled partitioning
JP4266196B2 (en) * 2004-09-17 2009-05-20 株式会社日立製作所 Nickel-base superalloy with excellent strength, corrosion resistance and oxidation resistance
SE528807C2 (en) * 2004-12-23 2007-02-20 Siemens Ag Component of a superalloy containing palladium for use in a high temperature environment and use of palladium for resistance to hydrogen embrittlement
FR2881439B1 (en) * 2005-02-01 2007-12-07 Onera (Off Nat Aerospatiale) PROTECTIVE COATING FOR SINGLE CRYSTALLINE SUPERALLIAGE
EP1997923B1 (en) 2006-03-20 2016-03-09 National Institute for Materials Science Method for producing an ni-base superalloy
GB2440127B (en) * 2006-06-07 2008-07-09 Rolls Royce Plc A turbine blade for a gas turbine engine
GB0611926D0 (en) * 2006-06-16 2006-07-26 Rolls Royce Plc Welding of single crystal alloys
CN101652487B (en) * 2006-09-13 2012-02-08 独立行政法人物质.材料研究机构 Ni-base single crystal superalloy
EP2128284B1 (en) * 2007-03-12 2015-08-19 IHI Corporation Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE VANE USING THE SAME
US9499886B2 (en) 2007-03-12 2016-11-22 Ihi Corporation Ni-based single crystal superalloy and turbine blade incorporating the same
EP2047940A1 (en) * 2007-10-08 2009-04-15 Siemens Aktiengesellschaft Preheating temperature during welding
US8206117B2 (en) * 2007-12-19 2012-06-26 Honeywell International Inc. Turbine components and methods of manufacturing turbine components
JP5467307B2 (en) 2008-06-26 2014-04-09 独立行政法人物質・材料研究機構 Ni-based single crystal superalloy and alloy member obtained therefrom
JP5467306B2 (en) 2008-06-26 2014-04-09 独立行政法人物質・材料研究機構 Ni-based single crystal superalloy and alloy member based thereon
US8216509B2 (en) 2009-02-05 2012-07-10 Honeywell International Inc. Nickel-base superalloys
US8877122B2 (en) 2009-04-17 2014-11-04 Ihi Corporation Ni-based single crystal superalloy and turbine blade incorporating the same
EP2616679A2 (en) 2010-09-16 2013-07-24 Wilson Solarpower Corporation Concentrated solar power generation using solar receivers
EP2620514A4 (en) * 2010-09-24 2016-08-17 Univ Osaka Prefect Public Corp Re-ADDED Ni-BASED DUAL-PHASE INTERMETALLIC COMPOUND ALLOY AND PROCESS FOR PRODUCTION THEREOF
US20120111526A1 (en) 2010-11-05 2012-05-10 Bochiechio Mario P Die casting system and method utilizing high melting temperature materials
EP2684264B1 (en) 2011-03-10 2016-05-18 Ericson Manufacturing Company Electrical enclosure
EP2823074A4 (en) 2012-03-09 2016-01-13 Indian Inst Scient Nickel- aluminium- zirconium alloys
AU2013235508B2 (en) 2012-03-21 2018-02-08 Wilson 247Solar, Inc. Multi-thermal storage unit systems, fluid flow control devices, and low pressure solar receivers for solar power systems, and related components and uses thereof
US20160214350A1 (en) 2012-08-20 2016-07-28 Pratt & Whitney Canada Corp. Oxidation-Resistant Coated Superalloy
US8858876B2 (en) 2012-10-31 2014-10-14 General Electric Company Nickel-based superalloy and articles
US8858873B2 (en) * 2012-11-13 2014-10-14 Honeywell International Inc. Nickel-based superalloys for use on turbine blades
JP6226231B2 (en) * 2013-09-18 2017-11-08 株式会社Ihi Heat-shielding coated Ni alloy part and manufacturing method thereof
US20150308449A1 (en) * 2014-03-11 2015-10-29 United Technologies Corporation Gas turbine engine component with brazed cover
US9518311B2 (en) 2014-05-08 2016-12-13 Cannon-Muskegon Corporation High strength single crystal superalloy
EP3029113B1 (en) * 2014-12-05 2018-03-07 Ansaldo Energia Switzerland AG Abrasive coated substrate and method for manufacturing thereof
GB2536940A (en) 2015-04-01 2016-10-05 Isis Innovation A nickel-based alloy
GB2539959A (en) 2015-07-03 2017-01-04 Univ Oxford Innovation Ltd A Nickel-based alloy
FR3052463B1 (en) * 2016-06-10 2020-05-08 Safran METHOD FOR MANUFACTURING A NICKEL-BASED SUPERALLOY PART BASED ON HAFNIUM
US10682691B2 (en) * 2017-05-30 2020-06-16 Raytheon Technologies Corporation Oxidation resistant shot sleeve for high temperature die casting and method of making
FR3073527B1 (en) 2017-11-14 2019-11-29 Safran SUPERALLIAGE BASED ON NICKEL, MONOCRYSTALLINE AUBE AND TURBOMACHINE
FR3073526B1 (en) 2017-11-14 2022-04-29 Safran NICKEL-BASED SUPERALLOY, SINGLE-CRYSTALLINE BLADE AND TURBOMACHINE
EP3775304A4 (en) 2018-04-04 2022-01-05 The Regents of The University of California High temperature oxidation resistant co-based gamma/gamma prime alloy dmref-co
FR3081883B1 (en) 2018-06-04 2020-08-21 Safran NICKEL BASED SUPERALLY, MONOCRISTALLINE VANE AND TURBOMACHINE
US10933469B2 (en) 2018-09-10 2021-03-02 Honeywell International Inc. Method of forming an abrasive nickel-based alloy on a turbine blade tip
FR3092340B1 (en) 2019-01-31 2021-02-12 Safran Nickel-based superalloy with high mechanical and environmental resistance at high temperature and low density
RU2710759C1 (en) * 2019-03-06 2020-01-13 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Nickel-based heat-resistant alloy and article made from it
KR102197355B1 (en) * 2019-05-17 2021-01-04 한국재료연구원 Ni base single crystal superalloy
GB2584905B (en) * 2019-06-21 2022-11-23 Alloyed Ltd A nickel-based alloy
FR3100144B1 (en) 2019-09-04 2021-10-01 Safran Aircraft Engines PROCESS FOR MANUFACTURING A METAL PART LIMITING THE APPEARANCE OF RECRISTALLIZED GRAINS IN THE SAID PART
FR3124195B1 (en) * 2021-06-22 2023-08-25 Safran NICKEL-BASED SUPERALLOY, MONOCRYSTAL BLADE AND TURBOMACHINE

Family Cites Families (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3765879A (en) * 1970-12-17 1973-10-16 Martin Marietta Corp Nickel base alloy
USRE29920E (en) * 1975-07-29 1979-02-27 High temperature alloys
US4055447A (en) * 1976-05-07 1977-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Directionally solidified eutectic γ-γ' nickel-base superalloys
US4045255A (en) * 1976-06-01 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Directionally solidified eutectic γ+β nickel-base superalloys
US4209348A (en) * 1976-11-17 1980-06-24 United Technologies Corporation Heat treated superalloy single crystal article and process
US4116723A (en) * 1976-11-17 1978-09-26 United Technologies Corporation Heat treated superalloy single crystal article and process
US4169742A (en) * 1976-12-16 1979-10-02 General Electric Company Cast nickel-base alloy article
US4292076A (en) * 1979-04-27 1981-09-29 General Electric Company Transverse ductile fiber reinforced eutectic nickel-base superalloys
US4222794A (en) * 1979-07-02 1980-09-16 United Technologies Corporation Single crystal nickel superalloy
US4371404A (en) * 1980-01-23 1983-02-01 United Technologies Corporation Single crystal nickel superalloy
US4402772A (en) * 1981-09-14 1983-09-06 United Technologies Corporation Superalloy single crystal articles
US4801513A (en) * 1981-09-14 1989-01-31 United Technologies Corporation Minor element additions to single crystals for improved oxidation resistance
US4492672A (en) * 1982-04-19 1985-01-08 The United States Of America As Represented By The Secretary Of The Navy Enhanced microstructural stability of nickel alloys
US4589937A (en) * 1982-09-22 1986-05-20 General Electric Company Carbide reinforced nickel-base superalloy eutectics having improved resistance to surface carbide formation
US4492632A (en) * 1983-12-16 1985-01-08 Mattson Fred P Adaptor for external oil filter
US5043138A (en) * 1983-12-27 1991-08-27 General Electric Company Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys
US5035958A (en) * 1983-12-27 1991-07-30 General Electric Company Nickel-base superalloys especially useful as compatible protective environmental coatings for advanced superaloys
US4597809A (en) * 1984-02-10 1986-07-01 United Technologies Corporation High strength hot corrosion resistant single crystals containing tantalum carbide
US4643782A (en) * 1984-03-19 1987-02-17 Cannon Muskegon Corporation Single crystal alloy technology
US5077141A (en) * 1984-12-06 1991-12-31 Avco Corporation High strength nickel base single crystal alloys having enhanced solid solution strength and methods for making same
US4677035A (en) * 1984-12-06 1987-06-30 Avco Corp. High strength nickel base single crystal alloys
US4719080A (en) * 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
US5100484A (en) * 1985-10-15 1992-03-31 General Electric Company Heat treatment for nickel-base superalloys
US4908183A (en) * 1985-11-01 1990-03-13 United Technologies Corporation High strength single crystal superalloys
US4888069A (en) * 1985-11-01 1989-12-19 United Technologies Corporation Nickel base superalloys having low chromium and cobalt contents
US5068084A (en) * 1986-01-02 1991-11-26 United Technologies Corporation Columnar grain superalloy articles
GB2234521B (en) * 1986-03-27 1991-05-01 Gen Electric Nickel-base superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries
CA1291350C (en) * 1986-04-03 1991-10-29 United Technologies Corporation Single crystal articles having reduced anisotropy
US4915907A (en) * 1986-04-03 1990-04-10 United Technologies Corporation Single crystal articles having reduced anisotropy
US4849030A (en) * 1986-06-09 1989-07-18 General Electric Company Dispersion strengthened single crystal alloys and method
GB2235697B (en) * 1986-12-30 1991-08-14 Gen Electric Improved and property-balanced nickel-base superalloys for producing single crystal articles.
US5151249A (en) * 1989-12-29 1992-09-29 General Electric Company Nickel-based single crystal superalloy and method of making
US5366695A (en) * 1992-06-29 1994-11-22 Cannon-Muskegon Corporation Single crystal nickel-based superalloy

Also Published As

Publication number Publication date
AU4138393A (en) 1994-01-06
DE69320666D1 (en) 1998-10-01
CZ290913B6 (en) 2002-11-13
ZA934378B (en) 1994-01-13
IL106040A (en) 1997-02-18
EP0746634A4 (en) 1995-04-05
DE69320666T2 (en) 1999-05-12
EP0577316A2 (en) 1994-01-05
CA2138672A1 (en) 1994-01-06
BR9302682A (en) 1994-02-08
EP0577316A3 (en) 1994-06-15
ATE157126T1 (en) 1997-09-15
ES2121588T3 (en) 1998-12-01
DE69313207T2 (en) 1998-01-02
US5540790A (en) 1996-07-30
JPH07138683A (en) 1995-05-30
JP2881626B2 (en) 1999-04-12
EP0746634A1 (en) 1996-12-11
AU662227B2 (en) 1995-08-24
US5366695A (en) 1994-11-22
JP2704698B2 (en) 1998-01-26
DE69313207D1 (en) 1997-09-25
CZ9301304A3 (en) 2001-11-14
CA2099358A1 (en) 1993-12-30
WO1994000611A1 (en) 1994-01-06
KR940005817A (en) 1994-03-22
ES2106973T3 (en) 1997-11-16
CA2099358C (en) 1998-11-03
ATE170230T1 (en) 1998-09-15
IL106040A0 (en) 1993-10-20
JPH08505432A (en) 1996-06-11
DK0577316T3 (en) 1997-12-29
KR0126120B1 (en) 1997-12-26
EP0746634B1 (en) 1998-08-26
EP0577316B1 (en) 1997-08-20

Similar Documents

Publication Publication Date Title
CA2138672C (en) Single crystal nickel-based superalloy
EP0789087B1 (en) High strength Ni-base superalloy for directionally solidified castings
WO1994000611A9 (en) Single crystal nickel-based superalloy
EP0560296B1 (en) Highly hot corrosion resistant and high-strength superalloy, highly hot corrosion resistant and high-strength casting having single crystal structure, gas turbine and combined cycle power generation system
US5100484A (en) Heat treatment for nickel-base superalloys
JP2000512341A (en) Nickel-based superalloys
AU621149B2 (en) Improvements in or relating to alloys
EP2188401A1 (en) Nickel base superalloy compositions being substantially free of rhenium and superalloy articles
EP0684321B1 (en) Hot corrosion resistant single crystal nickel-based superalloys
IL91793A (en) Cast columnar grain hollow nickel base alloy article and alloy and heat treatment for making
EP1127948B1 (en) Hot corrosion resistant single crystal nickel-based superalloys
KR100224950B1 (en) Nickel-base superalloy of industrial gas turbine components
AU708992B2 (en) Hot corrosion resistant single crystal nickel-based superalloys
JPH09184035A (en) Production of nickel-base superalloy, and nickel-base superalloy excellent in high temperature corrosion resistance and high temperature strength
JP3209902B2 (en) High temperature corrosion resistant single crystal nickel-based superalloys
GB2159174A (en) A nickel-base alloy suitable for making single-crystal castings
CZ293486B6 (en) In hot state corrosion resistant monocrystalline nickel-based high-alloyed alloy, monocrystalline product and monocrystalline casting
CA2160965C (en) Hot corrosion resistant single crystal nickel-based superalloys
IL91634A (en) Process for preparing improved and property-balanced nickel-base superalloys for producing single crystal articles

Legal Events

Date Code Title Description
EEER Examination request