FIELD OF THE INVENTION OOO 1] The subj ect matter disclosed he rein re lates generally to high strength stainless steels. More particularly, the subject matter disclosed herein generally relate s to marte nsitic stainless ste el alloys and related methods o f manufac taring and use (e.g., in turbine rotating components).

BACKGROUND OF THE INVENTION

[D002] The metal alloys use d for rotating compore nts of a gas turbine, particularly the compressor airfoils, including rotating and statio ary blades, must have a combination of high strength, toughness, fatigue resistance and other physical and mechanical properties in order to provide the required operational properties of the se mac lines . I n addition, the alloys used must also have sufficient re sistance to corrosion damage due to the extreme environments in whi h turbines are operated, including xposure to various ionic reactant species (e.g., various species that include chlorides, sulfates, nitrides and other corrosive species). Corrosion can also diminish the other necessary physical and mechanical properties, such as the high cycle fatigue strength, by initiation of surface cracks that propagate under the cyclic thermal and operational stresse s associated with operation of the turbine.

POOJ Various high strength stainless steel alloys have been proposed to meet these and other requirements, particularly at a cost that permits their widespread use. In particular, precipitation hardenable, martensitic stainless steels have been proposed and used. While such precipitation hardenable, martensitic stainless steels have provided the corrosion resistance, mechanical strength and fracture toughness properties described and are suitable for use in rotating steam turbine components, these alloys are still known to be susceptible to both intergranular corrosion attack (IGA) and corrosion pitting phenomena. For example, stainless steel airfoils, such as those used in the co repressors of industrial gas turbines, have shown susceptibility to IGA, str ss corrosion cracking (SCC) and corrosion pitting on the surfaces, particularly the leading edge surface, of the airfoil. These are believed to be asso iated wit various ele trochemical reaction processes enabled by the airborne deposits, e spe cially corrosive spe cie s pre sent in the deposits and moisture from intake air on the airfoil surfa es. Electroctemically- induced mtergranukr corrosion attack (IGA) and corrosion pitting phenomena o urring at the airfoil surf ces can in turn result in cracking of the airfoils due to the cyclic thermal and operating str sses experience d by the se components. High level of mo isture can result fro m use of online water washing, fogging and evaporative cooling, or various combinations of them, to enhance compressor efficienc Corrosive contaminants usually re suit from the environments in which the turbines are opeia ting because they are frequently placed in highly corrosive vironments, such as those near chemical or petro emical plants where various chemical species maybe found in the intake air, or those at or near ocean coastlines or other saltwater environments where various sea salts maybe present in the intake air, or combinations of the above, or in other applications where the inlet air contains c orrosive chemical species.

[D004] Due to the significant operatio al costs associated with downtime of an industrial gas turbine, in luding the cost of purchase d power to replace the output of the tuibine, as well as the cost of dismantling the turbine to effect repair or

replacement of the airfoils and the repair or replacement costs of the airfoils themselves, enhanc ments of the IGA resistance or pitting corrosion re sistance, or both, have a significant commercial value.

ΡΟΟ-Ϊ] Inviewof the above, stainle ss steel alloys suitable for use in tiirbme airfoils, particularly industrial gas turbine airfoils, in the operating environments described and having improved resistance to IGA, or corrosion pitting, or preferably both, are desirable and commercially valuable, and provide a competitive advantage.

BRIEF DESCRIPTION OF THE INVENTION OOOfj] Aspe cts and advantage s of the inve ntion will be set forth in part in the following description, or maybe obvious from the description, or maybe learned through practice of the invention.

P007] Forged precipitation-hardened stainless steel alloys are generally provided. In one e mbodime nt, the foig ed precipitatio n-hardene d stainle ss stee 1 alloy includes (e.g., comprises, consists essentially of, or consists of), by weight, about 14.0% to about 16.0% chromium, about 6.0% to about 8.0% nickel, about 1 .25% to about 1.75% copper, about 1.0% to about 2.0% molybde um (e .g, about 1 .5% to about 2.0% molybde num), about 0.001% to about 0 D5% carbon, a carbide forming element in an amount of about 0.3% to a out 0E% and greater than about S times that of carbon, the balance iron, and incidental impurities. In this embodiment the carbide forming el ment is selected from the group consisting of titanium, zirconium, tantalum, and a mixture thereof (e.g., selected from the group consisting of titanium, zirconium, and tantalum).

OOOS] For example, in one particular embodiment the carbide forming element is titanium. In to embodiment, the forged precipitation-hardened stainless steel alloy can include about 0.3% to about 0.7% titanium, with titanium being present in an amount greater than about 25 times that of carbon.

[DOO ⁰ ] In another embodiment the carbide forming element is zirconium. In this embodiment the forged precipitation-hardened stainless steel alloy can include about 0.3% to a out 0 .7% zirconium, with zirconium being present in an amount greater than about 8 time s that of carbon.

[DO 10] In yet another e mbodiment the carbide forming ele ment is tantalum. In this embodiment the forged precipitation- hardened stainless steel alloy can include about 0.4% to about 0.8% tantalum, with tantalum being present in an amount greater than about 12 time s that of carbon.

POI I] The forge d precipitation-hardened stainle ss steel alloy can further include, in particular e mbodime nts, up to 1 .0 perc ent mangane se ; up to 1.0 percent silicon; up to 0.1 percent vanadium; up to 0.1 percent tin; up to 0.030 percent nitrogen; up to 0.025 perce t phosphorus; up to 0.005 percent sulfur, up to 0.05 per ent aluminum; up to 0.005 percent silver; and up to 0.005 percent lead as the incidental impurities. [DO 12] Ξ uch prec ipitation-hardene d stainle ss steel alloys are particularly suitable for use in a tabine airfoil or other rotary turbine component.

[DO 13] The se and other feature s, aspec ts and advantage s of the present invention will become better understood with re fere nee to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

PO 14] A full and e nabling disclosure o f the present invention, including the be st mode thereof, directed to one of ordinary skill in the ail, is set tbrthin the

specification, which makes reference to the appended figures, in which:

PO 15] FIG. 1 is a sche rnatic c ross sectional side vie w of an exemplary gas turbine as may incorporate various embodiments of the present invention.

DETAILED DESCRIPTION OF THE INVENTION PO 16] Reference no will be made in detail to embodrme nts of the inve ntio n, one or more examples of which are illustrate din the drawings. Each example is provided by way o f e xplanation of the invention, not kmitation of the inventio n In fad, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, featur s illustrated or described as part of one embodiment can be used with another enitoodiment to yield a still further embodiment. Thus, it is intended that the pr sent invention covers such modifications and variations as come within the scope of the appe nded claims and their e cjuivale nts. PO 17] It is to be understood that the ranges and hmits mentioned herein include all range s located within the prescribe d hmits (i. . , subrange s) . For instance , a range from about 100 to about 200 also includes ranges from 110 to 150, 170 to 190, 153 to lo ^~ 2, and 145.3 to 149 & . Further, a limit of up to about 7 also includes a limit of up to about 5, up to 3, and up to about 4.5, as well as ranges within the hmit, such as from about 1 to about 5, and from about 3.2 to about 6.5.

OOISG Che mical elements are discussed in the present disclosure using their common chemical abbreviation, sue has commonly found on a periodic table of elements. For example, hydrogen is represented by its common chemical

abbre^ation H; helium is repre se nted by its c ommon c hemical abbreviation He ; and so forth.

P01 ] Improve d pie cipitation hardened, martensitic stainless steel alloys are generally provided, along with methods of their m nufacture and use. The

precipitation hardened, martensitic stainless steel alloys exhibits improved IG A and pitting corrosion resistance, while retaining high mechanical strength and fracture toughne ss, through control of the alloy constitue nts and the ir relative amounts and an aging heat treatment. The alloys are highly resistant to IGA in known aqueous corrosion e aronments and to corrosion pitting and other generic corrosion mechanisms.

[0020] The se alloys are generally characterised by a uniform martensite microstructure with dispersed l^dening precipitate phases, including fine copper-rich prec ipitate s, ard about 10% by weight or less of reverte d austenite, which in combination with certain chemistry and processing re uirements yields the desired corrosion re sistance, mechanical strength and fracture toughn ss properties for the alloy. In certain embodiments, the alloys exhibit an ultimate tensile strength in the solution and aged c ondition of at least ab out 140 ksi (about 965 MPa), and a Charpy impact toughness of at least about 50 ft-lb (about 69 J and in one embodiment in excess of about 100 ft-lb (about 138 J).

[0021] In summary it has be en discovered that the inc lusion of a carbide forming element which is selected f om the group consisting of titanium, zirconium, tantalum, ard a mixture ther of, within the alloy at a relatively high level in relation to the amount of carbon present makes the alloy increasingly resistant to IGA. That is, the amount of the carbide forming element within the alloy is generally proportion^ to the amount of carbon in the alloy (e.g., greater than about 8 times the amount of carbon). Further, it has been determined that improvements to the IGA resistance by incorporation of the carbide forming element in the amounts relative to C indicated can be done while maintaining a desirable mechanical strength and fracture toughness, inc luding a nunimum ultimate tensile stre ngth and a minimum Charpy V -no tch toughness after solution and age heat treatments of greater than about 965 MPa and about 69 J, respe tively.

[0022] In one e nitoodime nt the forged pre cipitation-hardene d starnle ss stee 1 alloy in ludes, by weight about 14.0% to about 160% chromium, about o\0% to about 8.0% nicket about 1.25% to about 1.75% copper, about 1.0% to about 2.0%

molybdenum, about 0001% to about 0.05% carbon, a carbide forming element in an amount of about 0.3% to about 0.8% and greater than about 8 times that of carbon, the balance iron, and incidental impurities. As stated, the carbide forming element is selected from the group consisting of titanium, zir onium, tantalum, and a mixture thereof. For example, the carbide forming element is, in one embodiment, selected from the group consisting of titanium, zirconium, and tantalum. For example, in one particular embodiment, the forged precipitation- hardened stainless steel alloy consists ssentially of (e.g., consists of), by weight, about 1 40% to about 16.0% chromium, about 6.0% to about S.0% nickel, about 1.25% to about 1 .75% copper, about 1 .0% to about 2.0% molybdenum, about 0.001% to about 0.05% carbon, a carbide forming element in an amount of about 0.3% to about 0 £% and greater than about S times that of carb on, the balance iron, and incide rial impurities .

[0023] Without wishing to be bound by any particular the ory, it is believed that the carbide forming element (e.g., titanium, zirconium, and/ or tantalum) serves to protect chromium in the intergranular region of the alloy by consuming carbon by itse If. Thus, the intergranular re gion has a high c hromium content (i .e ., a chro mium- rich intergranular region) to provide a high corrosion resistance to intergranular corrosion attack and corrosion pitting.

[0024] In one embodiment the carbide forming element is titanium. The forged precipitation-hardened stainless steel alloy, in one particular embodiment comprises about 0.3 % to about 0.7% titanium and in an amount greater than ab out 25 times that of carbon. As such, the forged precipitation-hardened stainless steel alloy can include, by weight, about 14.0% to about 16.0% chromium, about 6.0% to about S.0% nicket about 1 .25% to about 1 .75% copper, about 1 .0% to about 2.0% molybdenum, about 0.001% to about 0.05% carbon, about 0.3% to about 0.7% titanium, the balarce iron, ard incide ntal impurities ; with titanium being pre se nt in an amount gre ate r than ab out 25 times that of carbon. Titanium is a strong carbide forming element stronger than niobium. As such, titanium prote cts c hromium in the intergranular region of the ally by consuming carbon by itse If (ie ., forming titanium carbide), leading to a high chromium c ontent in the intergranular re gion of the alloy to provide a hi h corrosion resistance to intergranular corrosion attack and corrosion pitting.

[10025] In another embodiment the carbide forming element is zirconium. The forged pre cipitation-harde red stainless steel alloy, in one particular embodiment comprises about 0.3% to about 0.7% zirconium and in an amount greater than about S times that of carbo n As sue h, the forge d precipitation-hardened stainle ss stee 1 alloy can include, by weight, about 14.0% to about 16.0% chromium, about 6.0% to about 8.0% nickel, about 1 .25% to about 1.75% copper, about 1.0% to about 2.0% molybdenum, about 0.001% to about 0.05% carbon, about 0.3% to about 0.7% zirconium, the balance iron, and incide tal impurities; with zirconium is present in an amount greater than about 8 times that of carbon. Zirconium is a strong carbide forming ele ment, stro nger than niob ium. As such, zirc onium can protec t chromium in the inter granular r ion of the ally by consuming carbon by itself (i.e., forming zirconium carbide), leading to a high chromium content in the intergranukr region of the alloy to provide a high corrosion resistance to intergranular corrosion attack and corrosion pittin .

[10026] In yet another nitoodiment, the carbide forming element is tantalum. The forged pre cipitauon-harde red stainless steel alloy, in one particular embodiment, comprises about 0.4% to about 0.8% tantalum and in an amount greater than about 1 times that of carbon As such, the forged precipitation-hardened stainless steel alloy can include, by weight about 14.0% to about 16.0% chromium, about 6.0% to about 8.0% nickel, about 1 .25% to about 1.75% copper, about 1.0% to about 2.0% molybdenum, about 0.001% to about 0.05% carbon, about 0.4% to about 0.8% tantalum, the balarc e iron, and incidental im purine s ; with tantalum is pre se nt in an amount greater than about 12 times that of carbon. Tantalum is a strong carbide forming element, stronger than niob ium. As such, tantalum can protect chromium in the intergranular region of the ally by consuming carbon by itself (i.e., forming tantalum cai ide), leading to a high chromium content in the intergranular region of the alloyto provide a high corrosion resistance to intergranular corrosion attack and corrosion pitting .

00027] Inviewof the above, the required constituents of the stainless ste el alloys disclos d herein are chromium, nickel, copper, molybdenum, carbon, and a caibide forming element selected from the group consisting of titanium, zirconium, tantalum, and a mixture thereof These constituents are present in amounts that ensure an essentiallymartensitic, age -hardened nucrostructure having about 10% or less by weight of reverted austenite. As in the Custom 450 stainless steel alloy (described in U.S. Pat. No. 3,574,601), copper is critical for forming the copper-rich pr cipitates required to strengthen the alloy Notably, the alloy compositions disclosed herein employ a very narrow range for carbon content, even more narrow than that disclosed for the Custom 450 alloy.

[TJ028] Carbon is an intentional constituent of the alloys disclosed herein as a key eleme nt for achieving stre ngth by a me chanism of solution strengtheriing in addition to the precipitation str gtheriing mechanism provided by precipitates. However, in comparison to other stainless steels such as Type 422 and Custom 450 (carbon content of 0.10 to 0.20 weight percent), carbon is mam tamed at impurity- type levels. The limite d amount o f carbon present in the alloy is stabilise d with the carbide forming element so as not to form austerdte and carefully limit the formation of reverted austenite to the amounts described herein. The relatively high ratio of carbide forming element to C is necessary to achieve the improvement in intergranular corrosion attac k resistanc e and maintain a de sired level of strength and fracture toughne ss . As disclosed herein, it is belie e d a re latively high conte nt of carbide forming element (relative to carbon) promotes carbide formation of the other major carbides present in the alloy (e.g., chromium carbides, molybdeiiium carbides, etc .), and may also influence the precipitation reaction during aging heat tre tment as the ratios greater than about 8 (carbide forming element to carbon) have a markedly decreased propensity for sensitization to intergranular corrosion attack associated with the aging temperature of these alloys (i.e., sensitization to intergranular corrosion attack is not a function of aging temperature, or effects re late d to aging temperature are greatly reduced) .

\QQ29 At such a ratio, the propensity to sensitization of the alloy is a function of aging temperature. For example, tensile strength and fracture toughness, including a UTS of at least about 965 MPa and a Charpy V -note h toughness o fat le ast about 69 J, that are desirable for turbine compressor airfoils and many other applications, can be obtained by aging at a temperature of about 1000° F. to about 1 100° F.. and more particularly about 1020° F. to about 1070 ° F . (about 549 ° C . to about 576° C.); and eve n more particularly about 1040° F . to about lOoTJ^ F. (about 560° C . to about 571 ⁰ C), but that in addition IGA resistance is enhanced, such that these alloys are virtually immune to IGA regardless of the aging temperature, as described herein. Further, it has been disc overed that a desirable mic ^structural morpho gy, particularly the presence of desirable phases and a desirable phase distribution, is realised, mcluding an e ssentially martensitic nucrostructural morphology, with about 10% or less, by weight of the alloy, of reverted austenite, particularly adjacent to the grain b oundarie s, following aging heat treatments of about 1020° F. to about 1070 ⁰ F . (about 549° C. to about 577° C.) for times in the lange of about 4 to about 6 hours. [Ό030] Chromium provide s the stainless propertie s for the alloys disclose d herein, and for this reason a minimum chromium content of about 14 weight percent is required for these alloys. However, as discussed in U.S. Pat. No. 3,574,601, chromium is a fertile former, and is therefore limited to an amount of about 16 weight perc ent in the alby to avoid delta ferrite . The chromium c ontent of the alby must also be taken into consideratbn with the nickel content to ensure that the alloy is e ssentially martensi tic. As discussed in U.S. Pat. No. 3,574,601 , nickel promotes corrosion resistance and works to balance the martensi tic nticrostructure, but also is an austenite former. The narrow range of about 6.0 to about S.O weight perc ent nickel serves to obtain the desirable effe cts of nickel and avoid austenite .

[D031] Molybdenum in the alby also promote s the corroston re sistance of the alby. In particular, the presence of Mo in amounts, by weight greater than about 1.0% up to about 2fl% significantly increases the resistance of the altoys discbsed herein to pitting corrosion, lather than adversely affecting the resistance by producing increased amounts of delta Mo ferrite as had bee n ievtously believed. Ivbre

particularly, incorporation of about 1 .5 to about 2.0% by weight of MD is particularly advantageous with regard to increasing the resistance of the alloys disclosed herein to pitting corrosion. This advantageous aspect of the altoys disclosed herein maybe used separately to improve the pitting corroston resistance only or it maybe used in combination with the relatively high ratios of the caibide forming element to caibon disclosed herein to increase the resistance of these albys to both intergranularand pitting corrosion.

00032] Use of Ivb contents in the rang es disclose d in the exe mplary e n iodime nts of the alby compositions disclosed herein produce martensitic microstructures that include ferrite in an amount of about 2¾ or less by weight. Forming of a territe phase (including delta ferrite) in the martensi te base microstructure has a detriment to corrosion resistance of the alloys discbsed herein. However, the existence of ferrite, in luding delta ferrite in an amount of about 2% or less by weight, has a minimal effect on the corrosion resistance and nr.echanical properties of these alloys.

[Ό033] The addition of the carbide forming element and Mo in the amounts described herein may have a propensity to promote segregation in these alloys during solidification due to their high melting pints. Su h segregation is g nerally undesirable due to the negative effect of segregation on the phase distributions and alloy nrriciOEtructure, e.g., a reduced propensity to form the desirable martensitic microstructure and an increase d propensity to form fe rrite or auste rdte, or a combination thereof. Therefore, a solution heat treatment is generally employed prior to aging to reduce the propensity for such segregation.

[10034] As stated, incidental impurities may also be present in the tbr ed precipitation-hardened stainless steel alloy. The most common incidental impurities inc ide Mn, Si, V, Ξ n, N, P, Ξ , Al Ag and Pb, ge nerally in c ontrolled amounts of less than about 1% or less by weight of the alloy for any one constituent and less than about 2.32% in any combination. However, the embodiment of the alloy described inayinclude other incidental impurities in amounts which do not materially diminish the alloy properties as described herein, particularly the resistanc to intergranular corrosion attack and corrosion pitting, tensile strength, fiacture toughness and n crostructural morphologies described herein For exampl , the incidental impurities may include, by weight up to about 1.0% Mn, up to about 1 0% Si, up to about 0.1% V, up to about 0.1% Sn, up to about 0.03% N, up to about 0.025% P. up to about 0.005% Ξ, up to about 0.05% Al, up to about 0.005% Ag, and up to about 0.005% Pb. [D035] The use of a very limited amount of nitrogen wilhin the alloy promotes an impact toughness as described herein. More particularly, nitrogen contents above about 0.03 weight percent will have an unacceptable adverse effect on the fiacture toughness of the alloys disclosed herein.

Mangane se and silic on are not require d in the alloy, and vanadium, nitrogen, aluminum, silver, lead, tin, phosphorus and sulfur are all considered to be impurities, and their maximum amounts are to be controlled as described herein. However, both manganese, anaustenite former, and silicon, a ferrite former, maybe pre sent in the alio y and whe n present maybe used se parately or together at levels sufficient to adjust the balance of ferrite and austenite as disclosed herein along with the other alloy constituents that affect the formation and relative amounts of these phases. Silicon also provides segregation control when melting steels, mcluding the stainless steel alloys disclosed herein.

[D037] A final important aspec t of the alloys disclose d herein is the re cjuireme nt for a tempering or aging heat treatment. This heat treatment together with the associated c ooling of the alloy is the precipitation hardening heat treatment and is responsible for the development the distributed fine precipitation phases, including Cu-ri h precipitates, and other aspects of the alloy mi rostructure tliat provide the desirable strength, toughness, corrosion resistance and other properties described herein. This heat treatment maybe performed at a temperature from about 1000° F. to about 1 100° F . (about 538 ° C . to about 593" C for a duration o fat least about 4 hours, and more particularly for a time ranging from about 4 to about o ^" hours. More particularly, an aging temperature in the range from about 1020° F. to about 1070° F. (about 549" C. to about 5Ί6" C.) maybe used. Even more particularly, an aging temperature in the range from about 1040° F. to about 1060° F. (about 560° C. to about 571 C.) maybe used. Otherwise, the stainless steel alloy can be processed by substantially conventional methods. For example, the alloy maybe produced by electric furnace melting with argon oxygen decarburisation (AOD) ladle refinement followed by electro-slag re melting (ESR) of the ingots. Other similar melting practices may also be used.

[Ό038] A suitable forming operation may then be employed to produc e bar stocks ard forgings that have the shape of turbine airfoils. The alloy, mcluding components forme d there fro m, is then solution heat treated in the rang e from about 1 §50° F . to about 1 ^Q 50° F. (about 101 0° C. to about 1066° C.) for about one to about two hours, followed by the age heat treatment described above. The age heat treatment maybe performed at the temperatures and for tie times disclosed herein in ambient or vacuum environments to achieve the desirable mechanical properties and corrosion resistance disclosed herein.

\ΰΰ39 Fig . 1 illustrates an example of a gas turbine 1 0 as may inc orporate the alloy described above in at least one component, particularly in forming turbine airfoil components. As shown, the gas turbine 10 generally includes a compressor section 12. The compressor se ction 12 includes a co mpressor 14 having a plurality of compressor blades 15 and stator vanes 17, with the compressor blades 15 attached to the shaft 24. The compressor includes an inlet 16 that is disposed at an upstream end of the gas turbine 10 . The gas turbine 10 furthe r includes a combustion section 18 having one or more combustors 0 disposed downstream from the compressor section 12. The gas orbine further includes a turbine section 22 that is downstream from the combustion section IS. A shaft 24 extends generally axially through the gas turbine 10. The turbine se ction 22 ge nerally includes alternating stage s of stationary nozzle s 26 ard turbine rotor blades 28 positiore d within the turbine section22 along an axial centerline 30 of the shaft 24. An outer casing 32 circumfeientkUy surrounds the alternating stages of stationary nozzles 26 and the turbine rotor blades 28. An exhaust diffuser 34 is positioned downstream from the turbine section 22.

[D040] Generally, each compressor blade 15 and rotor blade 28 has a leading edge, a trailing edge, a tip and a blade root su h as a dovetailed root that is adapted for detachable attachment to a turbine disk. The span of a blade extends from the tip edge to the blade root. The surface of the blade comprehended within the span constitutes the airfoil surface of the turbine airfoil. The airfoil surface is that portion of the turbine airfoil that is ex sed to the flow path of air from the turbine inlet through the compressor section of the turbine into the combustion chamber and other portions of the turbine. Wlule the alloys disclosed herein are particularly useful for use in turbine airfoils in the form of turbine compressor blades 15 and vanes 17, the alloys are broadlyapphcable to all manner of turbine airfoils used in a wide variety of tuibine engine components. These include turbine airfous assocktedwith ftirbine compressor van s ard nozzles, shrouds, liners and other turbine airfoils, i.e., turbine components having airfoil surfaces such as diaphragm components, seal com nents, valve stems, nozzle boxes, nozzle plate s, or the like . Also, while the se alio ys are use ful for turbine rotor blades, they can potentially also be used for the tuibine omponents of industrial gas turbines, including blades and vanes, steam turbine buckets and other airfoil components, aircraft engine components, oil and gas machinery components, as well as other applications requiring hightensile strength, fracture toughness and resistance to intergranular and pitting corrosion.

00041] In operation, ambie nt air 36 or other working fluid is drawn into the inlet 16 of the compre ssor 14 and is progressively compre ssed to provide a c ompre ssed air 38 to the combustion section IS. The compressed air 38 flows into the combustion section 18 and is mixed with fuel to forma combustible mixture which is burned in a combustion chamber 40 defined within each combustor 20, thereby generating a hot gas 42 that flows from the ombustion chamber 40 into the turbine section 22. The hot gas 42 rapidly expands as it flows through the alternating stages of stationary nozzles 26 and turbine rotor blades 28 of the turbine section 22.

OOO 1] Thermal and/or kinetic ener y is transferre d fro m the hot gas 42 to eac h stage of the turbine rotor blades 28, thereby causing the shaft 24 to rotate and produce mechanical work. The hot gas 42 exits the turbine section 22 and flows through the exhaust diffuser 34 and across a plurality of generally airfoil shap d diffuser struts 44 that are disposed within the exhaust diffuser 34. During various operating conditions of the gas turbine such as during part-load operation, the hot gas 42 flowing into the exhaust diffuser 34 from the turbine section 22 has a high level of swirl that is caused by the rotating turbine rotor blades 28. As a result of the swirling hot gas 42 exiting the turbine section 22, flow separation of the hot gas 42 from the exhaust diffuser struts occurs which compromises the aerodymmic performance of the gas turbine 10, the reby impacting overall engine output and heat rate . As shown in Fig . 1 , the diffuser struts 44 are positione d le lative to a dire ction of flow 60 o f the hot gas 42 flowing from the turbine section 22 of the gas turbine 10.

[10042] It is to be understood that the use of "c omprisin " in conj unction with the alloy compositions described herein sp cifically discloses and includes the

embodiments wherein the alloy compositions "consist essentially o ' the named components (i.e., contain the named components and no other components that significantly adversely affect the basic and novel features disclosed), and

e mbodiments where in the alloy c omposinons "c onsist o ' the name d compo ne rets (i .e ., contain only the named compone ts ex ept for contaminants which are naturally and inevitably present in each of the named components).

[D043] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, inc luding making and using any de vie es or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be uilhin the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.