Abstract: There are provided a high hardness, high corrosion resistance and high wear resistance alloy, wherein the alloy is an aging heat treated Cr(chromium)-Al(aluminum)-Ni(nickel)-base alloy, the proportion of a mixed phase of (? phase+?? phase+? phase) precipitated at grain boundaries of ? phase grains in a metal structure in the cross section of the alloy is not less than 95% in terms of area ratio, and the intensity ratio as measured by X-ray diffractometry of the alloy is not less than 50% and not more than 200% in terms of I?(110)/[I?(200)+I??(004)]×100, and a component comprising this alloy, a material for an alloy which can form this alloy, and a process for producing this alloy. The present invention can provide a Cr—Al—Ni-base alloy possessing excellent corrosion resistance, hardness, wear resistance, releasability, fatigue strength, and planishing property in a molding face, a component comprising this alloy, a material for an alloy which can form this alloy, and a process for producing this alloy.

Abstract: The invention includes a turbine cover bucket of an alloy including carbon at less than approximately 0.04 weight percent, manganese at approximately 0.0-0.2 weight percent, silicon at approximately 0.0-0.25 weight percent, phosphorus at approximately 0.0-0.015 weight percent, sulfur at approximately 0.0-0.015 weight percent, chromium from approximately 20.0-23.0 weight percent, molybdenum from approximately 8.5-9.5 weight percent, niobium from approximately 3.25-4 weight percent, tantalum at approximately 0.0-0.05 weight percent, titanium from approximately 0.2-0.4 weight percent, aluminum from approximately 0.15-0.3 weight percent, iron from approximately 3.0-4.5 weight percent, and the remainder being nickel. The alloy is heat treated at 538° C. to 760° C. for up to 100 hours. A method of manufacturing the turbine bucket cover is also provided.

Abstract: A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and dwell fatigue crack growth behavior. The superalloy contains, by weight, 10.00 to 22.0% cobalt, 10.0 to 14.0% chromium, 4.0 to 6.0% tantalum, 2.0 to 4.0% aluminum, 2.0 to 6.0% titanium, 1.5 to 5.0% tungsten, 1.5 to 5.0% molybdenum, 1.0 to 3.5% niobium, 0.05 to 0.6% hafnium, 0.02 to 0.10% carbon, 0.01 to 0.40% boron, 0.02 to 0.10% zirconium, the balance essentially nickel and impurities, wherein the titanium:aluminum weight ratio is 0.7 to 1.5. The superalloy is hot worked and heat treated to contain cellular gamma prime precipitates that distort grain boundaries, creating tortuous grain boundary fracture paths that are believed to promote the fatigue crack growth resistance of the superalloy.

Abstract: A compositionally graded gas turbine disk is made by preparing a rotationally symmetric radially inner segment of a gas turbine disk preform, rotating the inner segment about a central axis, spray applying a radially outer-segment material onto the radially inner segment as it rotates about the central axis, preferably achieving a gradual transition in composition, and thereafter further processing the gas turbine disk preform to produce the compositionally graded gas turbine disk.

Abstract: Improved compositions are described for the protection of gas turbine parts at elevated temperatures. The compositions are of the MCrAlY type, wherein M is Nickel, or Nickel in combination with cobalt and/or iron. The compositions further comprise a lanthanide, a group 4 metal selected from hafnium, zirconium, titanium, or a combination of these, and optionally, a group 14 element selected from silicon and/or germanium. The combination results in improved Al retention properties. Also disclosed herein are articles comprising the coatings.

Abstract: The corrosion-resistant nickel-base alloy combines thermal stability with corrosion resistance and mechanical strength. The alloy contains balanced proportions of nickel, molybdenum, chromium, and iron with an effective amount of yttrium to stabilize grain boundaries against unwanted reactions, which might degrade corrosion resistance, and an effective amount of boron to maintain an acceptable level of ductility. The alloy may contain minor amounts of additives or impurities, such as silicon, manganese, and aluminum. The alloy may contain between about 25-45% molybdenum, 2-6% chromium, 2-4% iron, 0.01-0.03% boron, 0.005-0.015% yttrium, and up to a maximum of 1% manganese, silicon, and aluminum, respectively, by weight, the balance being nickel. It is preferred that the combined ratio of molybdenum, chromium, and iron to nickel be in the range of about 25% to 45%.

Abstract: In one embodiment, a nickel-base alloy for forging or rolling contains, in weight %, carbon (C): 0.05 to 0.2, silicon (Si) 0.01 to 1, manganese (Mn): 0.01 to 1, cobalt (Co): 5 to 20, iron (Fe): 0.01 to 10, chromium (Cr): 15 to 25, and one kind or two kinds or more of molybdenum (Mo), tungsten (W) and rhenium (Re), with Mo+(W+Re)/2: 8 to 25, the balance being nickel (Ni) and unavoidable impurities.

Abstract: A Ni based cast alloy consisting essentially of C: 0.01 to 0.2% by weight, Si: 0.5 to 4.0% by weight, Cr: 14 to 22% by weight, Mo+W: 4.0 to 10% by weight, B: 0.001 to 0.02% by weight, Co: up to 10% by weight, Al: up to 0.5% by weight, Ti: up to 0.5% by weight, Nb: up to 5.0% by weight, Fe: up to 10% by weight, the balance being Ni and incidental impurities, wherein a ?? phase precipitates in a matrix phase thereof.

Abstract: A component made of an alloy including carbon at less than approximately 0.04 weight percent, manganese at about 0.0 to about 0.2 weight percent, silicon at about 0.0 to about 0.25 weight percent, phosphorus at about 0.0 to about 0.015 weight percent, sulfur at about 0.0 to about 0.015 weight percent, chromium from about 20.0 to about 23.0 weight percent, molybdenum from about 8.5 to about 9.5 weight percent, niobium from about 3.25 to about 4 weight percent, tantalum at about 0.0 to about 0.05 weight percent, titanium from about 0.2 to about 0.4 weight percent, aluminum from about 0.15 to about 0.3 weight percent, iron from about 3.0 to about 4.5 weight percent, and the remainder being nickel. The alloy may then be subjected to heat treatment procedures such as annealing at a temperature of less than approximately 982° C. and a duration of less than approximately one hour and aging at a temperature between approximately 538° C. and 760° C. and a duration of up to approximately 100 hours.

Abstract: A Ni—Fe—Cr—Mo alloy containing a small amount of Cu and correlated percentages of Nb, Ti and Al to develop a unique microstructure to produce 145 ksi minimum yield strength. The unique microstructure is obtained by special annealing and age hardening conditions, by virtue of which the alloy has an attractive combination of yield strength, impact strength, ductility, corrosion resistance, thermal stability and formability, and is especially suited for corrosive oil well applications that contain gaseous mixtures of carbon dioxide and hydrogen sulfide. The alloy comprises in weight percent the following: 0-15% Fe, 18-24% Cr, 3-9% Mo, 0.05 3.0% Cu, 3.6-6.5% Nb, 0.5-2.2% Ti, 0.05-1.0% Al, 0.005-0.040% C, balance Ni plus incidental impurities and a ratio of Nb/(Al+Ti) in the range of 2.5-7.5. To facilitate formability, the composition range of the alloy is balanced to be Laves phase free.

Abstract: Disclosed are a high-strength Ni-base alloy, a method of producing the Ni-base alloy, and a method of recovering a member made of a degraded Ni-base alloy. It contains not more than 0.1 wt % C, not more than 50 wt % Fe, not more than 30 wt % Cr, Ti, and at least one of Nb and Al. It has been strengthened by precipitates of a ?? phase (Ni3Al) and/or a ?? phase (Ni3Nb). It contains also a ? phase (Ni3Ti) which is thermodynamically stable in a temperature range of 800° C. to 900° C. When observed a cross-section of the Ni-base alloy, a plurality of nodes exist along each segment connecting two meeting points each of which point is defined by adjacent three crystal grains, and precipitates of the ?? phase and/or the ?? phase in each of crystal grains of the Ni-base alloy have an average particle size of not more than 100 nm.

Abstract: A method for preventing the formation of cellular gamma prime in nickel-based superalloys comprises the steps of: casting a nickel-based superalloy into a desired article; subjecting the cast article to hot isostatic pressing at a temperature in excess of 2000° F. at a pressure greater than 15,000 psi to close internal pores in the cast article; and avoiding any formation of the cellular gamma prime in the cast article.

Abstract: For a group of nickel-based superalloys, improved properties have been obtained by stabilizing at increased temperature for a reduced time relative to prior art specifications. In particular, improved creep properties have been obtained with a one-hour 1800° F. stabilization relative to a prior art four-hour 1500° F. stabilization.

Abstract: An Fe—Ni-based alloy that has improved wear resistance at high temperature over Ni-based superalloys is provided. The alloy is particularly useful for manufacturing engine exhaust valves and other high temperature engine components subjected to corrosion, wear and oxidation.

Abstract: An alloy comprising 5 at % ?Al<16 at %, about 0.05 at % to 1 at % of a reactive element selected from the group consisting of Hf, Y, La, Ce, Zr, and combinations thereof, and Ni, wherein the alloy composition has a predominately ?-Ni+??-Ni3Al phase constitution.

Abstract: The present invention relates to an anti-galling alloy with finely dispersed precipitates, more particularly to an anti-galling alloy comprising Ni, Cr, Sn, Bi, Mo, Fe, Si and Te, in which the matrix has a fine dendritic structure and the Bi-rich precipitates are finely dispersed between the dendritic structure, so that the anti-galling properties are significantly improved, while physicochemical properties such as corrosion resistance and hardness are not deteriorated. The anti-galling alloy of the present invention will greatly contribute to the improvement in life cycle and mechanical precision of a variety of wet machinery parts such as rotor, shaft, valve and mechanical sealing.

Abstract: Embodiments of the present disclosure relate to nickel-base alloys and methods of direct aging nickel-base alloys. More specifically, certain embodiments of the present disclosure relate to methods of direct aging 718Plus® nickel-base alloy to impart improved mechanical properties, such as, but not limited to, tensile strength, yield strength, low cycle fatigue, fatigue crack growth, and creep and rupture life to the alloys. Other embodiments of the present disclosure relate to direct aged 718Plus® nickel-base alloy, and articles of manufacture made therefrom, having improved mechanical properties, such as, but not limited to, tensile strength, yield strength, low cycle fatigue, fatigue crack growth, and creep and rupture life.

Abstract: A nickel (Ni) based alloy for forging includes: 0.001 to 0.1 wt. % of carbon (C); 12 to 23 wt. % of chromium (Cr); 3.5 to 5.0 wt. % of aluminum (Al); 5 to 12 combined wt. % of tungsten (W) and molybdenum (Mo) in which the Mo content is 5 wt. % or less; a negligible small amount of titanium (Ti), tantalate (Ta) and niobium (Nb); and the balance of Ni and inevitable impurities.

Abstract: A nickel base superalloy consisting of 20 to 40 wt % cobalt, 10 to 15 wt % chromium, 3 to 6 wt % molybdenum, 0 to 5 wt % tungsten, 2.5 to 4 wt % aluminium, 3.4 to 5 wt % titanium, 1.35 to 2.5 wt % tantalum, 0 to 2 wt % niobium, 0.5 to 1 wt % hafnium, 0 to 0.1 wt % zirconium, 0.01 to 0.05 wt % carbon, 0.01 to 0.05 wt % boron, 0 to 2 wt % silicon and the balance nickel plus incidental impurities. The gamma prime phase comprises (Ni/Co)3 (Al/Ti/Ta).

Abstract: Embodiments of the present invention relate to nickel-base alloys, and in particular 718-type nickel-base alloys, having a desired microstructure that is predominantly strengthened by ??-phase precipitates and comprises an amount of at least one grain boundary precipitate. Other embodiments of the present invention relate to methods of heat treating nickel-base alloys, and in particular 718-type nickel-base alloys, to develop a desired microstructure that can impart thermally stable mechanical properties. Articles of manufacture using the nickel-base alloys and methods of heat treating nickel-base alloys according to embodiments of the present invention are also disclosed.

Abstract: A method of forming a component from a gamma prime precipitation-strengthened nickel-base superalloy. The method entails formulating the superalloy to have a sufficiently high carbon content and forging the superalloy at sufficiently high local strain rates so that, following a supersolvus heat treatment, the component is characterized by a fine and substantially uniform grain size distribution, preferably finer than ASTM 7 and more preferably in a range of about ASTM 8 to 10.

Abstract: To provide a rotor material preferable for a steam turbine of which main steam temperature is 675° C. or more, particularly exceeding 700° C., and a steam turbine plant having a rotor formed by the material, the invention provides a steam turbine plant including a very-high-pressure turbine of which steam inlet temperature is 675 to 725° C. and steam outlet temperature is 650° C. or less, a high-pressure turbine, and a medium-low-pressure turbine, wherein a rotor of the very-high-pressure turbine is formed from a forged material of NiFe-base alloy containing: 14 to 18 weight % Cr, 15 to 45 weight % Fe, 1.0 to 2.0 weight % Al, 1.0 to 1.8 weight % Ti, C and N of which the sum is 0.05 or less weight %, and Nb in the range specified by the formula: 3.5?(Fe weight %)/20<(Nb weight %)<4.5?(Fe weight %)/20.

Abstract: A low-density nickel-base superalloy includes the following elements (percent by weight): 7-13% Chromium, 0-16% Cobalt, 2-5% Titanium, 4.5-7% Aluminium, 0-5% Tantalum, 0-2% Hafnium, 0-3% Tungsten, 0-2% Vanadium, 0-5% Molybdenum, 0.06-0.12% Carbon, 0.01-0.03% Boron, 0.005-0.02% Zirconium, nickel and residual impurities use and to the process for obtaining it. The superalloy has advantageous uses and is obtained by processing.

Abstract: A Ni—Fe—Cr alloy having high strength, ductility and corrosion resistance especially for use in deep-drilled, corrosive oil and gas well environments, as well as for marine environments. The alloy comprises in weight %: 35-55% Ni, 12-25% Cr, 0.5-5% Mo, up to 3% Cu, 2.1-4.5% Nb, 0.5-3% Ti, up to 0.7% Al, 0.005-0.04% C, balance Fe plus incidental impurities and deoxidizers. The alloy must also satisfy the ratio of (Nb-7.75 C)/(Al+Ti)=0.5-9 in order to obtain the desired high strength by the formation of ?? and ?? phases. The alloy has a minimum of 1% by weight ?? phase dispersed in its matrix for strength purposes and a total weight percent of ??+?? phases being between 10 and 30.

Abstract: A heat-resistant alloy spring is made of a Ni-based alloy material comprising in weight %: not more than 0.1% C; not more than 1.0% Si; not more than 1.50% Mn; 13.0 to 25.0% Cr; 1.5 to 7.0% Mo; 0.5 to 4.0% Ti; 0.1 to 3.0 % Al; {at least one optional element selected from the group consisting of 0.15 to 2.50% w, 0.001 to 0.020% B, 0.01 to 0.3% Zr, 0.30 to 6.00% Nb, 5.0 to 18.0% Co, and 0.03 to 2.00% Cu}; the balance being essentially Ni; and incidental impurities. The Ni-based alloy material is provided in its crystal structure with gamma prime phase [Ni3(Al, Ti)] or gamma prime phase [Ni3(Al, Ti, Nb)]. The gamma prime phase has an average grain diameter (d) of not less than 25 nanometers, and a hardness-diameter ratio (Hv/d) of a Vickers hardness Hv of a position at a depth of one-fourth of the entire thickness or the wire diameter from a surface of the Ni-based alloy material toward its center and the average grain diameter d(nanometer) is 5 to 25.

Abstract: There are provided a high hardness, high corrosion resistance and high wear resistance alloy, wherein the alloy is an aging heat treated Cr(chromium)-Al(aluminum)-Ni(nickel)-base alloy, the proportion of a mixed phase of (? phase+?? phase+? phase) precipitated at grain boundaries of ? phase grains in a metal structure in the cross section of the alloy is not less than 95% in terms of area ratio, and the intensity ratio as measured by X-ray diffractometry of the alloy is not less than 50% and not more than 200% in terms of I?(110)/[I?(200)+I??(004)]×100, and a component comprising this alloy, a material for an alloy which can form this alloy, and a process for producing this alloy. The present invention can provide a Cr—Al—Ni-base alloy possessing excellent corrosion resistance, hardness, wear resistance, releasability, fatigue strength, and planishing property in a molding face, a component comprising this alloy, a material for an alloy which can form this alloy, and a process for producing this alloy.

Abstract: A fixture and method for repairing superalloy articles. The fixture ideally holds the article in place if repairs are made. An interface between the fixture and the article facilitate transfer of heat between the article and the fixture so that the article can be differentially heat treated. A portion of the article extends from the fixture. This portion of the article, which may be repaired within the fixture or may be repaired elsewhere, is solution heat treated while in the fixture so that the area extending from the fixture is solutioned, while heat is transferred from the article through the fixture, thereby preventing the temperature of the portion of the article within the fixture from being elevated so as to modify its microstructure. The solutioned portion can then be heat treated, while in the fixture, to precipitation harden it as desired.

Abstract: A nickel alloy has 10-20 weight percent of chromium, and 1-4 weight percent of an element selected from the group consisting of aluminum, silicium and both, and can be used in an electrode, for example in an ignition device.

Abstract: A low thermal expansion Ni-base superalloy contains, by weight % (hereinafter the same as long as not particularly defined) C: 0.15% or less; Si: 1% or less; Mn: 1% or less; Cr: 5 to 20%; at least one of Mo, W and Re of Mo+½(W+Re) of 17 (exclusive) to 25%; Al: 0.2 to 2%; Ti: 0.5 to 4.5%; Fe of 10% or less; at least one of B: 0.02% and Zr: 0.2% or less; a remainder of Ni and inevitable impurities; wherein the atomic % of Al+Ti is 2.5 to 7.0.

Abstract: Castable and weldable nickel-base alloys that exhibit a desirable balance of strength and resistance to corrosion and oxidation suitable for gas turbine engine applications. The alloy contains, by weight, about 10% to about 25% cobalt, about 20% to about 28% chromium, about 1% to about 3% tungsten, about 1.6% to about 3.8% aluminum, about 0.4% to about 1.5% titanium, where the sum of aluminum and titanium is about 1.8% to about 5.0%, about 0.5% to about 1.5% columbium, 0.5% to about 1.5% tantalum, about 0.001% to about 0.025% boron, about 0.05% maximum zirconium, about 0.02% to about 0.15% carbon, with the balance essentially nickel and incidental impurities. The alloy may more preferably contain about 2.8% to about 3.8% aluminum where the sum of aluminum and titanium is about 3.0% to about 5.0%, or about 1.6% to about 2.8% aluminum, where the sum of aluminum and titanium is about 1.8% to about 4.3%.

Abstract: A solution treatment is firstly performed for a non-heat-treated Ni based alloy having a composition equivalent to that of Inconel 718 (registered trademark). Subsequently, a primary aging treatment is applied by holding the Ni based alloy at 610 to 660° C. for 5 to 10 hours. After that, a secondary aging treatment is performed by holding the Ni based alloy at 710 to 760° C. for 5 to 10 hours. There are 700 or more precipitates per ?m2, in which each precipitate has a longer diameter of not less than 0.5 nm, in a metal microstructure of the Ni based alloy. Some of the precipitates are large precipitates having average diameters of 25 nm to 1 ?m. There are 10 or more large precipitates per ?m2. A forging die is produced with the Ni based alloy.

Abstract: A protective layer has the composition 0.5 to 2% of rhenium, 15 to 21% of chromium, 9 to 11.5% of aluminum, 0.05 to 0.7% of yttrium and/or at least one equivalent metal from the group consisting of scandium and the rare earths, 0 to 1% of ruthenium, remainder cobalt and/or nickel and production-related impurities, and is scarcely subject to any embrittlement from Cr/Re precipitations.

Abstract: A composition of matter is about 1 to about 3 percent rhenium, from about 6 to about 9 percent aluminum, from 0 to about 0.5 percent titanium, from about 4 to about 6 percent tantalum, from about 12.5 to about 15 percent chromium, from about 3 to about 10 percent cobalt, from about 2 to about 5 percent tungsten, from 0 to about 0.2 percent hafnium, from 0 to about 1 percent silicon, from 0 to about 0.25 percent molybdenum, from 0 to about 0.25 percent niobium, balance nickel and minor elements. The composition is preferably made into a substantially single crystal article, such as a component of a gas turbine engine.

Abstract: A Ni-based alloy hardened with the &ggr;′ phase, which is able to exhibit not only superior strength at high temperatures, but also excellent hot corrosion resistance and oxidation resistance at high temperatures in spite of containing no Re or reducing the amount of Re. The Ni-based superalloy contains, by weight, C:0.01 to 0.5%, B:0.01 to 0.04%, Hf:0.1 to 2.5%, Co:0.8 to 15%, Ta:more than 0% but less than 8.5%, Cr:1.5 to 16%, Mo:more than 0% but less than 1.0%, W:5 to 14%, Ti:0.1 to 4.75%, Al:2.5 to 7%, Nb:more than 0% but less than 4%, V:0 to less than 1.0%, Zr:0 to less than 0.1%, Re:0 to less than 9%, at least one of platinum group elements: 0 to less than 0.5% in total, at least one of rare earth elements: 0 to less than 0.1% in total, and the rest being Ni except for unavoidable impurities.

Abstract: Creep-proof and corrosion-resistant nickel-based alloy for the use in high-temperature technology, comprising in wt-%: 0.0015 to 0.60 carbon (C); 0.20 to 0.90 nitrogen (N); 22.0 to 32.0 chromium (Cr); 5.0 to 20.0 elements of group 4, 5, and 6 of the periodic table, except Cr; 0.03 to 3.0 aluminum (Al); 0.4 to 3.0 silicon (Si); up to 0.15 elements of group 3 of the periodic table, except actinoids; up to 0.60 manganese (Ma); up to 14.8 iron (Fe); up to 0.01 boron (B); a maximum of 0.014 phosphorus (P); a maximum of 0.004 sulfur (S); a minimum of 51 nickel (Ni) or a combination of nickel (Ni) and cobalt (Co); and melting-related impurities.

Abstract: The present inventions offer a nickel-based single crystal alloy which has a high strength, is easy in conducting the solution heat treatment, hardly gives a harmful phase and is resistant to corrosion at high temperature. A nickel-based single crystal alloy is offered where the composition consists of 7-15 of Co, 0.1-4 of Cr, 1-4 of Mo, 4-7 of W, 5.5-6.5 of Al, 5-7 of Ta, 4-5.5 of Re, 0-0.5 each of Hf and V, and 0-2 each of Ti and Nb in terms of % by weight and residual part substantially consists of Ni wherein said alloy may contain unavoidable impurities.

Abstract: A castable and weldable nickel-base alloy that exhibits a desirable balance of strength and resistance to corrosion and oxidation suitable for gas turbine engine applications. A suitable composition for the alloy consists essentially of, by weight, 10% to 25% cobalt, 20% to 28% chromium, 1% to 3% tungsten, 0.5% to 1.5% aluminum, 1.5% to 2.8% titanium, 0.8% to 1.45% columbium, tantalum in an amount less than columbium and Cb+0.508Ta is 1.15% to 1.45%, 0.001% to 0.025% boron, up to 0.4% zirconium, 0.02% to 0.15% carbon, with the balance essentially nickel and incidental impurities.

Abstract: Nickel-based superalloy, suitable for monocrystalline solidification, having the following composition by weight: 1 Co: 4.75 to 5.25% Cr: 11.5 to 12.5% Mo: 0.8 to 1.2% W: 3.75 to 4.25% Al: 3.75 to 4.25% Ti:   4 to 4.8% Ta: 1.75 to 2.25% C: 0.006 to 0.04%  B: ≦0.01% Zr: ≦0.01% Hf: ≦1%   Nb: ≦1%   Ni and any impurities: complement to 100%.

Abstract: A group of alloys suitable for use in a high-temperature, oxidative environment, a protective coating system comprising a diffusion barrier that comprises an alloy selected from the group, an article comprising the diffusion barrier layer, and a method for protecting an article from a high-temperature oxidative environment comprising disposing the diffusion barrier layer onto a substrate are presented.

Abstract: A nickel-based single crystal gas turbine component (30) having a low angle boundary (34) with improved material properties resulting from retained gamma/gamma prime eutectic phase at the low angle boundary. The coarse eutectic phase nodules roughen the grain boundary, reduce the slip distance and disperse concentrated planar slip in the vicinity of the boundary. As a result, the allowable angle of misorientation at the boundary may be increased to greater than 6° for the most highly stressed or critical areas of the component, thereby reducing the amount of scrap material and lowering the cost of manufacturing of a single crystal gas turbine component.

Abstract: A fusion weldable superalloy containing 0.005-0.5 wt. % scandium. In one embodiment, the superalloy may have a composition similar to IN-939 alloy, but having added scandium and having only 0.005-0.040 wt. % zirconium. A gas turbine component may be formed by an investment casting of such a scandium-containing superalloy, and may include a fusion weld repaired area. A scandium-containing nickel-based superalloy coated with an MCrAlY bond coat will have improved cyclic oxidation resistance due to the sulfur-gettering effect of the scandium.

Abstract: A core rod is utilized in the process of forming a core in a metal casting. The core rod has a length and opposite ends The core rod is generally round in cross-section along at least a portion of the length of the core rod proximate at least one of the ends configured for use in forming the core of the metal casting. The core rod is made from a precipitation-hardenable alloy including about 40.0 to 75.0 wt. % Ni, about 0.0 to 25.0 wt. % Co, about 10.0 to 25.0 wt. % Cr, and about 0.0 to 20.0 wt. % Fe. A method for forming a core within a metal casting includes the steps of providing a precipitation-hardenable alloy core rod having a length and opposite ends; packing sand around at least one end of the core rod to form a sand core with core rod; placing the sand core with core rod into a mold; pouring molten metal into the mold and around the sand core with core rod; and producing a metal casting having a core and a uniform sidewall thickness in a range of ±0.060 inches.

Abstract: A nickel-base alloy includes, in weight percent, up to about 0.10 percent carbon; about 12 up to about 20 percent chromium; up to about 4 percent molybdenum; up to about 6 percent tungsten, wherein the sum of molybdenum and tungsten is at least about 2 percent and not more than about 8 percent; about 5 up to about 12 percent cobalt; up to about 14 percent iron; about 4 percent up to about 8 percent niobium; about 0.6 percent up to about 2.6 percent aluminum; about 0.4 percent up to about 1.4 percent titanium; about 0.003 percent up to about 0.03 percent phosphorous; about 0.003 percent up to about 0.015 percent boron; nickel; and incidental impurities. The sum of atomic percent aluminum and atomic percent titanium is from about 2 to about 6 percent, the ratio of atomic percent aluminum to atomic percent titanium is at least about 1.5, and the atomic percent of aluminum plus titanium divided by the atomic percent of niobium equals about 0.8 to about 1.3.

Abstract: A nickel-base superalloy that exhibits outstanding mechanical properties under high temperature and high strain conditions when cast in an equiaxed and/or directionally solidified, columnar grain structure, and which exhibits increased grain boundary strength and ductility while maintaining microstructural stability includes, in percentages by weight, 5-6 chromium, 9-9.5 cobalt, 0.3-0.7 molybdenum, 8-9 tungsten, 5.9-6.3 tantalum, 0.05-0.25 titanium, 5.6-6.0 aluminum, 2.8-3.1 rhenium, 1.1-1.8 hafnium, 0.10-0.12 carbon, 0.010-0.024 boron, 0.011-0.020 zirconium, with the balance being nickel and incidental impurities. The superalloys of this invention are useful for casting gas turbine engine components exhibiting significantly improved low cycle fatigue life, improved airfoil high temperature stress rupture life, significantly reduced life cycle cost, and longer useful life.

Abstract: A nickel-based fine grained alloy consisting essentially of 40-55 wt % Ni, 14.5-21 wt % Cr, 2.5-5.5 wt % Nb+Ta, up to 3.3 wt % Mo, 0.65-2.00 wt % Ti, 0.10-0.8 wt % Al, up to 0.35 wt % Mn, up to 0.07 wt % C, up to 0.015 wt % S, up to 0.35 wt % Si, at least 0.016 wt % P, from 0.003 % to 0.030 wt % B, and the balance Fe and incidental impurities, has a high stress rupture life.

Abstract: A nickel base superalloy suitable for the production of a large, crack-free nickel-base superalloy gas turbine bucket suitable for use in a large land-based utility gas turbine engine, comprising, by weight percents:

Abstract: A single step heat treatment for Ni-Cr-Mo alloys containing from 12% to 19% chromium and from 18% to 23% molybdenum provides higher yield strength, high tensile strength and other mechanical properties comparable to those observed in similar alloys age-hardened according to current practices. This treatment is done over a total time of at least 4 hours and preferably less than 50 hours. However, the treatment works for only those alloys having alloying elements present in amounts according to an equation here disclosed.

Abstract: A two step heat treatment for Ni—Cr—Mo alloys containing from 12% to 23.5% chromium provides higher yield strength, high tensile strength and other mechanical properties comparable to those observed in similar alloys age-hardened according to current practices. This treatment is done over a total time of not more than 50 hours. However, the treatment works for only those alloys having alloying elements present in amounts according to an equation here disclosed.

Abstract: An article, such as a turbine engine component, formed from a nickel-base superalloy, the nickel-base superalloy containing a &ggr;″ tetragonal phase and comprising aluminum, titanium, tantalum, niobium, chromium, molybdenum, and the balance nickel, wherein the article has a time dependent crack propagation resistance of at least about 20 hours to failure at about 1100° F. in the presence of steam. The invention also includes a nickel-base superalloy for forming such and article and methods of forming the article and making the nickel-base superalloy.

Abstract: High molybdenum, corrosion-resistant alloys are provided with greatly increased thermal stability by controlling the atom concentrations to be NiaMobXcYdZe, where: a is between about 73 and 77 atom percent b is between about 18 and 23 atom percent X is one or more required substitutional alloying elements selected from Groups VI, VII and VIII of the Periodic Table and c does not exceed about 5 atom percent for any one element, Y is one or more optional substitutional alloying elements which may be present and d does not exceed about one atom percent for any one element, Z is one or more interstitial elements and e is as low as possible, not exceeding about 0.2 atom percent in total; and the sum of c and d is between about 2.5 and 7.5 atom percent.