Abstract: The present disclosure is directed, in certain embodiments, a component of a mechanical apparatus. The component includes a cast body with an initial structure formed by a mold and at least one feature deposited on the cast body using a solid state additive manufacturing process, such that in combination the initial structure and the at least one feature form a complete structure of the component.

Abstract: A metal composition, a method for additive manufacturing using such metal composition and the use of such metal composition is provided. The components of the metal composition are selected according to ranges and typically provide a more generic applicability in additive manufacturing.

Abstract: A nickel-base alloy welding material according to an embodiment comprises: Cr (chromium) larger than 30.0% and less than or equal to 36.0% by mass; C (carbon) less than or equal to 0.050% by mass; Fe (iron) larger than or equal to 1.00% and less than or equal to 3.00% by mass; Si (silicon) less than or equal to 0.50% by mass; Nb (niobium)+Ta (tantalum) less than or equal to 3.00% by mass; Ti (titanium) less than or equal to 0.70% by mass; Mn (manganese) larger than or equal to 0.10% and less than or equal to 3.50% by mass; Cu (copper) less than or equal to 0.5% by mass, and a remainder is Ni and unavoidable impurities.

Abstract: A method produces semi-finished products from a nickel-based alloy having the composition (in wt. %): Ni>50-<55%, Cr>17-<21%, Nb>4.8-<5.2%, Mo>2.8-<3.3%, Ti>0.8-<1.15%, Al>0.4-<0.6%, C maximum 0.045%, Co maximum 1.0%, Mn maximum 0.35%, Si maximum 0.35%, S maximum 0.01%, Cu maximum 0.3%, the remainder iron and unavoidable impurities. B 0.0001-0.01%, P 0.0001-0.02% are added. In the method: the alloy is melted, or remelted, to produce preliminary products that then undergo a hot-forming process and subsequently undergo a multi-stage annealing and aging treatment, a solution heat treatment being carried out between 1000 and 1100° C. for 1-3 hours, then cooled in air, water or oil, and made to undergo a precipitation hardening process between 650° C.-<770° C. for 5-9 hours, then cooled to room temperature, the intermediate products undergoing, if necessary, at least one further heating process.

Abstract: A nickel-based alloy is disclosed which is suitable for casting gas turbine components having improved strength and comparative lower density while utilizing commercially available heat treatment cycles. The nickel-based alloy is suitable for providing equiaxed, directionally solidified, and single crystal castings. Methods of providing a cast article of the nickel-based alloy and subjecting the article to heat treatment cycles are also disclosed.

Abstract: A local phase transformation strengthened nickel-base superalloy includes at least 8.0 wt % eta phase formers; at least 7.0 wt % of chi phase formers; less than 12 wt % chromium; at least 18 wt % cobalt; and aluminum. A ratio of eta phase formers:aluminum is (3.2-3.4):1. The eta phase formers can include titanium, tantalum, hafnium, and niobium. The chi phase formers include tungsten and molybdenum. When the superalloy is subjected to elevated temperatures, these levels of components promote eta and chi phase formation along superlattice stacking faults, thereby resulting in a local phase transformation at the stacking faults, which strengthens the superalloy and inhibits creep deformation.

Abstract: A nickel-based superalloy comprises in mass percent: 4.0% to 6.0% chromium; 0.4% to 0.8% molybdenum; 2.5% to 3.5% rhenium; 6.2% to 6.6% tungsten; 5.2% to 5.7% aluminum; 0.0 to 1.6% titanium; 6.0% to 9.9% tantalum; 0.0 to 0.7% hafnium; and 0.0 to 0.3% silicon; the balance being constituted by nickel and any impurities. A monocrystalline blade comprises such an alloy and a turbomachine including such a blade.

Abstract: A nickel and chromium alloy having a combined wt. % of nickel and chromium of at least 97 wt. %, wherein the chromium accounts for 33 to 50 wt. % of the alloy. The alloy may be provided in strip form and has adequate ductility for the manufacture of various products, such as sheaths for flux cored welding electrodes. A method of making the alloy strip includes forming a powder charge that is 97 to 100 wt. % of nickel and chromium combined and the chromium accounts for 33 to 50 wt. % of the charge, roll compacting the powder charge to form a green strip, sintering the green strip to form a sintered strip, and cold rolling and annealing the sintered strip to form the alloy strip.

Abstract: A nickel-base superalloy includes essentially, by weight: 14.75 to 26.5 percent cobalt, 4.1 to 4.65 percent aluminium, 1.1 to 1.9 percent titanium, 3.85 to 6.3 percent tantalum, 1.2 to 2.55 percent niobium, up to 0.07 percent boron, up to 0.06 percent carbon, up to 14.0 percent chromium, up to 1.0 percent iron, up to 1.0 percent manganese, up to 4.2 percent molybdenum, up to 0.5 percent silicon, up to 4.9 percent tungsten, and up to 0.1 percent zirconium, the balance being nickel and incidental impurities; wherein the overall concentration in the alloy of aluminium, titanium, tantalum, and niobium is from 13 to 14 atomic percent and the atomic ratio of aluminium to titanium is from 4.625:1 to 6.333:1.

Abstract: A cast nickel-base superalloy that includes iron added substitutionally for nickel. The cast nickel-base superalloy comprises, in weight percent about 1-6% iron, about 7.5-19.1% cobalt, about 7-22.5% chromium, about 1.2-6.2% aluminum, optionally up to about 5% titanium, optionally up to about 6.5% tantalum, optionally up to about 1% Nb, about 2-6% W, optionally up to about 3% Re, optionally up to about 4% Mo, about 0.05-0.18% C, optionally up to about 0.15% Hf, about 0.004-0.015 B, optionally up to about 0.1% Zr, and the balance Ni and incidental impurities. The superalloy is characterized by a ?? solvus temperature that is within 5% of the ?? solvus temperature of the superalloy that does not include 1-6% Fe and a mole fraction of ?? that is within 15% of the mole fraction of the superalloy that does not include 1-6% Fe.

Abstract: Age-hardening nickel-chromium-cobalt-titanium-aluminum wrought alloy with very good wear resistance combined with very good creep strength, good high-temperature corrosion resistance and good processability, the alloy including (in % by mass) >18 to 26% chromium, 1.5 to 3.0% titanium, 0.6 to 2.0% aluminum, 5.0 to 40% cobalt, 0.005 to 0.10% carbon, 0.0005 to 0.050% nitrogen, 0.0005 to 0.030% phosphorus, max. 0.010% sulfur, max. 0.020% oxygen, max. 0.70% silicon, max. 2.0% manganese, max. 0.05% magnesium, max. 0.05% calcium, max. 0.5% molybdenum, max. 0.5% tungsten, max. 0.2% niobium, max. 0.5% copper, max. 0.5% vanadium, optionally 0 to 20% Fe, optionally 0 to 0.20% Zr, optionally 0.0001 to 0.008% boron, optionally 0-0.20% Y, La, Ce, Ce mixed metal, and/or Hf, and/or 0-0.60% Ta, remainder nickel and the conventional process-related impurities are adjusted in contents of max. 0.002% Pb, max. 0.002% Zn, max. 0.

Abstract: A method of welding a component and a treated component are provided. The method comprises an initial heat-treating of the component comprising a substrate. The method further comprises removing a portion of the substrate to form a treatment region comprising an exposed surface. The method further comprises buttering the exposed surface with a first filler additive to form a weld metal adjacent to the fusion line comprising an easy-to-weld alloy. The method further comprises welding the component with the easy-to-weld alloy and a second filler additive. The first filler additive comprises a sufficient amount of each of Co, Cr, Mo, Fe, Al, Ti, Mn, C and Ni to form the easy-to-weld alloy, when welded with the hard-to-weld base alloy.

Abstract: Disclosed are nickel alloys for exhaust system components having improved tensile strength, fatigue strength, oxidation resistance, and abrasion resistance at a high temperature condition. A nickel alloy for exhaust system components according to an embodiment is used for exhaust system components of a vehicle engine, the nickel alloy including: 0.01 to 0.2 wt % of C; 0.1 to 1.0 wt % of Si; 0.1 to 1.5 wt % of Mn; 8 to 24 wt % of Cr; 0.1 to 2.5 wt % of Nb; 0.1 to 4.0 wt % of Al; 0.01 to 1 wt % of Co; 0.01 to 5.0 wt % of Mo; 0.01 to 4 wt % of W; 0.1 to 1 wt % of Ta; 0.1 to 2.4 wt % of Ti; 4.0 to 11.0 wt % of Fe; a remainder being Ni; and inevitable impurities.

Abstract: A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.

Abstract: Welding material for welding of superalloys comprising boron with the range of 0.3-0.8 wt. % B, 0.2-0.8 wt. % C, 17-23 wt. % Cr, 0.35-10 wt. % Mo, 0.1-4.15 wt. % Nb with nickel or iron and impurities to balance for weld repair of engine components manufactured of precipitation hardening superalloys with high content of gamma prime phase at an ambient temperature.

Abstract: The present invention relates to composition comprising a blend of at least one boron source and at least one silicon source, and the composition further comprises particles selected from particles having wear resistance properties, particles having surface enhancing properties, particles having catalytic properties or combinations thereof, wherein the blend comprises boron and silicon in a weight ratio boron to silicon within a range from about 3:100 wt:wt to about 100:3 wt:wt, wherein silicon and boron are present in the blend in at least 25 wt %, and wherein the at least one boron source and the at least one silicon source are oxygen free except for inevitable amounts of contaminating oxygen, and wherein the blend is a mechanical blend of particles in and the particles have an average particle size less than 250 ?m. The present invention relates further to a method for providing a coated product and a coated product obtained by the method.

Abstract: There is provided a Ni-based alloy excellent in hot forgeability, high-temperature oxidation resistance, and high-temperature halogen gas corrosion resistance that is suitable as constituent materials, such as a baking tray for chip capacitor, a baking tray for lithium battery cathode material, a CVD apparatus member, a PVD apparatus member, an LCD apparatus member, and a semiconductor manufacturing apparatus member. The Ni-based alloy contains, by weight, 2.0 to 5.0% Al, 0.1 to 2.5% Si, 0.1 to 1.5% Mn, 0.001 to 0.01% B, 0.001 to 0.1% of Zr, and the balance of Ni with inevitable impurities and excels in hot forgeability, high-temperature oxidation resistance, and high-temperature halogen gas corrosion resistance. The Ni-based alloy may further contain 0.8 to 4.0% Cr.

Abstract: An alumina-forming, high temperature creep resistant alloy is composed essentially of, in terms of weight percent: up to 10 Fe, 3.3 to 4.6 Al, 6 to 22 Cr, 0.68 to 0.74 Mn, 5.2 to 6.6 Mo, 0.4 to 1.2 Ti, up to 0.1 Hf, 0.005 to 0.05 La, 0.4 to 0.6 W, 0.1 to 0.35 C, up to 0.002 B, 0.001 to 0.02 N, balance Ni.

Abstract: An article includes a substrate comprising a precipitate-strengthened alloy and a coating disposed over the substrate. The alloy comprises a) a population of gamma-prime precipitates, the population having a multimodal size distribution with at least one mode corresponding to a size of less than about 100 nanometers; or b) a population of gamma-double-prime precipitates having a median size less than about 300 nanometers. The coating comprises at least two elements, and further comprises a plurality of prior particles. At least a portion of the coating is substantially free of rapid solidification artifacts. Methods for fabricating the article and for processing powder useful for fabricating the article are also provided.

Abstract: A method is disclosed including operations for repairing a component. The method includes providing a component including one of titanium and a titanium alloy, providing a laser deposition device, and providing a shielding means that ensures an oxygen content remains below a first threshold and that a water vapor content remains below a second threshold in a target area of the component. The method further includes depositing a metal material on the component, where the depositing includes operating the deposition device along a tool path including a plurality of tool passes, wherein the tool path further comprises a deposition device velocity specification, a laser power specification, and a specified delay time between each of the plurality of tool passes.

Abstract: A modified electroplated nickel-based metallic alloy coating and method of forming the same is provided. The electroplated coatings exhibit unique microstructure and composition which improves performance over conventional metallic materials. The coatings have significantly higher strength at elevated service temperatures.

Abstract: A Ni-based alloy includes, as a chemical composition, C, Si, Mn, Cr, Mo, Co, Al, Ti, B, P, S, and a balance consisting of Ni and impurities. The average grain size d is 10 ?m to 300 ?m, when the average grain size d is an average grain size in unit of ?m of a ? phase included in a metallographic structure of the Ni-based alloy. Precipitates with a major axis of 100 nm or more are absent in the metallographic structure. An area fraction ? is f2 or more, when the area fraction ? and the f2 are expressed by using the average grain size d and amounts in mass % of each element in the chemical composition.

Abstract: A Ni-based alloy for a welding material including, by mass, 0.001 to 0.1% of C, 18 to 25% of Co, 16 to 20% of Cr, 2.5 to 3.5% of Al, 9.0 to 15.0% of Mo+W, 0.001 to 0.03% of B and the balance being Ni and inevitable impurities.

Abstract: An austenitic alloy tube subjected to a cold working and an annealing heat treatment contains C: 0.01% to 0.15%, Cr: 10.0% to 40.0%, Ni: 8.0% to 80.0%, in mass %, and has a metallographic structure satisfying the following Expressions (i) to (iii). R?f1??(i) R=I220/I111??(ii) f1=0.28×(F1118.0/(F1118.0+0.358.0))??(iii) Where, in the above Expressions, R is a ratio of an integrated intensity of {220} to an integrated intensity of {111} on a surface layer which is measured by a grazing incidence X-ray diffraction method, I220 is the integrated intensity of {220}, I111 is the integrated intensity of {111}, and F111 is full width of half maximum of {111} on the surface layer which is measured by the grazing incidence X-ray diffraction method.

Abstract: In a Ni-base alloy, an area-equivalent diameter D is calculated. D is defined by D=A1/2 from an area A of a largest nitride in a field of view when an observation area S0 is observed. This process is repeated in n fields of view for measurement, where n is the number of the fields of view for measurement, so as to acquire n pieces of data on D, and the pieces are arranged in ascending order D1, D2, . . . , Dn to obtain a reduced variate yj. The obtained values are plotted on X-Y axis coordinates, where an X axis corresponds to D and a Y axis corresponds to yj. In a regression line yj=a×D+b, yj is obtained when a target cross-sectional area S is set to 100 mm2. When the obtained yj is substituted into the regression line, the estimated nitride maximum size is ?25 ?m in diameter.

Abstract: A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight: 16.0 to 30.0% cobalt; 9.5 to 12.5% chromium; 4.0 to 6.0% tantalum; 2.0 to 4.0% aluminum; 2.0 to 3.4% titanium; 3.0 to 6.0% tungsten; 1.0 to 4.0% molybdenum; 1.5 to 3.5% niobium; up to 1.0% hafnium; 0.02 to 0.20% carbon; 0.01 to 0.05% boron; 0.02 to 0.10% zirconium; the balance essentially nickel and impurities. The superalloy has a W+Nb?Cr value of at least ?6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours.

Abstract: The Ni based forged alloy has a composition containing, on the basis of mass percent, Al: 0.5 to 1.0%, Cr: 17 to 21%, Fe: 17 to 19%, Nb: 4.5 to 5.5%, Ti: 0.8 to 1.3%, W: 3.0 to 6.0%, B: 0.001 to 0.03%, C: 0.001 to 0.015%, and Mo: 1.0% or less, the balance being Ni and inevitable impurities. The alloy includes carbide grains of the contained elements. The carbide grains have an average grain diameter of 20 ?m or less. Thus, a Ni based forged alloy is provided which is excellent in high-temperature fatigue property and has a moderate macrosegregation property.

Abstract: A Ni-based heat resistant alloy as pipe, plate, rod, forgings and the like consists of C?0.15%, Si?2%, Mn?3%, P?0.03%, S?0.01%, Cr: 15% or more and less than 28%, Mo: 3 to 15%, Co: more than 5% and not more than 25%, Al: 0.2 to 2%, Ti: 0.2% to 3%, Nd: fn to 0.08%, and O?0.4Nd, further containing, as necessary, at least one kind of Nb, W, B, Zr, Hf, Mg, Ca, Y, La, Ce, Ta, Re and Fe of specific amounts, the balance being Ni and impurities, wherein, fn=1.7×10?5d+0.05{(Al/26.98)+(Ti/47.88)+(Nb/92.91)}. In the formula, d denotes an average grain size (?m), and each element symbol denotes the content (mass %) of that element. If the alloy contains W, Mo+(W/2)?15% holds. The alloy has improved ductility after long-term use at high temperatures, and cracking due to welding can be avoided.

Abstract: A heat resistant super alloy suffices the following conditions: carbon 0.01-0.2 percent in weight chromium 8-10 percent in weight aluminum 4-6 percent in weight titanium 2-4 percent in weight molybdenum 1.5-2.8 percent in weight tungsten 10-13.5 percent in weight niobium 1.5-2.5 percent in weight boron 0 < B ? 0.04 percent in weight zircon 0 < Zr ? 0.15 percent in weight the contents of hafnium and lanthanum together amounts to 0 < Hf + La ? 1.5 percent in weight, optionally traces of tantalum, the remainder being nickel. Such an alloy is preferably used for turbine wheels and particularly for turbochargers.

Abstract: A high strength, corrosion resistant alloy suitable for use in oil and gas environments includes, in weight %: 0-12% Fe, 18-24% Cr, 3-6.2% Mo, 0.05-3.0% Cu, 4.0-6.5% Nb, 1.1-2.2% Ti, 0.05-0.4% 0.05-0.2% Al, 0.005-0.040% C, balance Ni plus incidental impurities and deoxidizers. A ratio of Nb/(Ti+Al) is equal to 2.5-7.5 to provide a desired volume fraction of ?? and ?? phases. The alloy has a minimum yield strength of 145 ksi.

Abstract: A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight, 16.0 to 30.0% cobalt, 11.5 to 15.0% chromium, 4.0 to 6.0% tantalum, 2.0 to 4.0% aluminum, 1.5 to 6.0% titanium, up to 5.0% tungsten, 1.0 to 7.0% molybdenum, up to 3.5% niobium, up to 1.0% hafnium, 0.02 to 0.20% carbon, 0.01 to 0.05% boron, 0.02 to 0.10% zirconium, the balance essentially nickel and impurities, wherein the titanium:aluminum weight ratio is 0.5 to 2.0.

Abstract: A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight, 18.0 to 30.0% cobalt, 11.4 to 16.0% chromium, up to 6.0% tantalum, 2.5 to 3.5% aluminum, 2.5 to 4.0% titanium, 5.5 to 7.5% molybdenum, up to 2.0% niobium, up to 2.0% hafnium, 0.04 to 0.20% carbon, 0.01 to 0.05% boron, 0.03 to 0.09% zirconium, the balance essentially nickel and impurities, wherein the titanium:aluminum weight ratio is 0.71 to 1.60.

Abstract: The object of the present invention is to provide an Ni-based single crystal super alloy capable of improving strength by preventing precipitation of a TCP phase at high temperatures. This object is achieved by an Ni-based single crystal super alloy having a composition comprising 5.0-7.0 wt % of Al, 4.0-10.0 wt % of Ta, 1.1-4.5 wt % of Mo, 4.0-10.0 wt % of W, 3.1-8.0 wt % of Re, 0-0.50 wt % of Hf, 2.0-5.0 wt % of Cr, 0-9.9 wt % of Co and 4.1-14.0 wt % of Ru in terms of its weight ratio, with the remainder consisting of Ni and unavoidable impurities. Furthermore, in this Ni-based single crystal super alloy, when lattice constant of matrix is taken to be a1 and lattice constant of precipitation phase is taken to be a2, a2?0.999a1.

Abstract: A protective coating system includes a nickel-aluminum-zirconium alloy coating having beta phase nickel-aluminum and at least one phase selected from gamma phase nickel and the gamma prime phase nickel-aluminum. The nickel-aluminum-zirconium alloy coating comprises 10 vol % to 60 vol % of the beta phase nickel-aluminum or 25 vol % to 75 vol % of the beta phase nickel-aluminum.

Abstract: Disclosed herein is a nickel-based heat-resistant superalloy produced by a casting and forging method, the nickel-based heat-resistant superalloy comprising 2.0 mass % or more but 25 mass % or less of chromium, 0.2 mass % or more but 7.0 mass % or less of aluminum, 19.5 mass % or more but 55.0 mass % or less of cobalt, [0.17×(mass % of cobalt content?23)+3] mass % or more but [0.17×(mass % of cobalt content?20)+7] mass % or less and 5.1 mass % or more of titanium, and the balance being nickel and inevitable impurities, and being subjected to solution heat treatment at 93% or more but less than 100% of a ?? solvus temperature.

Abstract: Low rhenium nickel base superalloy compositions and articles formed from the superalloy composition are provided. The nickel base superalloy composition includes in percentages by weight: about 5-8 Cr; about 6.5-9 Co; about 1.3-2.5 Mo; about 4.8-6.8 W; about 6.0-7.0 Ta; if present, up to about 0.5 Ti; about 6.0-6.4 Al; about 1-2.3 Re; if present, up to about 0.6 Hf; if present, up to 1.5 C; if present, up to about 0.015 B; the balance being nickel and incidental impurities. Exemplary compositions are characterized by an Re ratio defined as the weight % of Re relative to the total of the weight % of W and the wt % of Mo, of less than about 0.3. Exemplary articles include airfoils for gas turbine engine blades or vanes, nozzles, shrouds, and splash plates.

Abstract: It is an objective of the invention to provide a Ni-based forged alloy having good large ingot formability and good hot formability as well as high mechanical strength at high temperature. There is provided a Ni-based forged alloy comprising: 0.001 to 0.1 mass % of C; 0.001 to 0.01 mass % of B; 16 to 22 mass % of Cr; 0.5 to 1.5 mass % of Al; 0.1 to 6.0 mass % of W; 3.5 to 5.5 mass % of Nb; 0.8 to 3.0 mass % of Ti; 16 to 20 mass % of Fe; 2.0 mass % or less of Mo; and the balance including Ni and unavoidable impurities, in which: a segregation parameter Ps defined by a formula of “Ps (mass %) =1.05×[Al concentration (mass %)]+0.6×[Ti concentration (mass %)]?0.8×[Nb concentration (mass %)]?0.3×[Mo concentration (mass %)]” satisfies a relationship of “Ps??3.0 mass %”; and a total amount of W and Mo is 1.75 atomic % or less.

Abstract: Provided is an Ni-base alloy excellent in strength, ductility and other properties through the resolution of micro-segregation. Also provided is a process for manufacturing an Ni-base alloy containing by mass C:0.15% or less, Si:1% or less, Mn:1% or less, Cr:10 to 24%, Mo+(1/2)W (where Mo may be contained either alone or as an essential component):5 to 17%, Al:0.5 to 1.8%, Ti:1 to 2.5%, Mg:0.02% or less, and either B:0.02% or less and/or Zr:0.2% or less at an Al/(Al+0.56Ti) ratio of 0.45 to 0.70 with the balance consisting of Ni and impurities, which comprises subjecting, at least one time, an Ni-base alloy material which is prepared by vacuum melting and has the above composition to homogenization heat treatment at 1160 to 1220° C. for 1 to 100 hours. The Mo segregation ratio of the alloy is controlled to 1 to 1.17 by the homogenization heat treatment.

Abstract: The invention relates to a nickel alloy derived from René 125, but with reduced levels of certain elements (Zr, B, P, S, Si and, to a lesser extent, Ti and Hf) in order to limit the appearance of cracks upon solidification in a moulding process. Specifically, 4.80%?Al?5.00%, 1.48%?Hf?1.52%, 2.28%?Ti?2.33%, 0.005%?B?0.01%, 1.77%?Mo?1.97%, and Zr?0.007%. Other elements can have levels that match those of René 125.

Abstract: An austenitic heat resistant alloy includes, by mass percent, C: 0.15% or less, Si: 2% or less, Mn: 3% or less, Ni: 40 to 60%, Co: 10.14 to 25%, Cr: 15% or more and less than 28%, either one or both of Mo: 12% or less and W: less than 0.05%, the total content thereof being 0.1 to 12%, Nd: 0.001 to 0.1%, B: 0.0005 to 0.006%, N: 0.03% or less, O: 0.03% or less, at least one selected from Al: 1.36% or less, Ti: 3% or less, and Nb: 3% or less, and the balance being Fe and impurities. The contents of P and S in the impurities are P: 0.03% or less and S: 0.01% or less. The alloy satisfies 1?4×Al+2×Ti+Nb?12 and P+0.2×Cr×B?0.035, where an element in the Formulas represents the content by mass percent.

Abstract: [Problem to be Solved] A Ni-based alloy product consisting of, by mass percent, C: 0.03 to 0.10%, Si: 0.05 to 1.0%, Mn: 0.1 to 1.5%, Sol.Al: 0.0005 to 0.04%, Fe: 20 to 30%, Cr: not less than 21.0% and less than 25.0%, W: exceeding 6.0% and not more than 9.0%, Ti: 0.05 to 0.2%, Nb: 0.05 to 0.35%, and B: 0.0005 to 0.006%, the balance being Ni and impurities, the impurities being P: 0.03% or less, S: 0.01% or less, N: less than 0.010%, Mo: less than 0.5%, and Co: 0.8% or less, wherein a value of effective B (Beff) defined by the formula, Beff (%)=B?(11/14)×N+(11/48)×Ti, is 0.0050 to 0.0300%, and the rupture elongation in a tensile test at 700° C. and at a strain rate of 10?6/sec is 20% or more. This alloy may contain one or more kinds of Cu, Ta, Zr, Mg, Ca, REM, and Pd.

Abstract: A radiopaque alloy based on titanium nickelide and having shape memory and superelastic properties includes, according to one embodiment, at least one radiopaque alloying element selected from among gold, platinum, and palladium at a concentration of from about 10 at. % to about 20 at. %, and at least one additional alloying element selected from among aluminum, chromium, cobalt, iron, and zirconium, where the additional alloying element has a concentration of from about 0.5 at. % to about 4 at. %. The alloy includes titanium at a concentration of from about 48 at. % to about 52 at. %, and the balance of the alloy is nickel. The radiopaque alloy preferably exhibits superelastic behavior suitable for medical device applications in the human body.

Abstract: A method of forging includes a first forging action that changes the shape of a metallic alloy work piece. A second forging action further changes the shape of the metallic alloy work piece after the first forging action. A heat treatment step is conducted after the first forging action and prior to the second forging action. The heat treatment step includes subjecting the metallic alloy work piece to a heat treatment temperature that alters the microstructure of the metallic alloy work piece without the application of a forging action that changes the shape of the metallic alloy work piece.

Abstract: A Ni-based single crystal superalloy according to the invention has, for example, a composition including: 5.0 to 7.0 wt % of Al, 4.0 to 10.0 wt % of Ta, 1.1 to 4.5 wt % of Mo, 4.0 to 10.0 wt % of W, 3.1 to 8.0 wt % of Re, 0.0 to 2.0 wt % of Hf, 2.5 to 8.5 wt % of Cr, 0.0 to 9.9 wt % of Co, 0.0 to 4.0 wt % of Nb, and 1.0 to 14.0 wt % of Ru in terms of weight ratio; and the remainder including Ni and incidental impurities. In addition, the contents of Cr, Hf and Al are preferably set so as to satisfy the equation OP?108. According to the Ni-based single crystal superalloy of the invention, high creep strength can be maintained and the oxidation resistance can be improved.

Abstract: Provided is a pot-shaped copper sputtering target manufactured with die forging, wherein the Vickers hardness Hv at all locations of the inner surface of the pot-shaped target is 70 or greater. With this pot-shaped copper sputtering target, the average crystal grain size in the target structure is 65 ?m or less. Further, the inner surface of the pot-shaped target comprises crystalline orientations of (220), (111), (200), (311) obtained by X-ray diffraction, and the crystalline orientation of the face subject to erosion of the pot-shaped target is of a (220) primary orientation. An object of the present invention is to obtain a manufacturing method of a high quality sputtering target by improving and devising the forging process and heat treatment process to make the crystal grain size refined and uniform, and to obtain a high-quality sputtering target.

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 method for heat treating a nickel base alloy includes the steps of: a. heating a nickel base alloy to at least its delta (?) phase solvus temperature, and lower than its incipient melting temperature for a predetermined time sufficient to dissolve substantially all of the nickel base alloy's delta (?) phase, and b. cooling the nickel base alloy to a temperature below the gamma prime (?) precipitation temperature at a rate sufficient to precipitate the alloy's chromium carbide and gamma prime (?) in a serrated grain boundary.

Abstract: A Co-based alloy containing not less than 0.001 mass % and less than 0.100 mass % of C, not less than 9.0 mass % and less than 20.0 mass % of Cr, not less than 2.0 mass % and less than 5.0 mass % of Al, not less than 13.0 mass % and less than 20.0 mass % of W, and not less than 39.0 mass % and less than 55.0 mass % of Ni, with the remainder being made up by Co and unavoidable impurities, wherein the contents of Mo, Nb, Ti and Ta which are included in the unavoidable impurities are as follows: Mo<0.010 mass %, Nb<0.010 mass %, Ti<0.010 mass %, and Ta<0.010 mass %.

Abstract: The present invention relates to a low thermal expansion Ni-base superalloy containing, in terms of mass %, C: 0.15% or less; Si: 1% or less; Mn: 1% or less; Cr: 5% or more but less than 20%; at least one of Mo, W and Re, in which Mo+½(W+Re) is 5% or more but less than 20%; W: 10% or less; Al: 0.1 to 2.5%; Ti: 0.10 to 0.95%; Nb+½Ta: 1.5% or less; B: 0.001 to 0.02%; Zr: 0.001 to 0.2%; Fe: 4.0% or less; and a balance of inevitable impurities and Ni, in which the total amount of Al, Ti, Nb and Ta is 2.0 to 6.5% in terms of atomic %. The low thermal expansion Ni-base superalloy of the present invention has a thermal expansion coefficient almost equal to that of 12 Cr ferritic steel, excellent high temperature strength, excellent corrosion and oxidation resistance, good hot-workability, and excellent weldability.

Abstract: A heat treatment method for desensitizing a nickel-based alloy with respect to environmentally-assisted cracking, the alloy having the following composition in percentages by weight: C?0.10%; Mn?0.5%; Si?0.5%; P?0.015%; S?0.015%; Ni?40%; Cr=12%-40%; Co?10%; Al?5%; Mo=0.1%-15%; Ti?5%; B?0.01%; Cu?5%; W=0.1%-15%; Nb=0-10%; Ta?10%; the balance being Fe, and inevitable impurities that result from processing, characterized in that the alloy is held at 950° C.-1160° C. in an atmosphere of pure hydrogen or containing at least 100 ppm of hydrogen mixed with an inert gas. A part made of a nickel-based alloy having the composition and that has been subjected to the heat treatment.