Abstract: A nickel-chromium-cobalt-molybdenum alloy includes (in weight %) Cr 21-23%, Fe 0.05-1.5%, C 0.05-0.08%, Mn?0.5%, Si?0.25%, Co 11-13%, Cu?0.15%, Mo 8.0-10.0%, Ti 0.3-0.5%, Al 0.8-1.3%, P<0.012%, S<0.008%, B>0.002-<0.006%, Nb>0-1%, N?0.015%, Mg?0.025%, Ca?0.01%, V 0.005-0.6%, optionally W in contents between 0.02-max. 2%, Ni rest as well as smelting-related impurities, in the form of tubes, sheets, wire, bars, strips or forgings, wherein the alloy satisfies the following formula: X3=5?50, wherein X ? ? 3 = 100 * X ? ? 1 X ? ? 2 and X1=C+5N and X2=0.5Ti+Nb+0.5 V.

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: 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: 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: Known protective layers having a high Cr content and additionally a silicon form brittle phases which additionally become brittle under the influence of carbon during use. The protective layer hereof has a composition 22% to 24% cobalt (Co), 10.5% to 11.5% aluminum (AI), 0.2% to 0.4% yttrium (Y) and/or at least one equivalent metal from the group comprising scandium and the rare earth elements, 14% to 16% chrome (Cr), optionally 0.3% to 0.9% tantalum, the remainder nickel (Ni).

Abstract: Known protective layers having a high Cr-content and a silicone in addition, form brittle phases that embrittle further under the influence of carbon during use. The protective layer according to the invention is composed of 22% to 26% cobalt (Co), 10.5% to 12% aluminum (Al), 0.2% to 0.4% Yttrium (Y) and/or at least one equivalent metal from the group comprising Scandium and the rare earth elements, 15% to 16% chrome (Cr), optionally 0.3% to 1.5% tantal, the remainder nickel (Ni).

Abstract: The invention relates to a novel alloy which comprises the elements carbon (C), chromium (Cr), cobalt (Co), molybdenum (Mo), tungsten (W), titanium (Ti), aluminium (Al), boron (B), and zirconium (Zr), based on nickel, and which has a very low tendency to form cracks during welding.

Abstract: Disclosed is a novel heat-resistant superalloy for turbine disks having a chemical composition consisting of, in mass %, 19.5-55% of cobalt, 2-25% of chromium, 0.2-7% of aluminum, 3-15% of titanium and the balance of nickel and inevitable impurities.

Abstract: A metallic coating or alloy is provided. The metallic coating includes iron, cobalt, chromium, and aluminum. Tantalum may also be included. A new addition in nickel based coating with stabilized gamma/gamma? phases at high temperatures lead to a reduction of local stresses. A component including the metallic coating or alloy is also provided.

Abstract: A coating and process for depositing the coating on a substrate. The coating is a nickel aluminide overlay coating of predominantly the beta (NiAl) and gamma-prime (Ni3Al) intermetallic phases, and is suitable for use as an environmental coating and as a bond coat for a thermal barrier coating (TBC). The coating can be formed by depositing nickel and aluminum in appropriate amounts to yield the desired beta+gamma prime phase content. Alternatively, nickel and aluminum can be deposited so that the aluminum content of the coating exceeds the appropriate amount to yield the desired beta+gamma prime phase content, after which the coating is heat treated to diffuse the excess aluminum from the coating into the substrate to yield the desired beta+gamma prime phase content.

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)].

Abstract: Disclosed is a low-thermal-expansion Ni-based super-heat-resistant alloy for a boiler, which has excellent high-temperature strength. The alloy can be welded without the need of carrying out any aging treatment. The alloy has a Vickers hardness value of 240 or less. The alloy comprises (by mass) C in an amount of 0.2% or less, Si in an amount of 0.5% or less, Mn in an amount of 0.5% or less, Cr in an amount of 10 to 24%, one or both of Mo and W in such an amount satisfying the following formula: Mo+0.5 W=5 to 17%, Al in an amount of 0.5 to 2.0%, Ti in an amount of 1.0 to 3.0%, Fe in an amount of 10% or less, and one or both of B and Zr in an amount of 0.02% or less (excluding 0%) for B and in an amount of 0.2% or less (excluding 0%) for Zr, with the remainder being 48 to 78% of Ni and unavoidable impurities.

Abstract: An object of the present invention is to provide a Ni base alloy solid wire for welding, which has excellent cracking resistance to ductility dip cracking in weld metal, can increase the tensile strength of the weld metal to not less than the tensile strength of the base material, and has excellent weldability. The present invention provides a solid wire which has a composition containing Cr: 27.0 to 31.5 mass %, Ti: 0.50 to 0.90 mass %, Nb: 0.40 to 0.70 mass %, Ta: 0.10 to 0.30 mass %, C: 0.010 to 0.030 mass %, and Fe: 5.0 to 11.0 mass %, and is regulated to Al: 0.10 mass % or less, N: 0.020 mass % or less, Zr 0.005 mass % or less, P:0.010 mass % or less, S: 0.0050 mass % or less, Si: 0.50 mass % or less, and Mn: 1.00 mass % or less, with the balance including Ni and inevitable impurities.

Abstract: An Ni-based alloy for casting used for a steam turbine of an embodiment contains in percent (%) by mass C (carbon): 0.01 to 0.1, Cr (chromium): 15 to 25, Co (cobalt): 10 to 15, Mo (molybdenum): 5 to 12, Al (aluminum): 0.5 to 2, Ti (titanium): 0.3 to 2, B (boron): 0.001 to 0.006, Ta (tantalum): 0.05 to 1, Si (silicon): 0.1 to 0.5, Mn (manganese): 0.1 to 0.5, and the balance of Ni (nickel) and unavoidable impurities.

Abstract: A thermo-mechanical treatment process is disclosed. A nickel-base alloy workpiece is heated in a first heating step to a temperature greater than the M23C6 carbide solvus temperature of the nickel-base alloy. The nickel-base alloy workpiece is worked in a first working step to a reduction in area of 20% to 70%. The nickel-base alloy workpiece is at a temperature greater than the M23C6 carbide solvus temperature when the first working step begins. The nickel-base alloy workpiece is heated in a second working step to a temperature greater than 1700° F. (926° C.) and less than the M23C6 carbide solvus temperature of the nickel-base alloy. The nickel-base alloy workpiece is not permitted to cool to ambient temperature between completion of the first working step and the beginning of the second heating step. The nickel-base alloy workpiece is worked to a second reduction in area of 20% to 70%. The nickel-base alloy workpiece is at a temperature greater than 1700° F. (926° C.

Abstract: The invention is a class of nickel-base alloys for gas turbine applications, comprising, by weight, about 13.7 to about 14.3 percent chromium, about 5.0 to about 10.0 percent cobalt, about 3.5 to about 5.2 percent tungsten, about 2.8 to about 5.2 percent titanium, about 2.8 to about 4.6 percent aluminum, about 0.0 to about 3.5 percent tantalum, about 1.0 to about 1.7 percent molybdenum, about 0.08 to about 0.13 percent carbon, about 0.005 to about 0.02 percent boron, about 0.0 to about 1.5 percent niobium, about 0.0 to about 2.5 percent hafnium, about 0.0 to about 0.04 percent zirconium, and the balance substantially nickel. The nickel-base alloys may be provided in the form of useful articles of manufacture, and which possess a unique combination of mechanical properties, microstructural stability, resistance to localized pitting and hot corrosion in high temperature corrosive environments, and high yields during the initial forming process as well as post-forming manufacturing and repair processes.

Abstract: A Ni-based heat resistant alloy for a gas turbine combustor, comprising a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.001 to 0.020%, C: 0.03 to 0.15%, and a balance consisting of Ni and unavoidable impurities, wherein a content of S and P contained in the unavoidable impurities is controlled to be, in mass %, S: 0.015% or less, and P: 0.015% or less, wherein the alloy has a texture in which M6C type carbide and MC type carbide are uniformly dispersed in ? phase matrix.

Abstract: A nickel, chromium, iron alloy and method for use in producing weld deposits and weldments formed therefrom. The alloy comprises, in weight percent, about 28.5 to 31.0% chromium; about 0 to 16% iron; less than about 1.0% manganese; about 2.1 to 4.0% niobium plus tantalum; 1.0 to 6.5% molybdenum; less than 0.50% silicon; 0.01 to 0.35% titanium; 0 to 0.25% aluminum; less than 1.0% copper; less than 1.0% tungsten; less than 0.5% cobalt; less than about 0.10% zirconium; less than about 0.01% sulfur; less than 0.01% boron; less than 0.03% carbon; less than about 0.02% phosphorous; 0.002 to 0.015% magnesium plus calcium; and balance nickel and incidental impurities. The method includes the steps of forming a welding electrode from the above alloy composition and melting the electrode to form a weld deposit. A preferred weldment may be in the form of a tubesheet of a nuclear reactor.

Abstract: A wire for welding Ni-based heat resistant alloy, comprising: a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.0001 to 0.020%, C: 0.03 to 0.15%, and a balance of Ni and unavoidable impurities, wherein a content of S and P contained in the unavoidable impurities is controlled to be, in mass %, S: 0.004% or less, and P: 0.010% or less, wherein the wire has a texture in which M6C type carbide and MC type carbide are uniformly dispersed in the matrix.

Abstract: A method for producing a low thermal expansion Ni-base superalloy including the steps of subjecting the alloy to a solution heat treatment under the condition of at a temperature of 1000 to 1200° C. and subjecting the alloy to either a carbide stabilizing treatment for making aggregated carbides on grain boundaries and stabilizing the carbides under the conditions of at a temperature of not less than 850° C. and less than 1000° C. and for 1 to 50 hours, or a carbide stabilizing treatment for making aggregated carbides on grain boundaries and stabilizing the carbides by cooling from the temperature in the solution heat treatment to 850° C. at a cooling rate of 100° C. or less per hour. The method also including the steps of subjecting the alloy to a first aging treatment for precipitating y? phase under the conditions of at a temperature of 720 to 900° C.

Abstract: A welding additive is provided. A component including a welding additive is also provided. The welding additive improves the weldability of a few nickel-based superalloys and includes the following contents (in wt %): 10.0%-20.0% chromium, 5.0%-15.0% cobalt, 0.0%-10.0% molybdenum, 0.5-3.5% tantalum, 0.0%-5.0% titanium, 1.5%-5.0% aluminum, 0.3%-0.6% boron, remainder nickel.

Abstract: Disclosed is a novel heat-resistant superalloy for turbine disks having a chemical composition consisting of, in mass %, 19.5-55% of cobalt, 2-25% of chromium, 0.2-7% of aluminum, 3-15% of titanium and the balance of nickel and inevitable impurities.

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+(½)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: Disclosed is a welding material for a Ni-based alloy, comprising components expressed as follows: C?0.05 mass %; 8 mass %?Cr?25 mass %; Fe?4.0 mass %; W?15 mass %; 5 mass %?Mo+½(W+Re)?20 mass %; Co?20 mass %; 0.01 mass %?Al<2.0 mass %; 0.01 mass %?Ti<2.0 mass %; Al+½Ti?3.0 mass %; Nb+½Ta?1.5 mass %; B?0.007 mass %; Zr?0.04 mass %; 0.01 mass %?Si?0.5 mass %; Mn?1.0 mass %; P?0.010 mass %; S?0.002 mass %; O?0.005 mass %; and Ni and unavoidable impurities which constitute the balance.

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: Gamma prime nickel-base superalloy and components formed therefrom. The alloy contains, by weight, 11.3 to 13.3% cobalt, 12.4 to 15.2% chromium, 2.1 to 2.7% aluminum, 3.6 to 5.8% titanium, 3.5 to 4.5% tungsten, 3.1 to 3.8% molybdenum, 0.0 to 1.2% niobium, 0.0 to 2.3% tantalum, 0.0 to 0.5% hafnium, 0.040 to 0.100% carbon, 0.010 to 0.046% boron, 0.030 to 0.080% zirconium, the balance nickel and impurities, wherein the Nb+Ta content is 0.0-3.5%.

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 invention provides a Ni—Fe-based alloy which is preferable for a welding of a joint between different materials such as a steel material and a Ni-based alloy, and a rotor for a steam turbine which is manufactured by using the same. The invention employs a Ni—Fe-based alloy comprising Cr: 14 to 18%, Al: 1.0 to 2.5%, Mo+W: 2.5 to 5.0%, C: 0.01 to 0.10%, B: 0.001 to 0.03%, and Fe: 15 to 20%, in mass, in which the remaining portion is constructed by an unavoidable impurity and Ni, as a welding metal. As a result, it is possible to provide a rotor for a steam turbine which can hold down a reduction of a ductility and a toughness generated in the case of welding the different materials, and is excellent in a strength and the ductility.

Abstract: Disclosed is a low-thermal-expansion Ni-based super-heat-resistant alloy for a boiler, which has excellent high-temperature strength. The alloy can be welded without the need of carrying out any aging treatment. The alloy has a Vickers hardness value of 240 or less. The alloy comprises (by mass) C in an amount of 0.2% or less, Si in an amount of 0.5% or less, Mn in an amount of 0.5% or less, Cr in an amount of 10 to 24%, one or both of Mo and W in such an amount satisfying the following formula: Mo+0.5 W=5 to 17%, Al in an amount of 0.5 to 2.0%, Ti in an amount of 1.0 to 3.0%, Fe in an amount of 10% or less, and one or both of B and Zr in an amount of 0.02% or less (excluding 0%) for B and in an amount of 0.2% or less (excluding 0%) for Zr, with the remainder being 48 to 78% of Ni and unavoidable impurities.

Abstract: An austenitic heat resistant alloy, which comprises, by mass percent, C?0.15%, Si?2%, Mn?3%, Ni: 40 to 80%, Cr: 15 to 40%, W and Mo: 1 to 15% in total content, Ti?3%, Al?3%, N?0.03%, O?0.03%, with the balance being Fe and impurities, and among the impurities P?0.04%, S?0.03%, Sn?0.1%, As?0.01%, Zn?0.01%, Pb?0.01% and Sb?0.01%, and satisfies the conditions [P1=S+{(P+Sn)/2}+{(As+Zn+Pb+Sb)/5}?0.050], [0.2?P2=Ti+2Al?7.5?10×P1], [P2?9.0?100×O] and [N?0.002×P2+0.019] can prevent both the liquation crack in the HAZ and the brittle crack in the HAZ and also can prevent defects due to welding fabricability, which occur during welding fabrication, and moreover has excellent creep strength at high temperatures. Therefore, the alloy can be used suitably as a material for constructing high temperature machines and equipment, such as power generating boilers, plants for the chemical industry and so on.

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: A component for a high-temperature steam turbine which operates at temperatures above 600° C., especially above 700° C., is formed of a nickel-based alloy. The negative influence of oxidation of the component which is induced by the superheated steam is prevented by the alloy which is used, having the following composition (in % by weight): C: ?0.2 Si: ?1.0 Mn: ?1.0 Cr: 22.0-25.0 Co: 15.0-25.0 Mo: ?3.0 Nb: ?2.0 Al: 1.0-3.0 Ti: 2.0-4.0 Fe: ?2.0 Zr: ?0.2 B: ??0.05 Ni: remainder.

Abstract: A method for locally heat-treating a gas turbine engine superalloy article to improve resistance to strain-induced fatigue of the article is disclosed. The method comprises providing a gas turbine engine superalloy article having a gamma prime solvus temperature; and locally over aging only a selected portion of the article to locally improve fatigue resistance at the selected portion of the article, wherein the local over age cycle includes heating at about 843° C. for about 3 to 4 hours.

Abstract: A fuel cell catalyst comprising platinum, chromium, and copper, nickel or a combination thereof. In one or more embodiments, the concentration of platinum is less than 50 atomic percent, and/or the concentration of chromium is less than 30 atomic percent, and/or the concentration of copper, nickel, or a combination thereof is at least 35 atomic percent.

Abstract: Nickel based superalloys with excellent mechanical strength, corrosion resistance and oxidation resistance, which consist essentially of chromium in an amount of 3 to 7% by weight, cobalt in an amount of 3 to 15% by weight, tungsten in an amount of 4.5 to 8% by weight, rhenium in an amount of 3.3 to 6% by weight, tantalum in an amount of 4 to 8% by weight, titanium in an amount of 0.8 to 2% by weight, aluminum in an amount of 4.5 to 6.5% by weight, ruthenium in an amount of 0.1 to 6%, hafnium in an amount of 0.01 to 0.2% by weight, molybdenum in an amount of less than 0.5% by weight, carbon in an amount 0.06% by weight or less, boron in an amount of 0.01% by weight or less, zirconium in an amount of 0.01% by weight or less, oxygen in an amount of 0.005% by weight or less, nitrogen in an amount of 0.005% by weight or less and inevitable impurities and the balance being nickel.

Abstract: Bulk amorphous alloys based on quaternary Ni—Zr—Ti—Al alloy system, and the extension of this quaternary system to higher order alloys by the addition of one or more alloying elements, methods of casting such alloys, and articles made of such alloys are provided.

Abstract: A Ni-based alloy member has resistance against grain boundary fracture, fatigue strength, and oxidation resistance at temperatures near 1000° C. or higher. The Ni-based alloy member includes a non-repaired region made of a Ni-based alloy base and a region repaired by welding, which is formed on the non-repaired region and which is made of a buildup-welded layer, the buildup-welded layer being made of a Ni-based alloy containing, by weight, 15% or less of Co, 18-22% of Cr, 0.8-2.0% of Al, 5.0% or less of Ta, 0.5% or less of Mo, 0.5% or less of Ti, 13-18% of W, 0.05-0.13% of C, 0.06% or less of Zr, 0.015% or less of B, 0.4-1.2% of Mn, and 0.1-0.3% of Si, the balance of the alloy being preferably essentially made of Ni.

Abstract: A Ni-based heat resistant alloy for a gas turbine combustor, comprising a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.001 to 0.020%, C: 0.03 to 0.15%, and a balance consisting of Ni and unavoidable impurities, wherein a content of S and P contained in the unavoidable impurities is controlled to be, in mass %, S: 0.015% or less, and P: 0.015% or less, wherein the alloy has a texture in which M6C type carbide and MC type carbide are uniformly dispersed in ? phase matrix.

Abstract: A wire for welding Ni-based heat resistant alloy, comprising: a composition containing, in mass %, Cr: 14.0 to 21.5%, Co: 6.5 to 14.5%, Mo: 6.5 to 10.0%, W: 1.5 to 3.5%, Al: 1.2 to 2.4%, Ti: 1.1 to 2.1%; Fe: 7.0% or less, B: 0.0001 to 0.020%, C: 0.03 to 0.15%, and a balance of Ni and unavoidable impurities, wherein a content of S and P contained in the unavoidable impurities is controlled to be, in mass %, S: 0.004% or less, and P: 0.010% or less, wherein the wire has a texture in which M6C type carbide and MC type carbide are uniformly dispersed in the matrix.

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 steam turbine power plant which is provided with an extra-high-pressure turbine 100, a high-pressure turbine 200, an intermediate-pressure turbine 300 and a low-pressure turbine 400, and has high-temperature steam of 650° C. or more introduced into the extra-high-pressure turbine 100, wherein the extra-high-pressure turbine 100 has an outer casing cooling unit which cools an outer casing 111, and a turbine rotor 112, an inner casing 110 and a nozzle box 115 of the extra-high-pressure turbine 100 are formed of an Ni base heat-resisting alloy, and the outer casing 111 is formed of a ferrite-based alloy.

Abstract: A nickel-based superalloy that forms a chromia scale in an oxidizing environment is disclosed. The alloy provides good oxidation resistance at temperatures below 900° C. in a dry or moist atmosphere. The superalloy is suited for components of gas or steam turbine engines including blades and vanes.

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: An organic silver salt composition used for thermally developable photothermographic material is disclosed, comprising at least two organic acids differing in melting point and their silver salts, wherein a silver salt of a lower-melting organic acid account for 10 to 80 mol % of the silver salts and the lower melting organic acid accounting for 0 to 30 mol % of the acids. A method of manufacturing an organic silver salt compositions also disclosed.

Abstract: The present invention provides a Ni-based super alloy including, by mass %, C: 0.01 to 0.15%; Si: 1% or less; Mn: 1% or less; P: 0.02% or less; S: 0.01% or less; Co: less than 0.10%; Cr: 16 to 22%; Mo: 4 to 10%; W: 5% or less; Al: 1.2 to 2.5%; Ti: 2.4 to 4%; B: 0.001 to 0.05%; Zr: 0.01 to 0.5%; Fe: 1% or less; and a balance of Ni and inevitable impurities.

Abstract: A family of 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. A first alloy consists essentially of, by weight, 1 8% to 20% cobalt, 22.2% to 22.8% chromium, 1.8% to 2.2% tungsten, greater than 1.5% to 2.3% aluminum, 1.6% to 2.4% titanium, where the sum of aluminum and titanium is 2.8% to 4.4%, 0.7% to 0.9% columbium, 0.9% to 1.9% tantalum, 0.003% to 0.009% boron, 0.002% to 0.02% zirconium, 0.05% to 0.10% carbon, with the balance essentially nickel and incidental impurities. A second alloy consists essentially of, by weight, 5% to 8% cobalt, 22.2% to 22.8% chromium, 1.8% to 2.2% tungsten, 1.2% to 2.3% aluminum, 1.6% to 2.4% titanium, where the sum of aluminum and titanium is 2.8% to 4.4%, 0.7% to 0.9% columbium, 0.9% to 1.9% tantalum, 0.003% to 0.009% boron, 0.002% to 0.02% zirconium, 0.05% to 0.10% carbon, with the balance essentially nickel and incidental impurities.

Abstract: A nickel base superalloy comprising 14.0 to 20.0 wt % cobalt, 13.5 to 17.0 wt % chromium, 2.5 to 4.0 wt % aluminium, 3.4 to 5.0 wt % titanium, 0 to 3.0 wt % tantalum, 3.8 to 5.5 wt % molybdenum, 0.035 to 0.07 wt % carbon, 0.01 to 0.04 wt % boron, 0.055 to 0.075 wt % zirconium, 0 to 0.4 wt % hafnium and the balance nickel plus incidental impurities. The nickel base superalloy is suitable for use as gas turbine engine high pressure compressor rotor discs or turbine discs. It is capable of operation at temperatures above 700° C. and has good fatigue crack propagation resistance, creep resistance and tensile strength.

Abstract: A welding material composition, which is a nickel based super alloy having ?? phase and chromium carbides precipitated. The composition comprising 18 to 25% by weight of Co, 15 to 20% by weight of Cr, 1.5 to 5.5% by weight of Al, 5 to 14% by weight of W, 0.05 to 0.15% by weight of C, 0 to 0.02% by weight of B, 0 to 1% by weight of at least one of Ta, Nb, Ti, Mo, Re and Fe, 0 to 0.5% by weight of at least one of V, Zr, rare earth elements and Y, 0 to 1% by weight of Mn, 0 to 0.5% by weight of Si, and the balance being Ni.

Abstract: A high-temperature protection layer contains (% by weight) 23 to 27% Cr, 4 to 7% Al, 0.1 to 3% Si, 0.1 to 3% Ta, 0.2 to 2% Y, 0.001 to 0.01% B, 0.001 to 0.01% Mg and 0.001 to 0.01% Ca, remainder Ni and inevitable impurities. Optionally, the Al content is in a range from over 5 up to 6% by weight.

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%.