A nickel-cobalt based superalloy composition consisting of by weight (wt.): 33.5 to 54 percent Ni; 19.5 to 36 percent Co; 9 to 12 percent Cr; 3.9 to 5.5 percent Al; 4.5 to 9.5 percent W; up to 5.5 percent Fe; 2 to 3.5 percent Mo; 0.6 to 5 percent Ta; 0.15 to 2.2 percent Ti; up to 1.75 percent Nb; up to 0.1 percent Hf; 0.005 to 0.03 percent C; 0.001 to 0.02 percent B; 0.005 to 0.06 percent Zr; up to 0.3 percent Si; up to 0.6 percent Mn; and the balance being impurities.

A nickel-cobalt based superalloy composition consisting of by weight (wt.): 33.5 to 54 percent Ni; 19.5 to 36 percent Co; 9 to 12 percent Cr; 3.9 to 5.5 percent Al; 4.5 to 9.5 percent W; up to 5.5 percent Fe; 2 to 3.5 percent Mo; 0.6 to 5 percent Ta; 0.15 to 2.2 percent Ti; up to 1.75 percent Nb; up to 0.1 percent Hf; 0.005 to 0.03 percent C; 0.001 to 0.02 percent B; 0.005 to 0.06 percent Zr; up to 0.3 percent Si; up to 0.6 percent Mn; and the balance being impurities.

A high hardness and temperature-resistant alloy is disclosed, and comprises 10-40 atomic percent Co, 30-56 atomic percent Cr, 10-40 atomic percent Ni, 6-13 atomic percent C, 0-8 atomic percent Mo, and 0-8 atomic percent W. Moreover, the elemental composition of the high hardness and temperature-resistant alloy can further comprise at least one additive element, such as Pb, Sn, Ge, Si, Zn, Sb, P, B, Mg, Mn, V, Nb, Ti, Zr, Y, La, Ce, Al, Ta, Cu, and Fe. Experimental data reveal that, the high hardness and temperature-resistant alloy can still show a property of hardness greater than HV100 in 900 degrees Celsius. Therefore, experimental data have proved that the high hardness and temperature-resistant alloy has a significant potential for applications in the manufacture of hot working die metals, components (e.g., turbine blade) for high temperature applications, and devices (e.g., aeroengine) for high temperature applications.

A method for coating a component of an aircraft engine with a wear-resistant layer, wherein the component is first coated at least regionally with a nickel- or cobalt-based alloy and subsequently aluminized. Also disclosed is a method for producing a spray powder for producing a wear-resistant layer of a component of an aircraft engine.

A method for coating a component of an aircraft engine with a wear-resistant layer, wherein the component is first coated at least regionally with a nickel- or cobalt-based alloy and subsequently aluminized. Also disclosed is a method for producing a spray powder for producing a wear-resistant layer of a component of an aircraft engine.

Provided is a metal gasket including, expressed in mass %, C: 0.10% or less, Si: 1.0% or less, Mn: 2.0% or less, P: 0.04% or less (including 0%), S: 0.01% or less (including 0%), Ni: 25.0-60.0%, Cr: 10.0-20.0%, either Mo or W alone, or both Mo+W/2:0.05-5.0%, Al: more than 0.8% to 3.0% or less, Ti: 1.5-4.0%, Nb: 0.05-2.5%, V: 1.0% or less (including 0%), B: 0.001-0.015%, Mg: 0.0005-0.01%, S/Mg: 1.0 or less, N: 0.01% or less (including 0%), and O: 0.005%) or less (including 0%), with the remainder being Fe and unavoidable impurities. The metal gasket has a metal structure in which a precipitate γ′ phase having an average equivalent circle diameter of 25 nm or larger is not present within the austenite base.

A nickel-based alloy composition consisting, in weight percent, of: between 1.0 and 3.5% aluminium, 0.0 and 3.6% titanium, 0.0 and 6.0% niobium, 0.0 and 4.9% tantalum, 0.0 and 5.4% tungsten, 0.0 and 4.0% molybdenum, 8.9 and 30.0% cobalt, 10.8 and 20.6% chromium, 0.02 and 0.35% carbon, between 0.001 and 0.2% boron, between 0.001 and 0.5% zirconium, 0.0 and 5.0% rhenium, 0.0 and 8.5% ruthenium, 0.0 and 4.6 percent iridium, between 0.0 and 0.5% vanadium, between 0.0 and 1.0% palladium, between 0.0 and 1.0% platinum, between 0.0 and 0.5% silicon, between 0.0 and 0.1% yttrium, between 0.0 and 0.1% lanthanum, between 0.0 and 0.1% cerium, between 0.0 and 0.003% sulphur, between 0.0 and 0.25% manganese, between 0.0 and 6.0% iron, between 0.0 and 0.5% copper, between 0.0 and 0.5% hafnium, the balance being nickel and incidental impurities, wherein the following equations are satisfied in which W.sub.Nb, W.sub.Ta, W.sub.Ti, W.sub.Mo, W.sub.Al, W.sub.Re and W.sub.Ru are the weight percent of niobium, tantalum, titanium, molybdenum, aluminium, rhenium and ruthenium in the alloy respectively 4.2≤(W.sub.w+0.92 W.sub.R.sub.e+1.58 W.sub.Ru) W.sub.Mo, W.sub.Al+CO 0.5 W.sub.Ti+0.3 W.sub.Nb+0.15W.sub.Ta≤4.0 and 3.0≤W.sub.Al+0.5W.sub.Ti+1.5(0.3W.sub.Nb+0.15W.sub.TA).

A nickel-based alloy composition consisting, in weight percent, of: between 1.0 and 3.5% aluminium, 0.0 and 3.6% titanium, 0.0 and 6.0% niobium, 0.0 and 4.9% tantalum, 0.0 and 5.4% tungsten, 0.0 and 4.0% molybdenum, 8.9 and 30.0% cobalt, 10.8 and 20.6% chromium, 0.02 and 0.35% carbon, between 0.001 and 0.2% boron, between 0.001 and 0.5% zirconium, 0.0 and 5.0% rhenium, 0.0 and 8.5% ruthenium, 0.0 and 4.6 percent iridium, between 0.0 and 0.5% vanadium, between 0.0 and 1.0% palladium, between 0.0 and 1.0% platinum, between 0.0 and 0.5% silicon, between 0.0 and 0.1% yttrium, between 0.0 and 0.1% lanthanum, between 0.0 and 0.1% cerium, between 0.0 and 0.003% sulphur, between 0.0 and 0.25% manganese, between 0.0 and 6.0% iron, between 0.0 and 0.5% copper, between 0.0 and 0.5% hafnium, the balance being nickel and incidental impurities, wherein the following equations are satisfied in which W.sub.Nb, W.sub.Ta, W.sub.Ti, W.sub.Mo, W.sub.Al, W.sub.Re and W.sub.Ru are the weight percent of niobium, tantalum, titanium, molybdenum, aluminium, rhenium and ruthenium in the alloy respectively 4.2≤(W.sub.w+0.92 W.sub.R.sub.e+1.58 W.sub.Ru) W.sub.Mo, W.sub.Al+CO 0.5 W.sub.Ti+0.3 W.sub.Nb+0.15W.sub.Ta≤4.0 and 3.0≤W.sub.Al+0.5W.sub.Ti+1.5(0.3W.sub.Nb+0.15W.sub.TA).

There are provided a Ni-based thermal spraying alloy powder having excellent corrosion resistance and erosion-corrosion resistance even in an environment in which corrosion acts or corrosion and erosion act simultaneously, and a method for manufacturing an alloy coating. A Ni-based thermal spraying alloy powder comprising Cr: 15 wt % or more and 25 wt % or less, Mo: 0 wt % or more and 5 wt % or less, Si: 0.5 wt % or more and less than 2 wt %, Fe: 5 wt % or less, C: 0.3 wt % or more and 0.7 wt % or less, and B: 4 wt % or more and 7 wt % or less, with the balance being Ni and incidental impurities.

There are provided a Ni-based thermal spraying alloy powder having excellent corrosion resistance and erosion-corrosion resistance even in an environment in which corrosion acts or corrosion and erosion act simultaneously, and a method for manufacturing an alloy coating. A Ni-based thermal spraying alloy powder comprising Cr: 15 wt % or more and 25 wt % or less, Mo: 0 wt % or more and 5 wt % or less, Si: 0.5 wt % or more and less than 2 wt %, Fe: 5 wt % or less, C: 0.3 wt % or more and 0.7 wt % or less, and B: 4 wt % or more and 7 wt % or less, with the balance being Ni and incidental impurities.