Honeywell International Inc.

The International Nickel Company, Inc.

The United States of America As Represented by the United States

Howmet Corporation

Alliedsignal Inc.

Avco Corporation

Inco Alloys International, Inc.

Howard F Merrick

Raymond C Benn

LeRoy R Curwick

Prabir R Bhowal

Michael K Korenko

Andrew F Hieber

Stephen J Donachie

Donald E Larsen, Jr

John R Mihalisin

Robert C Gibson

Prabir Ranjan Bhowal

Richard S Bellows

Frank W Heck

A nickel based superalloy composition comprising 16.0 to 20.0 weight % Co, 9.5 to 11.5 weight % Cr, 1.8 to 3.0 weight % Mo, 4.3 to 6.0 weight % W, 3.0 to 4.2 weight % Al, 3.0 to 4.4 weight % Ti, 1.0 to 2.0 weight % Ta, 0.5 to 1.5 weight % Nb, 0.01 to 0.05 weight % C, 0.01 to 0.04 weight % B, and 0.04 to 0.15 weight % Zr, balance Ni.

High temperature powder metallurgy superalloy with enhanced fatigue and creep resistance

A nickel base super alloy composition wherein the ratio of molybdenum to tungsten or to the sum of tungsten and rhenium,Is in the range of about 0.25 to about 0.5 weight percent.

High strength powder metallurgy nickel base alloy

A nickel based superalloy composition comprising about 16.5 to about 20.5 weight % Co, about 9.5 to about 12.5 weight % Cr, about 1.8 to about 3.2 weight % Mo, about 4.25 to about 6.0 weight % W, about 3.0 to about 4.2 weight % Al, about 3.0 to about 4.4 weight % Ti, about 1.0 to about 2.0 weight % Ta, about 0.6 to about 1.8 weight % Nb, about 0.01 to about 0.08 weight % C, about 0.01 to about 0.06 weight % B, and about 0.04 to about 0.15 weight % Zr, balance Ni.

A creep resistant titianium aluminide alloy composition consisting essentially of, in atomic percent, about 44 to about 49 Al, about 0.5 to about 4.0 Nb, about 0.0 to about 3.0 Mn, about 1.0 to about 1.5 W, about 0.1 to about 1.0 Mo, about 0.4 to about 0.75 Si, and the balance Ti.

Creep resistant gamma titanium aluminide alloy

Creep resistant titanium aluminide alloy article consisting essentially of, in atomic %, about 45 to about 48 Al, about 1.0 to about 3.0 Nb, about 0.5 to about 1.5 Mn, about 0.25 to about 0.75 Mo, about 0.25 to about 0.75 W, about 0.15 to about 0.3 Si and the balance titanium. The article has a heat treated microstructure including gamma phase, alpha-two phase and at least one additional particulate phase including, one or more or W, Mo, and Si dispersed as distinct regions in the microstructure.

Creep resistant titanium aluminide alloy

A dispersion strengthened aluminum-base alloy system is provided which is prepared by mechanical alloying and is characterized by an improved continuation of properties over binary aluminum-lithium alloys. The alloy system contains, by weight, about 0.5% up to about 4% Li, about 0.05 up to about 2% carbon, about 0.1 up to about 3% oxygen, at least one of the elements magnesium or copper in an amount of up to about 5% each, provided the total amount of said magnesium and copper does not exceed about 8%, and a dispersion strengthening agent in the amount of about 2% up to about 8% by volume.

Dispersion strengthened low density MA-Al

A nickel-chromium-iron alloy intended principally for automotive turbocharger applications, the alloy being characterized by good stress - rupture strength, ductility, tensile strength, etc. and containing, generally speaking, 10-15% Cr, 18-30% Fe, 3-4.25% Ti, 2.25-3.5% Al, Ti+Al from 6 to 7.25%, ratio of Ti to Al of at least 0.9 and up to 1.6, 4-6% Mo, 0.01-0.2% B, 0.03-0.3% C, balance essentially nickel.

Nickel-chromium-iron alloy

A method for heat treating an age-hardenable iron-nickel-chromium alloy to obtain a bimodal distribution of gamma prime phase within a network of dislocations, the alloy consisting essentially of about 25% to 45% nickel, 10% to 16% chromium, 1.5% to 3% of an element selected from the group consisting of molybdenum and niobium, about 2% titanium, about 3% aluminum, and the remainder substantially all iron. To obtain optimum results, the alloy is heated to a temperature of 1025.degree. C. to 1075.degree. C. for 2-5 minutes, cold-worked about 20% to 60%, aged at a temperature of about 775.degree. C. for 8 hours followed by an air-cool, and then heated to a temperature in the range of 650.degree. C. to 700.degree. C. for 2 hours followed by an air-cool.

Method for heat treating iron-nickel-chromium alloy

Nickel-base alloy containing chromium, aluminum, titanium, molybdenum, cobalt and tungsten has combination of strength and ductility at elevated temperatures, particularly including stress-rupture strength at 980.degree. C. and ductility at 760.degree. C., along with resistance against oxidation and to hot corrosion by combustion products from jet engine fuels. The alloy is especially useful in production of gas turbine rotor blade castings.

Nickel-based alloy

An iron-nickel-chromium age-hardenable alloy suitable for use in fast breeder reactor ducts and cladding which utilizes the gamma-double prime strengthening phase and characterized in having a morphology of the gamma-double prime phase enveloping the gamma-prime phase and delta phase distributed at or near the grain boundaries. The alloy consists essentially of about 40-50% nickel, 7.5-14% chromium, 1.5-4% niobium, 0.25-0.75% silicon, 1-3% titanium, 0.1-0.5% aluminum, 0.02-0.1% carbon, 0.002-0.015% boron, and the balance iron. Up to 2% manganese and up to 0.01% magnesium may be added to inhibit trace element effects; up to 0.1% zirconium may be added to increase radiation swelling resistance; and up to 3% molybdenum may be added to increase strength.

Precipitation hardenable iron-nickel-chromium alloy having good swelling

Nickel-base alloy containing chromium, aluminum, titanium and molybdenum, and desirably including cobalt and metal from group tungsten and tantalum, has combination of strength and ductility at elevated temperatures, particularly including stress-rupture strength at 1800.degree. F. and ductility at 1400.degree. F., along with resistance against oxidation and to hot corrosion by combustion products from jet propulsion fuels. Alloy is especially useful in production of gas turbine rotor blade castings.

Growing community of inventors

Suffern, NY, United States of America

Howard F Merrick