Abstract: Provided is a process for improving alloy properties which can improve the high-temperature ductility of a Ni-base heat-resisting alloy while maintaining its excellent high-temperature strength and weldability.

Abstract: A new nickel base superalloy suitable for compressor or turbine discs of gas turbine engines with fatigue crack propagation resistance equal to Waspaloy, tensile strength higher than Waspaloy and higher operating temperature than Waspaloy or UDIMET 720 family of alloys. The nickel base superalloy has a preferred composition by weight % of 14.0-19.0% cobalt, 14.35-15.15 Chromium, 4.25-5.25 Molybdenum, 1.35-2.15 tantalum, 3.45-4.15 titanium, 2.85-3.15 aluminium, 0.01-0.025 boron, 0.012-0.033 carbon, 0.05-0.07 zirconium, 0.5-1.0 hafnium, up to 1.0 rhenium, up to 2.0 tungsten, less than 0.5 niobium, up to 0.1 yttrium, up to 0.1 vanadium, up to 1.0 iron, up to 0.2 silicon, up to 0.15 manganese and balance nickel plus incidental impurities.

Abstract: Nickel-base alloys with improved elevated temperature creep and stress rupture lives are disclosed which are particularly useful for components in gas turbine engines exposed to high temperatures and stresses for long periods of time. The alloys are nickel-based consisting essentially of 0.005 to 0.15% C, 0.10 to 11% Mo, 0.10 to 4.25% W, from 12 to 31% Cr, 0.25 to 21% Co, up to 5% Fe, 0.10 to 3.75% Nb, 0.10 to 1.25% Ta, 0.01 to 0.10% Zr, 0.10 to 0.50% Mn, 0.10 to 1% V, l.8-4.75% Ti, 0.5 to 5.25% Al, less than 0.003% P, and 0.004 to 0.025% B. Key to the improvement of creep and stress rupture lives is the extremely low P content in conjunction with high B contents.

Abstract: The present invention is directed to the achievement of increased gas turbine engine efficiencies through further improvements in nickel-base superalloys used to make parts and components for gas turbine engines. The present invention comprises nickel-base superalloys for producing single crystal articles having a significant increase in temperature capability, based on stress rupture strength and low and high cycle fatigue properties, over single crystal articles made from current production nickel-base superalloys. Further, because of their superior resistance to degradation by cyclic oxidation, and their resistance to hot corrosion, the superalloys of this invention possess a balance in mechanical and environmental properties which is unique and has not heretofore been obtained.

Abstract: Improved compositions for fabricating nickel superalloy single crystal articles are described. The compositions are characterized by the substantial absence of carbon, boron, zirconium and vanadium and intentional additions of cobalt. The cobalt additions increase the stability of the compositions and provide enhanced heat treatability. Single crystal articles of these compositions have utility as gas turbine engine components.

Abstract: In order to provide a high strength Ni-base superalloy for directionally solidified castings, which is prevented from solidification cracking at the casting, having a sufficient grain boundary strength for ensuring reliability during its operation and a superior high temperature concurrently, a high strength Ni-base superalloy for directionally solidified castings having a superior grain boundary strength, which contains C: 0.05% to less than 0.1%, B: 0.015% to 0.04%, Hf: 0.01.about.less than 0.5%, Zr: less than 0.01%, Cr: 1.5%.about.16%, Mo: utmost 6%, W: 2.about.12%, Re: 0.1.about.9%, Ta: 2.about.12%, Nb: utmost 4%, Al: 4.5.about.6.5%, Ti: less than 0.5%, Co: less than 9%, and Ni: at least 60% in weight, is disclosed.

Abstract: An austenitic Ni-based alloy with improved workability, good corrosion resistance and good structure stability useful as heat exchanger tubing in sulphur-, chloride- or alkaline-containing environments. The material has an austenitic structure which contains in weight-% up to 0.025% C, 20-27% Cr, 8-12% Mo, up to 0.5% Si, up to 0.5% Mn, up to 0.3% Al, up to 0.1% N, 3-15% Fe, up to 0.5% Ti, up to 0.5% Nb, the remainder being Ni and usual impurities.

Abstract: A superalloy composition and single crystal articles of the composition are disclosed. The broad range, in weight percent, is 3.0-20.0% Co, 5.0-10.0% W, 5.0-7.0% Al, 0.4-2.9% Cr, 4.0-8.0% Ta, 0-1.0% V, 0-8.5% Re, 0-1.5% Ti, 0-3.0% Hf, 0-4.0% Mo, 0-2.0% Nb, 0-10.0% of one or more elements selected from the group consisting of Ru, Rh, Pd, Os, Ir, Pt, 0-1.0 of one or more elements selected from the group consisting of Y, La, Sc, Ce, lanthanides or actinides series of elements, balance essentially Ni. An equation is presented to select the most useful specific compositions from within this range.

Abstract: The invention relates to precipitation hardened alloy compositions comprising the following elements, with the contents expressed in % by weight:______________________________________ nickel: .gtoreq.52.00% chromium: 20.50%-22.50% iron: 7.00%-13.00% molybdenum: 5.50%-7.0% copper: 1.00%-3.50% niobium: 2.65%-3.50% titanium: 1.0%-2.0% cobalt: 0-3.00% aluminum: 0-0.75% tungsten: 0-0.50% silicon: 0-0.20% manganese: 0-0.20% phosphorous: 0-0.03% carbon: 0-0.02% nitrogen: 0-0.02% magnesium: 0-0.005% sulfur: 0-0.005% ______________________________________the elements satisfying the following four relationships:X=(2.271% Ti+1.142% Cr+0.957% Mn+0.858% Fe+0.777% Co+0.717% Ni+2.117% Nb+1.550% Mo+1.655% W+1.90% Al+1.90% Si+0.615% Cu).ltoreq.93.5, the percentages for this relationship being in atomic %;Y=(% Mo+% W+% Cu).ltoreq.9, the percentages for this relationship being in % by weight;A=(0.65% Nb+1.25% Ti+2.20% Al).gtoreq.4.

Abstract: The invention relates to an austenitic-chromium-iron alloy and its use as a material for articles with high resistance to isothermal and cyclic high temperature oxidation, high heat-resistance and high creep rupture strength at temperatures above 1100 to 1200.degree. C. The characterizing feature of the invention is that the austenitic nickel-chromium-iron alloy consists (in % by weight) of:______________________________________ 0.12 to 0.30% carbon 23 to 30% chromium 8 to 11% iron 1.8 to 2.4% aluminium 0.01 to 0.15% yttrium 0.01 to 1.0% titanium 0.01 to 1.0% niobium 0.01 to 0.20% zirconium 0.001 to 0.015% magnesium 0.001 to 0.010% calcium max 0.030% nitrogen max 0.50% silicon max 0.25% manganese max 0.020% phosphorus max 0.010% sulphur ______________________________________residue nickel, including unavoidable impurities caused by melting.

Abstract: A high strength nickel base superalloy article having a machined surface is disclosed. The superalloy comprises, in weight percent, 1.2-3.5 Al, 3.0-7.0 Ti, 12.0-20.0 Cr, 2.0-3.9 Mo, 10.0-20.0 Co, 0-4.5 W, 0.005-0.025 C, 0.005-0.05 B, 0.01-0.1 Zr, 0-0.005 Mg, 0-1.0 Ta, 0-1.0 Nb, 0-2.0 Fe, 0-0.3 Hf, 0-0.02 Y, 0-0.1 V, 0-1.0 Re, balance essentially Ni. The superalloy further comprises a plurality of discrete carbides essentially free from molybdenum for increased fatigue strength.

Abstract: A Ni-based superalloy consists of from 1.4 to 4.4 wt % of Cr; from 3 to 8 wt % of Co; from 5 to 7.5 wt % of W; from 4.8 to 7.5 wt % of Re; from 7.5 to 10 wt % of Ta; from 4.8 to 5.8 wt % of Al; from 0.1 to 0.2 wt % of Hf; from 0.1 to 0.5 wt % of Nb; from 0.01 to 0.05 wt % of Y; and balance Ni.

Abstract: A superalloy having more excellent hot corrosion resistance than conventional single crystal alloys, oxidation resistance levels as high as that of conventional single crystal alloys, high strength, and creep rupture strength; single crystal members used for a blade or a nozzle produced by utilizing such an alloy; and a combined cycle power generation system produced by utilizing such members. A highly hot corrosion resistant and high-strength superalloy consisting essentially of, by weight, 6-12% Cr, 4.5-6.5% Al, 2-12% W, 2.5-10% Ta, not more than 5.8% Mo, 0.1-3% Co, 0.2-3% Nb, 0.1-4% Re, not more than 0.3% Hf, and the balance being Ni and unavoidable impurities; single crystal members used for a blade or a nozzle produced utilizing such an alloy; and a combined cycle power generation system produced by utilizing such members.

Abstract: A high-temperature sulfidation-corrosion resistant nickel-base alloy includes 12.about.15 weight % of cobalt, 18.about.21 weight % of chromium, 3.5.about.5 weight % of molybdenum, 0.02.about.0.1 weight % of carbon, at most 2.75 weight % of titanium, and at least 1.6 weight % of aluminum. The remainder is essentially of nickel except for impurities. The high-temperature sulfidation-corrosion resistant nickel-base alloy has sufficient high-temperature strength and is highly resistant to a high-temperature sulfidation corrosion.

Abstract: A new nickel base superalloy suitable for compressor or turbine discs of gas turbine engines with fatigue crack propagation resistance equal to Waspaloy, tensile strength higher than Waspaloy and higher operating temperature than Waspaloy or UDIMET 720 family of alloys. The nickel base superalloy has a preferred composition by weight % of 14.0-19.0% cobalt, 14.35-15.15 Chromium, 4.25-5.25 Molybdenum, 1.35-2.15 tantalum, 3.45-4.15 titanium, 2.85-3.15 aluminium, 0.01-0.025 boron, 0.012-0.033 carbon, 0.05-0.07 zirconium, 0.5-1.0 hafnium, up to 1.0 rhenium, up to 2.0 tungsten, less than 0.5 niobium, up to 0.1 yttrium, up to 0.1 vanadium, up to 1.0 iron, up to 0.2 silicon, up to 0.15 manganese and balance nickel plus incidental impurities.

Abstract: This invention relates to nickel-cobalt based alloys comprising the following elements in percent by weight: from about 0.002 to about 0.07 percent carbon, from about 0 to about 0.04 percent boron, from about 0 to about 2.5 percent columbium, from about 12 to about 19 percent chromium, from about 0 to about 6 percent molybdenum, from about 20 to about 35 percent cobalt, from about 0 to about 5 percent aluminum, from about 0 to about 5 percent titanium, from about 0 to about 6 percent tantalum, from about 0 to about 6 percent tungsten, from about 0 to about 2.5 percent vanadium, from about 0 to about 0.06 percent zirconium, and the balance nickel plus incidental impurities, the alloys having a phasial stability number N.sub.v3B less than about 2.60. Furthermore, the alloys have at least one element selected from the group consisting of aluminum, titanium, columbium, tantalum and vanadium. Also, the alloys have at least one element selected from the group consisting of tantalum and tungsten.

Abstract: A nickel-base superalloy, in particular for the fabrication of monocrystalline components, consisting essentially of (measured in wt %) 6.0-6.8% of Cr, 8.0-10.0% of Co, 0.5-0.7% of Mo, 6.2-6.6% of W, 2.7-3.2% of Re, 5.4-5.8% of Al, 0.5-0.9% of Ti, 7.2-7.8% of Ta, 0.15-0.3% of Hf. 0.02-0.04% of C, 40-100 ppM of B, the remainder being nickel with impurities. The ratio (Ta+1.5 Hf+0.5 Mo-0.5 Ti)/(W+1.2 Re) is greater than or equal to 0.7.

Abstract: A heat-resistant nickel-based alloy having excellent welding properties, said nickel-based alloy consisting essentially of, in terms of wt. %, 0.05 to 0.25% of C, 18 to 25% of Cr, 15 to 25% of Co, at least one selected from the group consisting of up to 3.5% of Mo and 5 to 10% of W, with W+1/2Mo being 5 to 10%, 1.0 to 5.0% of Ti, 1.0 to 4.0% of Al, 0.5 to 4.5% of Ta, 0.2 to 3.0% of Nb, 0.005 to 0.10% of Zr, 0.001 to 0.01% of B and the balance being Ni and unavoidable impurities, wherein the (Al+Ti) content and the (W+1/2Mo) content are within the range surrounded by the lines connecting points A (Al+Ti: 5%, W+1/2Mo: 10%), B (Al+Ti: 5%, W+1/2Mo: 5%), C (Al+Ti: 7%, W+1/2Mo: 5%), and D (Al+Ti: 7%, W+1/2Mo: 10%) excluding the line A-B in FIG. 1.

Abstract: A nickel-based superalloy possessing good mechanical properties when hot regarding traction, creep and cracking resistance has a chemical composition which comprises, in percentages by weight: Co 14.5 to 15.5 ; Cr 12 to 15 ; Mo 2 to 4.5 : Al 2.5 to 4; Ti 4 to 6; Hf not more than 0.5 ; C 100 to 300 ppm; B 100 to 500 ppm; Zr 200 to 700 ppm; possibly W up to 4.5; and nickel as the remainder. Components made from these alloys have an excellent microstructural stability when operating at temperatures up to 800.degree. C.

Abstract: A nickel base superalloy composition consisting essentially of, in weight %, 9.3-10.0% Co, 6.4-6.8% Cr, 0.5-0.7% Mo, 6.2-6.6% W, 6.3-6.7% Ta, 5.45-5.75% Al, 0.8-1.2% Ti, 0.07-0.12% Hf, 2.8-3.2% Re, and balance essentially Ni wherein a carbon concentration of about 0.01 to about 0.08 weight % is provided for improving the cleanliness of a single crystal investment casting produced therefrom.

Abstract: A power generation gas turbine includes first stage turbine blades made of an alloy whose 10.sup.5 -hour 14-kgf/mm.sup.2 temperature capacity is 920.degree. C. or over, second and subsequent stage turbine blades made of an alloy whose 10.sup.5 -hour 14-kgf/mm.sup.2 temperature capacity is 800.degree. C. or over, first stage turbine nozzles made of an alloy whose 10.sup.5 -hour 6 kgf/mm.sup.2 temperature capacity is 900.degree. C. or over, and second and subsequent stage turbine nozzles made of an alloy whose 10.sup.5 -hour 6-kgf/mm.sup.2 temperature capacity is 800.degree. C. or over.

Abstract: Target for a magnetron-cathode sputtering apparatus is made from a cobalt base alloy containing additional elements in such concentrations that intermetallic phases are formed with at least one of these elements and intermetallic phases are observed on the basis of the phase diagram in the state of equilibrium at the operating temperature of the target. The grain boundaries, sub-grain boundaries, twin-grain boundaries or slip bands of the cobalt mixed crystal forming the matrix are decorated with the elements forming the intermetallic phases. X-ray diffraction diagrams made from the target display reflections of an intermetallic phase which is largely absent in the cast state and which forms only during a heat treatment in the temperature range below the solidus temperature of the alloy by a solid state reaction.

Abstract: Alloy foils for liquid-phase diffusion bonding of heat-resisting metals in an oxidizing atmosphere comprise 6.0 to 15.0 percent silicon, 0.1 to 2.0 percent manganese, 0.50 to 30.0 percent chromium, 0.10 to 5.0 percent molybdenum, 0.50 to 10.0 percent vanadium, 0.02 to 1.0 percent niobium, 0.10 to 5.0 percent tungsten, 0.05 to 2.0 percent nitrogen, 0.50 to 20.0 percent phosphorus, plus 0.005 to 1.0 percent carbon, and/or either or both of 0.01 to 5.0 percent titanium and 0.01 to 5.0 percent zirconium, all by mass, with the balance comprising nickel and impurities, and have a thickness of 3.0 to 300 .mu.m. Alloy foils for liquid-phase diffusion bonding of heat-resisting metals in an oxidizing atmosphere are also available with substantially vitreous structures.

Abstract: A protective coating resistant to corrosion at medium and high temperatures is applied on a nickel-based or cobalt-based superalloy component. The protective coating essentially consists of the following elements (in percent by weight): 25 to 40% nickel, 28 to 32% chromium, 7 to 9% aluminum, 1 to 2% silicon, 0.3 to 1% of at least one reactive element of the rare earths, at least 5% cobalt; and impurities, as well as selectively from 0 to 15% of at least one of the elements of the group consisting of rhenium, platinum, palladium, zirconium, manganese, tungsten, titanium, molybdenum, niobium, iron, hafnium, and tantalum. The total share of the elements of the group is from 0 to a maximum of 15% and a remainder of at least 5% cobalt. The component and the coating applied thereon have a ductile brittle transition temperature below 500.degree. C.

Abstract: A protective coating resistant to corrosion at medium and high temperatures is applied on a nickel-based or cobalt-based superalloy component. The protective coating essentially consists of the following elements (in percent by weight): 25 to 40% nickel, 28 to 32% chromium, 7 to 9% aluminum, 1 to 2% silicon, 0.3 to 1% of at least one reactive element of the rare earths, at least 5% cobalt; and impurities, as well as selectively from 0 to 15% of at least one of the elements of the group consisting of rhenium, platinum, palladium, zirconium, manganese, tungsten, titanium, molybdenum, niobium, iron, hafnium, and tantalum. The total share of the elements of the group is from 0 to a maximum of 15% and a remainder of at least 5% cobalt. The component and the coating applied thereon have a ductile brittle transition temperature below 500.degree. C.

Abstract: An age hardenable nickel base chromium, molybdenum, alloy as well as intermediate products and articles made therefrom are disclosed which, in the solution treated and age hardened condition, have a 0.2% yield strength greater than 100 ksi combined with resistance to pitting and crevice corrosion and to stress corrosion cracking in chloride and sulfide environments at elevated temperatures up to about 500.degree. F. without requiring working below the recrystallization temperature of the alloy. Broad and preferred ranges are disclosed as follows:______________________________________ Broad (w/o) Preferred (w/o) ______________________________________ C 0.1 Max. 0.03 Max. Mn 5 Max. 2 Max. Si 1 Max. 0.5 Max. P 0.03 Max. 0.015 Max. S 0.03 Max. 0.010 Max. Cr 16-24 18-22 Mo 7-12 7.5-11 W 4 Max. -- Nb 2-6 2.75-4.25 Ti 0.50-2.5 0.75-1.5 Al Trace-1 0.05-0.35 B 0.02 Max. 0.001-0.006 Zr 0.50 Max. 0.08 Max. Co 5 Max. -- Cu 0-3 0.5 Max. N 0.04 Max. 0.01 Max. Fe 20 Max.

Abstract: A nickel base superalloy composition consisting essentially of, in weight %, 9.3-10.0% Co, 6.4-6.8% Cr, 0.5-0.7% Mo, 6.2-6.6% W, 6.3-6.7% Ta, 5.45-5.75% Al, 0.8-1.2% Ti, 0.07-0.12% Hf, 2.8-3.2% Re, and balance essentially Ni wherein a carbon concentration of about 0.01 to about 0.08 weight % is provided for improving the cleanliness of a single crystal investment casting produced therefrom.

Abstract: A high Cr austenitic heat resistant alloy excellent in high temperature strength which essentially consists of, in weight percent, from more than 0.02% to 0.10% C, not more than 1.0% Si, not more than 2.0% Mn, 28 to 38% Cr, 35 to 60% Ni, from more than 0.5% to 1.5% Ti, not more than 0.05% N, 0.01 to 0.3% Al, 0.001 to 0.01% B, 0 to 0.1% Zr, 0 to 1.0% Nb, one or both of 0.5 to 3.0% Mo and 1.0 to 6.0% W, and the balance being Fe and incidental impurities. The alloy may further contain one or both of 0.001 to 0.05% Mg and 0.001 to 0.05% Ca. This alloy is suitable for producing a single layered tube which is less expensive and more reliable than the conventional double layered tube.

Abstract: This invention relates to a single crystal casting to be used under high stress, high temperature conditions up to about 2030.degree. F., characterized by an increased resistance to creep under such conditions. The casting is made from a nickel-based superalloy consisting essentially of the following elements in percent by weight: from 6.2 to 6.8 percent rhenium, from 1.8 to 2.5 percent chromium, from 1.5 to 2.5 percent cobalt, from 8 to 9 percent tantalum, from 3.5 to 6 percent tungsten, from 5.5 to 6.1 percent aluminum, from 0.1 to 0.5 percent titanium, from 0.01 to 0.1 percent columbium, from 0.25 to 0.60 percent molybdenum, from 0 to 0.05 percent hafnium, from 0 to 0.04 percent carbon, from 0 to 0.01 percent boron, from 0 to 0.01 percent yttrium, from 0 to 0.01 percent cerium, from 0 to 0.01 percent lanthanum, from 0 to 0.04 percent manganese, from 0 to 0.05 percent silicon, form 0 to 0.01 percent zirconium, from 0 to 0.001 percent sulfur, from 0 to 0.

Abstract: A nickel-based alloy which is excellent not only in anti-corrosion properties but also in workability is disclosed. The alloy contains 15 to 35 weight % of chromium; 6 to 24 weight % of molybdenum; wherein the sum of chromium plus molybdenum is no greater than 43 weight %; 1.1 to 8 weight % of tantalum; and balance nickel and unavoidable impurities. The alloy may optionally include no greater than 0.1 weight % of nitrogen; no greater than 0.3 weight % of magnesium, no greater than 3 weight % of manganese, no greater than 0.3 weight % of silicon, no greater than 0.1 weight % of carbon, no greater than 6 weight % of iron, no greater than 0.1 weight % of zirconium, no greater than 0.01 weight % of calcium, no greater than 1 weight % of niobium, no greater than 4 weight % of tungsten, no greater than 4 weight % of copper, no greater than 0.8 weight % of titanium, no greater than 0.8 weight % of aluminum, no greater than 5 weight % of cobalt, no greater than 0.

Abstract: Air meltable, weldable cast alloys of high hot strength and hot gas corrosion resistance especially in the service temperature range of about 1800.degree. F. to 2100.degree. F. which consist essentially of:______________________________________ Nickel 41-54% by weight Chromium 24-29% Iron 8-18% Cobalt 3-8% Tungsten 4.5-6.5% Molybdenum 4-6.5% Niobium 0.8-2% Manganese 0.1-1.5% Silicon 0.1-1.5% Carbon 0.2-0.4% ______________________________________provided, that the nickel plus cobalt content is at least about 45%.

Abstract: A rotating blade or stationary vane of a gas turbine which is made of a nickel alloy containing Cr, Co, Mo, W, Ta, Al, Ti, C, B, Zr, and one or both of Mg and Ca. Additionally, the alloy may contain Hf, Pt, Rh and Re.

Abstract: This invention relates to a hot corrosion resistant nickel-based superalloy comprising the following elements in percent by weight: from about 11.5 to about 13.5 percent chromium, from about 5.5 to about 8.5 percent cobalt, from about 0.40 to about 0.55 percent molybdenum, from about 4.5 to about 5.5 percent tungsten, from about 4.5 to about 5.8 percent tantalum, from about 0.05 to about 0.25 percent columbium, from about 3.4 to about 3.8 percent aluminum, from about 4.0 to about 4.4 percent titanium, from about 0.01 to about 0.06 percent hafnium, and the balance nickel plus incidental impurities, the superalloy having a phasial stability number N.sub.V3B less than about 2.45. Single crystal articles can be suitably made from the superalloy of this invention. The article can be a component for a gas turbine engine and, more particularly, the component can be a gas turbine blade or gas turbine vane.

Abstract: A Ni-base superalloy consisting essentially of, by weight: 0.05 to 0.20% C, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 55% Ni, the combination of the [Al+Ti] and tungsten contents being determined as shown in FIG. 5. This superalloy has a high thermal-fatigue resistance, a great high-temperature strength, particularly, a great creep rupture strength, and a good weldability. The superalloy is used to form gas turbine nozzles, which are employed in a gas turbine. Using such a gas turbine, a combined power generating system is built.

Abstract: The improved superalloy that possesses all the characteristics required of the high-temperature structural material of high-temperature gas-cooled reactors (i.e., high-temperature strength, corrosion resistance, good producibility, good hot workability and resistance to embrittlement due to thermal aging) consists essentially of 16-28% Cr, 15-24% W (provided that Cr+W=39-44%), 0.01-0.1% Zr, 0.001-0.015% Y, 0.0005-0.01% B, up to 0.05% C, up to 0.1% Si, up to 0.1% Mn (provided that Si+Mn.ltoreq.0.1%), up to 0.1% Ti, up to 0.1% Al and up to 0.1% Nb (provided that Ti+Al.ltoreq.0.1% and Ti+Al+Nb.ltoreq.0.15%), with the balance being Ni and inevitable impurities and all percentages being on a weight basis.

Abstract: A nickel-based monocrystalline superalloy suitable for turbine engine blades is obtained by adding to the alloy at least one element chosen from erbium and silicon, at a concentration by weight of 50 to 500 ppm for Er and of 500 to 1000 ppm for Si and, optionally, hafnium at a concentration by weight of 500 to 1000 ppm.

Abstract: The improved nickel-base heat-resistant alloy consists of 13.1-15.0% Cr (all percentages that follows are by weight), 8.5-10.5% Co, 1.0-3.5% Mo, 3.5-4.5% W, 3.0-5.5% Ta, 3.5-4.5% Al, 2.2-3.2% Ti, 0.06-0.12% C, 0.005-0.025% B, 0.010-0.05% Zr and 1-100 ppm of Mg and/or Ca, in the optional presence of 0-1.5% Hf and/or 0-0.5% of at least one element of Pt, Rh and Re, with the remainder being Ni and incidental impurities. The alloy has high strength and high resistance to oxidation and corrosion at elevated temperatures and, hence, is suitable for use as a constituent material for machine parts that are to be exposed to elevated temperatures.

Abstract: A nickel base alloy is provided having excellent hot and cold workability and superior corrosion resistance to a variety of media including deep sour gas well environments and highly corrosive oxidizing environments. The alloy consists essentially of, by weight, about 27 to 33% chromium, about 8 to 12% molybdenum, about 1 to 4% tungsten, and the balance nickel. The alloy may also contain as impurities or as additions, up to about 1.5% iron, up to about 0.15% carbon, up to about 1% aluminum, up to about 1% titanium and up to about 2% columbium.

Abstract: An Ni--Cr--W base alloy having superior creep strength and excellent corrosion resistance consists essentially of: by weight 21 to 25% of Cr, 18 to 25% of W, 0.5 to 2.0% Ti, 1 to 5% of Al, between zero and 0.2% of B, 0.025 to 0.5% of C, between zero and 0.3% of Zr and 0.3 to 3.0% of Ta, the balance being substantially Ni.

Abstract: An oxidation resistant alloy containing iron, cobalt, nickel and at least 4 to 5% by weight aluminum having at least a duplex crystalline structure. One crystalline component of this structure is a gamma (fcc) phase having a gamma prime phase dispersed therein. The second crystalline component is enriched in aluminum compared to the first crystalline component and exhibits characteristics under X-ray diffraction and electron diffraction analysis of a BCC B2 structured phase.

Abstract: A nickel-based superalloy suitable for directed solidification, in particular for industrial gas turbine parts, having the following composition by weight:Co: 0 to 5%Cr: 13 to 16%W: 0 to 2%Mo: 2 to 3.5%Al: 3.5 to 4%Ti: 3.5%Ta: 3.

Abstract: There is provided by the present invention nickel-base superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries and an improved balance between cyclic oxidation and hot corrosion resistance. The improved tolerance arises from the discovery that nickel-base superalloys suitable for casting as single crystal articles can be improved by the addition of small, but controlled, amounts of boron and carbon, and optionally hafnium, and is manifested principally by improved grain boundary strength. As one result of this increased grain boundary strength, grain boundary mismatches far greater than the 6.degree. limit for prior art single crystal superalloys can be tolerated in single crystal articles made from the nickel-base superalloys of this invention. This translates, for example, into lower inspection costs and higher casting yields as grain boundaries over a broader range can be accepted by visual inspection techniques without resort to expensive X-ray techniques.

Abstract: A nickel based superalloy composition is disclosed that provides increased high temperature stress-rupture strength and improved resistance to fatigue crack propagation at elevated temperatures up to about 760.degree. C. The composition is comprised of, by weight percent, about 10% to 12% chromium, about 17% to 19% cobalt, about 1.5% to 3.5% molybdenum, about 4.5% to 6.5% tungsten, about 3.25% to 4.25% aluminum, about 3.25% to 4.25% titanium, about 2.5% to 3,5% tantalum, about 0.02% to 0.08% zirconium, about 0.005% to 0.03% boron, less than 0.1% carbon, and the balance essentially nickel. Thermomechanical processing including isothermal forging at controlled strain rates and temperature ranges, supersolvus annealing, and slow cooling are disclosed for producing an enlarged grain structure that provides the improved properties in the alloy of this invention.

Abstract: A process is provided for welding a gamma-prime precipitation-strengthened nickel base superalloy by heating the weld area and adjacent region to a ductile temperature, welding while maintaining the entire weld area and adjacent region at the ductile temperature and holding the weldment, weld area and adjacent region at the ductile temperature until the entire weld has solidified. The ductile temperature is above the aging temperature but below the incipient melting temperature of the superalloy.

Abstract: A nickel-chromium-molybdenum-cobalt alloy has additions of tantalum and tungsten to provide superior stress rupture strength in the presence of grain size control agents, and has the following composition:______________________________________ Carbon 0.04-0.15 Iron 0-8 Chromium 18-25 Cobalt 10-15 Molybdenum 5-9 Aluminum 0.7-1.5 Tungsten 0-5 Titanium 0-0.5 Tantalum 0.7-2.5 Manganese 0-1 Silicon 0.05-0.75 Zirconium 0.01-0.05 Boron 0-0.

Abstract: A Ni-base superalloy consisting essentially of, by weight: 0.05 to 0.20% C, 20 to 25% Co, 15 to 25% Cr, 1.0 to 3.0% Al, 1.0 to 3.0% Ti, 1.0 to 3.0% Nb, 5 to 10% W, and at least 42.5% Ni, the combination of the [Al+Ti] and tungsten contents being determined as shown in FIG. 5. This superalloy has a high thermal-fatigue resistance, a great high-temperature strength, particularly, a great creep rupture strength, and a good weldability. The superalloy is used to form gas turbine nozzles, which are employed in a gas turbine. Using such a gas turbine, a combined power generating system is built.

Abstract: This invention relates to a nickel-based superalloy comprising the following elements in percent by weight: from about 5.0 to about 7.0 percent rhenium, from about 1.8 to about 4.0 percent chromium, from about 1.5 to about 9.0 percent cobalt, from about 7.0 to about 10.0 percent tantalum, from about 3.5 to about 7.5 percent tungsten, from about 5.0 to about 7.0 percent aluminum, from about 0.1 to about 1.2 percent titanium, from about 0 to about 0.5 percent columbium, from about 0.25 to about 2.0 percent molybdenum, from about 0 to about 0.15 percent hafnium, and the balance nickel+incidental impurities, the superalloy having a phasial stability number N.sub.v3B less than about 2.10.

Abstract: A nickel-base casting alloy for use in gas turbine components consists essentially of the composition (in weight percent): carbon 0.02-0.15, chromium 14-18, cobalt 8-12, aluminum 0.5-1.5, titanium 2.0-3.5, niobium 3.5-6.0, tantalum 1.0-2.0, tungsten 1.0-3.0, molybdenum 3.0-6.0, boron 0.002-0.05, zirconium 0.01-0.1, balance nickel and incidental impurities. The alloy is characterized by a volume fraction of gamma prime of about 32%, an ultimate tensile strength in the range 990-1010 MPa over the temperature range 550.degree.-750.degree. C., and a mean coefficient of linear thermal expansion in the range 11.5-15.0 alpha(*E-06/.degree.C.).

Abstract: Nickel base superalloy articles, especially gas turbine disks, are provided with substantially enhanced resistance to crack growth through a specific heat treatment. The heat treatment employs a true solution treatment step followed by a subsolvus solution treatment step, followed by at least one aging step. The effect of this series of heat treatment steps is to provide a microstructure having an optimum arrangement of gamma prime particles, with respect to both size and location. Reductions in crack growth rates of several hundred percent relative to prior art heat treatments are achieved.

Abstract: A superalloy component includes a substrate article of a superalloy, and a strengthenable, adherent coating on the substrate. The coating is preferably a nickel-base superalloy that is strengthened by the formation of gamma and gamma-prime phases. The coating is stronger than conventional MCrAlX coatings, and, therefore, more resistant to thermal fatigue. One operable coating has a composition, in weight percent, of about 7.5 percent cobalt, about 9 percent chromium, about 6 percent aluminum, about 1 percent titanium, about 1.5 percent molybdenum, about 4 percent tantalum, about 3 percent tungsten, about 3 percent rhenium, about 0.5 percent hafnium, about 0.3 percent yttrium, about 0.5 percent columbium, about 0.05 percent carbon, about 0.015 percent boron, about 0.015 percent zirconium, and balance nickel.