Abstract: A nickel- or cobalt-based alloy of the type containing, by weight, 5 to 40% chromium, up to about 10% aluminum, up to about 10% titanium, up to about 30%, in combination, of elements from the group tantalum, tungsten, molybdenum, columbium, rhenium, or vanadium, up to about 2% silicon, up to about 5% hafnium, and up to about 5% reactive elements such as lanthanum, yttrium or other rare earths. Manganese is present in an amount from 0.1 to 12%, preferably 0.5 to 4%. Silicon in amounts from 1.0 to 2.0 by weight, or hafnium in amounts from 0.1 to 5.0% by weight may also be used. Alloys in accordance with this invention are particularly suitable for casting by the single crystal technique; however, the alloys can also be used in the production of polycrystalline components such as directionally solidified, conventionally solidified (equiaxed), wrought, or dispersion strengthened materials. In the latter case, grain boundary modifiers such as carbon, boron, zirconium and hafnium are utilized.

Abstract: A carburization-resistant alloy comprising in weight percent about 50 to about 55% nickel, about 16 to 22% chromium, about 3 to about 4.5% aluminum, up to about 5% cobalt, up to about 5% molybdenum, up to about 2% tungsten, about 0.03 to about 0.3% carbon, up to about 0.2% rare earth element, balance essentially iron. The alloy is useful for structures, objects, parts etc. which are exposed in use to carburizing atmospheres and which, periodically are subjected to oxidizing atmospheres. For example the alloys are useful for pyrolysis tubes used in the petrochemical industry which must periodically be subjected to oxidizing atmospheres to burn-out carbon deposits and which, during pyrolysis are in contact with atmospheres having log Po.sub.2 spanning at least the range of -17 to -26 and which exist at various temperatures.

Abstract: The present invention provides Ni (and/or Co) base precipitation hardened alloy compositions having improved resistance to stress corrosion cracking and being comprised of:12-25 wt. % Cr;0-10 wt. % Mo;0-12 wt. % W, with the proviso that Mo+0.5 W is .gtoreq.2 wt. % and .ltoreq.10 wt. % and with the proviso that Cr+Mo+0.5 W is .ltoreq.28 wt. %;2-6 wt. % of one or more of Al, Nb, and Ti;<0.05 wt. % C;<0.05 wt. % O;<0.05 wt. % N; and the balance being Ni (and/or Co) and any incidental impurities,wherein the concentrations of Ni (and/or Co), Cr and Mo (and/or W) are correlated so that their combination represents a point within the area ABCD of FIG. 1 hereof. Preferably, the ratio, expressed in atomic percent, of Al to Nb+Ti is between about 0 and 4.0, preferably between about 0.8 and 1.5, more preferably about 1. In addition, Hf is preferably included in a concentration, expressed in weight percent, of between about 10 (C+O+N) and 30 (C+O+N), more preferably between about 15 (C+O+N) and 20 (C+O+N).

Abstract: A nickel base superalloy composition useful in the cast+HIP+heat treated condition is described. Articles having the invention composition have properties which are comparable to similarly processed IN718 articles. The invention alloys have an as-cast microstructure which is substantially free from Laves phase, even at slow solidification rates. As a result, the alloys are significantly more weldable than IN718. This desirable microstructure is achieved by modifications of the chromium, molybdenum, iron, and nickel contents compared to the typical IN718 composition.

Abstract: Disclosed is a process for treating the surface of super alloys, notably nickel-base alloys, with thin cross sections, in preparation for brazing processes. The super alloy is heat treated in a partial pressure of oxygen at a temperature less than about 1975.degree. F. but above the engineering solvus temperature of gamma prime intermetallics followed by a rapid cooling step. The resultant alloy is thereby provided with a surface that has improved brazability.

Abstract: This invention relates to platinum group metal-containing alloys comprising, apart from impurities:(a) at least 40 wt. % nickel or at least 40 wt. % cobalt;(b) a trace to 30 wt. % chromium; and(c) a trace to 15 wt. % of one or more of the metals platinum, palladium, rhodium, iridium, osmium and ruthenium.

Abstract: A single crystal nickel alloy is provided having many of the foundry and performance characteristics of the higher density, single crystal, nickel base super alloys from which the vanes and blades are cast for high performance turbine aircraft engines. The lower density of this alloy permits its use for rebuilding and upgrading the performance of older turbine aircraft engines of designs which cannot withstand the centrifugal forces generated by the new state of the art higher density single crystal super alloys. The alloy for the first time provides a lower density single crystal alloy capable of heat treatment to stabilize its microstructure for high temperature, high stress use. It also provides for the first time a lower density alloy having acceptable resistance to the effects of high temperature sulfidation, salt corrosion and also to have good coating life.

Abstract: Methods for heat treating cast, nickel base superalloy articles are described. According to the invention, the articles are heated to progressively higher temperatures greater than the gamma prime solvus temperature and less than the incipient melting temperature. The incipient melting temperature is increased due to homogenization of segregate phases, while at the same time, the gamma prime goes into solution. The rate at which the temperature is increased closely approximates the rate at which the incipient melting temperature increases due to homogenization.

Abstract: A gamma-prime precipitation hardening nickel-base yttria particle-dispersion-strengthened superalloy having a composition consisting essentially of, by weight, 3.0 to 6.0% of Al, 8.5 to 10.9% of Co, 3.9 to 7.5% of Cr, 0.5 to 1.2% of Ti, 3.6 to 6.3% of Ta, 11.4 to 13.3% of W, 0.02 to 0.2% of Zr, 1.3 to 2.6% of Mo, 0.001 to 0.1% of C, 0.001 to 0.02% of B, 0.5 to 1.7% of yttria (Y.sub.2 O.sub.3), not more than 0.8% of O and the balance being Ni and having a structure composed of coarse recrystallized grains with a GAR of at least 20 and a short axis diameter of at least 0.

Abstract: A nickel-chromium alloy excellent in a stress corrosion cracking resistance which is obtained by carrying out an annealing treatment under specific conditions, said alloy having the following composition:______________________________________ in terms of % by weight, ______________________________________ 0.04% or less of C; 1.0% or less of Si; 1.0% or less of Mn; 0.030% or less of P; 0.02% or less of S; 40 to 70% of Ni; 25 to 35% of Cr; 0.1 to 0.5% of Al; 0.05 to 1.0% of Ti; 0.5 to 5.0% in all of one or more of Mo, W and V, and ______________________________________the residue comprising substantially Fe. A nickel-chromium alloy further including 0.2 to 5.0% of Nb subject to Ti=0.2 to 1.0% and Nb/C=10 to 125.

Abstract: A nickel-base single crystal superalloy having high creep rupture strength at high temperatures, said superalloy being obtained by subjecting a single crystal alloy having a composition consisting essentially of, by weight,Cr 4.5-10%,W 7.5-20%,Al 4.5-6%,Ta 2-12%,Co 5-10%,Ni substantially being the balance,W+Ta=17-24%,to a solutionizing treatment, an air cooling treatment and an aging treatment; and a process for producing the same.

Abstract: A solid solution, nonmagnetic, austenitic nickel base alloy class is described. It contains: about 12 to 21 weight percent chromium; a concentration of molybdenum and/or tungsten, such that the sum of the weight percent molybdenum and one third the weight percent tungsten present is between 1 and 7 weight percent and wherein the w % tungsten is less than 12 w %; about 4 to 13 w % iron; small but effective amounts of the desulfurizing agent, manganese; and up to about 2.5 w % silicon. Carbon may be present at levels up to 0.15 w % and cobalt may be present at levels up to 2 w %. The above elements are balanced to provide alloys having a mean thermal expansion coefficient, .alpha..sub.(RT-T), for T.ltoreq.1000.degree. F., of less than 8.3.times.10.sup.-6 in./in./.degree.F., and preferably less than 8.times.10.sup.-6 in./in./.degree.F.In addition, a precipitation hardening, non-magnetic, austenitic nickel base alloy class is also described.

Abstract: New .gamma.' strengthened nickel-base superalloy compositions are described that, when forged and properly heat treated, demonstrate superior resistance to fatigue crack growth accompanied by very good high temperature properties. Parts can be fabricated (e.g., using conventional cast and wrought processing) from these alloys without encountering difficulty in forging.

Abstract: A cobalt-free nickel-base superalloy composed of in weight % 15 Cr-5 Mo-3.5 Ti-4 Al-0.07 (max) C-remainder Ni is given a modified heat treatment. With this heat treatment the cobalt-free alloy achieves certain of the mechanical properties of the corresponding cobalt-containing nickel-base superalloy at 1200.degree. F. (650.degree. C.). Thus strategic cobalt can be replaced with nickel in the superalloy.

Abstract: A novel nickel-base high temperature alloy body preferably containing about 22% chromium, sufficient aluminum and titanium to provide a .gamma.' precipitate structure, additional strengthing elements and oxidic yttrium in finely dispersed form. The alloy body has an elongated crystal structure and is characterized by high strength along with excellent hot corrosion and oxidation resistance.

Abstract: In construction of a clad material for ornamental use such as eyeglass frames and watch bands, use of age-hardenable alloy sheath followed by age-hardening enables production of product with light weight, high mechanical strength, excellent workability and good fit to brazing and plating.

Abstract: Nickel alloys comprising less than 25% by volume of .gamma.' precipitate and containing 23 to 37% by weight of chromium and in addition a trace to 1.7% carbon, 0.3 to 4% by weight of platinum and/or 0.3 to 8% by weight of ruthenium, a trace to 1.5% by weight titanium and/or a trace to 1.5% aluminium the balance being nickel. The alloys combine improved corrosion resistance with high mechanical strength. Major improvements in mechanical strength seem to be obtained by adding small amounts of titanium and/or aluminium. The alloy is especially suited for use in contact with molten glass for example in a centrifugal spinner.

Abstract: A precipitation-hardening Ni-base alloy exhibiting improved resistance to corrosion under a corrosive environment containing at least one of hydrogen sulfide, carbon dioxide and chloride ions and method of producing the same are disclosed. The alloy is of the .gamma."-phase, or (.gamma.'+.gamma.")-phase precipitation hardening type in which Ti is restricted to less than 0.40% and is comprised of:C: not greater than 0.050%,Si: not greater than 0.50%,Mn: not greater than 2.0%,Ni: 40-60%,Cr: 18-27%,Ti: less than 0.40%,Mo: 2.5-5.5% and/or W: not greater than 11%, t 2.5%.ltoreq.Mo+1/2W.ltoreq.5.5%,Al: not greater than than 2.0%,Nb: 2.5-6.0% and/or Ta: not greater than 2.0%, 2.5%.ltoreq.Nb+1/2Ta.ltoreq.6.0%.

Abstract: Single crystal nickel-base superalloy having very fine gamma prime after heat treatment in a temperature range permitting total gamma prime solutioning without incipient melting. Component of the heat treated alloy has exceptional resistance to creep under high temperature and stress, particularly in that part of the creep curve representing one percent or less elongation. The alloy exhibits exceptionally low steady-state creep rate.

Abstract: A monocrystalline alloy with a high resistance to creep having a nickel base matrix, with a density of the order of 8.5 and having a percentage, by weight, composition as follows: Co 5 to 8%--Cr 6.5 to 10%--Mo 0.5 to 2.5%--W 5 to 9%--Ta 6 to 9%--Al 4.5 to 5.8%--Ti 1 to 2%--Nb 0 to 1.5%--C, Zr, and B each less than 100 ppm--Ni remainder to 100%. Furthermore, the summation Ta+Mo+1/2 W lies between 11.5% and 13.5% by weight, the atomic sum Ti+Al+Ta+Nb lies between 15.5% and 17%, the atomic sum Ta+Nb+Mo+1/2 W lies between 4% and 5.5%, the atomic sum Ti+Al+Ta+Nb+Mo+1/2 W lies between 17.5% and 19% and the atomic sum Ti+Al lies between 12.8% and 14.5%.

Abstract: A gamma prime strengthened nickel-base alloy characterized by a highly desirable combination of stress rupture life, hot corrosion resistance, oxidation resistance, phase stability and ductility. The alloy contains from 14 to 18% chromium, from 0.3 to 3% molybdenum, from 4 to 8% tungsten, from 0.01 to 1.0% vanadium, from 3.5 to 5.5% aluminum, from 1 to 4% titanium, from 3 to 7% cobalt, from 0.01 to 0.05% carbon and from 0.035 to 0.1% boron.

Abstract: The invention relates to an alloy suitable for making single-crystal castings and to a casting made thereof. The alloy comprises, by weight percent, Chromium 10-16%, Cobalt 4-16%, Molybdenum 2-4%, Tungsten 0-2%, Tantalum 2-8%, the sum of ##EQU1## lying between 5 and 7%, Aluminium 4-6%, Titanium 1-4% the sum of ##EQU2## lying between 5 and 7%. Carbon 0.015-0.05%, Boron 0-0.01%, Zirconium 0-0.01%, the balance being nickel plus incidental impurities.

Abstract: A method of heat treating a nickel base superalloy comprising solution treatment at 2050.degree. to 2150.degree. F. (1121.degree. to 1177.degree. C.) for about 2 hours and cooling at a rate at least as rapid as still air; stabilization at 1750.degree. to 1850.degree. F. (954.degree. to 1010.degree. C.) for 1/4 to 4 hours and cooling at a rate at least as rapid as still air; and precipitation hardening at 1350.degree. F. (732.degree. C.) for at least about 8 hours and air cooling. The heat treated product contains a low level of precipitated grain boundary carbides, and exhibits an optimum balance of tensile strength, stress rupture life and creep strength, along with reduced residual stress in the product.

Abstract: A gas turbine combustor defines a combustion chamber for combustion of injected fuel and for introduction of the resultant hot combustion gas to nozzles of a gas turbine. The combustor has parts subjected to hot combustion gas during operation of the turbine, such as a cap connected to a fuel injection nozzle, a liner connected to the cap, and a transition piece connected to the liner. These parts subjected to the hot combustion gas are made from an alloy having a composition consisting essentially of 0.02 to 0.2 wt % of C, 15 to 30 wt % of Cr and 10 to 25 wt % of W.

Abstract: Thermo-mechanical treatment of superalloys enabling simultaneously the production of a structure which is fine and homogeneous, with work hardened grains, a reduction in the stresses resulting from cooling and the absence of parasitic phase (Ni.sub.3 Nb-.delta. in the form of platelets for the Ni bases), characterized by an isothermal aging of predetermined duration after deformation in the final shaping sequence and in the finishing sequence which is followed by a limited amount of deformation and by a final heat treatment constituted solely by annealing producing precipitation of the hardening phase, this final treatment being optionally arranged to follow the finishing treatment, or in sequence, after cooling in air.

Abstract: A method is described for producing metallic articles, especially turbine disks, which have a hot-worked structure in one region and a warmworked structure in another region and thereby have properties which differ in different regions. The method comprises an initial hot-working step, an intermediate heat treatment step and a final warm-working step.

Abstract: Alignment of the [001] crystal axis of a face centered cubic metal with the primary z axis of a single crystal article provides good thermal fatigue resistance along the z axis, and minimizes cracking transverse to the axis. However, significant cracking is still observed parallel the z axis in severe applications. This cracking can be reduced by controlling the secondary crystallographic orientation (i.e., orientation of crystal axes within x-y planes transverse to the z axis), to make the [110] crystal axis tangent to the article surface in the region most prone to thermal fatigue cracking. Algorithims derived from empirical relationships enable calculation of the orientation likely to produce improved fatigue resistance. More durable single crystal gas turbine blades result when the [110] crystal axis is made tangent to the blade surface in the critical crack prone regions just behind the leading edge of the airfoil at about 40-80% of the airfoil span.

Abstract: There are described construction parts for gaseous hydrogen containing media which construction parts are made of a nickel alloy containing 40 to 70% nickel, 15 to 30% chromium, 0 to 20% cobalt, 5 to 10% molybdenum, and 0 to 20% iron and which construction parts have optimum hydrogen permeation prevention properties. For this purpose, the alloys contain 0.5 to 0.8% manganese and the parts are provided with a 1 to 10 .mu.m thick oxide coating by treating at a temperature of 850.degree. to 1000.degree. C. in an oxidizing atmosphere.

Abstract: Corrosion resistant, high strength, superalloy single crystal articles are described. Starting with a nominal composition of 11.75% Cr, 9% Co, 1.75% Mo, 4.5% W, 2.5% Ta, 2.5% Al, 4% Ti, balance essentially nickel, intentional additions are made of carbon and extra tantalum. From 0.05-0.15% carbon is added along with sufficient tantalum to combine with the carbon to form tantalum carbon. The resultant articles have substantially improved hot corrosion resistance and creep properties.

Abstract: Monocarbide reinforced nickel-base eutectic superalloys which are particularly characterized by improved resistance to the formation of surface nucleated carbides and are, therefore, especially suited for making unidirectionally solidified anisotropic metallic bodies in the form of vanes and rotating blades for aircraft gas turbine engines are provided.

Abstract: Concepts relating to the heat treatment of single crystal superalloy articles are disclosed. A first concept is the use of a heat treatment sequence which includes incipient melting of the article being heat treated followed by one or more steps which essentially heal the incipient melting damage. A second concept relates to the treatment of previously heat treated single crystal articles which have incipient melting. Methods are disclosed for healing this damage and for recovering the mechanical properties of such articles. A third concept disclosed is a particular cycle which permits effective heat treatment of a specific single crystal alloy composition.

Abstract: The alloy is a nickel base, superalloy specifically intended for the making of castings which consist of a single crystal. The castings are intended for use under extreme conditions of high temperature and stress. The alloy, for the first time, achieves the desired characteristics of phase stability, high stress-rupture strength and resistance to oxidation while maintaining a sufficient temperature differential between gamma prime solvus and incipient melting temperatures, that it is practical to solution heat treat without unacceptable percentages of rejects due to failure either to completely solution the primary coarse gamma prime or to initiation of incipient melting. In a modified form the coated oxidation/corrosion resistance of the alloy is increased by the addition of a trace quantity of hafnium.

Abstract: Methods for increasing the forgeability of cast superalloy materials are described. An extremely overaged microstructure is developed by solutionizing the material and slow cooling in the vicinity of the solvus temperature to cause a precipitation of extremely coarse gamma prime material. Subsequently the material can be isothermally forged.

Abstract: An improved eutectic superalloy composition is described. The eutectic composition upon solidification forms a gamma matrix, containing a substantial quantity of particles of the gamma prime phase, and containing about 12% by volume of aligned continuous chromium carbide fibers (Cr.sub.3 C.sub.2). Material of this composition is provided with significantly improved mechanical properties and surface stability through the addition of approximately one atomic percent of the material selected from the group consisting of manganese, technetium and rhenium. Directionally solidified articles of this composition have utility as gas turbine engine components.

Abstract: Monocarbide reinforced nickel-base eutectic superalloys which are substantially phase stable and have improved high temperature stress-rupture strength with improved resistance to the formation of surface nucleated carbides are provided. These superalloys are especially suited for making unidirectionally solidified anisotropic metallic bodies in the form of vanes and rotating blades for aircraft gas turbine engines.

Abstract: Single crystal nickel base superalloys of the gamma-gamma prime type are strengthened by deforming them 2-14% at temperatures in the range 700.degree.-1100.degree. C. Yield strength will be increased typically by 25-50%, depending on the crystallographic orientation. Careful control of parameters is necessary to obtain the strengthening while avoiding recrystallization. The metal is first homogenized and provided with a fine gamma prime deformation; strain rates in the range of 10.sup.-1 cm/cm/sec or less are used.

Abstract: In-pile parts for a nuclear reactor made of alloy consisting essentially of by weight 0.01-0.2% C, 10-21% Cr, 1-4% Ti, 0.3-2% Nb, 0.1-2% Al and the balance Ni wherein Ti content being higher than Nb content, said alloy having the microstructure of chromium carbides precipitated in the grain boundaries and a .gamma.' phase precipitated in the grains with the matrix thereof being austenite in microstructure.

Abstract: Single crystal superalloy articles of a composition similar to that of IN-939 are given a combined coating and heat treatment cycle. The cycle includes a solution treatment step, a coating application step, a post coating treatment at a temperature above the gamma prime solvus and one or more aging steps. Articles so treated have improved mechanical properties.

Abstract: A relatively low-density Nickel based superalloy particularly suitable for use in the form of a single crystal casting comprised by weight percent:Chromium: 7-13%Aluminium: 5-7%Titanium: 2-5%Cobalt: 4-16%Molybdenum and/or Ruthenium: 1-4%Vanadium: 0-2%Carbon: 0-0.05%Balance Nickel plus incidental impurities, the density of the alloy being less than 7.9 kg/dm.sup.3.

Abstract: A process of producing a NiCrFe alloy having a high resistance to stress corrosion cracking comprising heating a NiCrFe alloy to a temperature sufficient to enable the carbon present in the alloy body in the form of carbide deposits to enter into solution, rapidly cool the alloy body, and heat the cooled body to a temperature between 1100.degree. to 1500.degree. F. for about 1 to 30 hours.

Abstract: Disclosed in a gas turbine nozzle having a superior thermal fatigue resistance. The gas turbine nozzle is made of a cast alloy consisting essentially of 0.1 to 1 wt % carbon, 0.1 to 2 wt % silicon, 0.1 to 2 wt % manganese, 20 to 35 wt % chromium, 0.001 to 0.1 wt % boron, 5 to 15 wt % of at least one of tungsten and molybdenum, 16 to 35 wt % cobalt and the balance nickel. The alloy has a heat-treated structure in which eutectic carbides and secondary carbides are dispersed in the matrix.

Abstract: An Ni-Cr-W alloy having improved high temperature fatigue strength and superior creep rupture strength. The alloy contains, by weight, less than 0.1% of C, 21 to 26% of Cr, 16 to 21% of W and more than 50% of Ni. The alloy has a structure in which the austenite has a mean grain size larger than 100 .mu.m and in which the primary solid solution of W of body centered cubic crystal is precipitated preferentially in the austentite grain boundary. Disclosed also is a method of producing this alloy.

Abstract: An improved alloy for use in directional solidification casting is disclosed in which the proportions of carbon, zirconium, tungsten and molybdenum have been changed to produce a new ultra high strength casting alloy free of the problem of grain boundary cracking which has been encountered in the production of directional solidification castings of this type of alloy and to minimize M.sub.6 C plate phase formation in turbine blades under high temperature conditions over extended operating periods. In addition there is disclosed the unexpected characteristic of the alloy's substantial increase in fracture toughness and tensile ductility under extreme operating conditions.

Abstract: A high temperature oxidation resistant alloy. The alloy consists essentially of, by weight, from 14 to 18% chromium, from 4 to 6% aluminum, from 1.5 to 8% iron, a small but effective yttrium content not exceeding 0.04%, up to 12% cobalt, up to 1% manganese, up to 1% molybdenum, up to 1% silicon, up to 0.25% carbon, up to 0.03% boron, up to 1% tungsten, up to 1% tantalum, up to 0.5% titanium, up to 0.5% hafnium, up to 0.5% rhenium, up to 0.04% of elements from the group consisting of elements 57 through 71 of the periodic table of the elements, balance essentially nickel. The nickel plus the cobalt content is at least 66%. The iron content is in accordance with the relationship, Fe .gtoreq.3+4 (%Al-5), when the aluminum content is at least 5%.

Abstract: An alloy composition intended for use in the form of a single crystal casting comprises a modified nickel-based superalloy. The alloy consists essentially of, by weight percent,7-13% Chromium,0-15% Cobalt,1.25-3% Titanium+1/2 Niobium,4.5-6.7% Aluminium,3-12% Tungsten,0-3.5% Molybdenum,0-5% Tantalum,0-2% Hafnium,0-1.5% Vanadium,0.015-0.05% Carbon,0-0.01% Boron,0-0.05% Zirconium,Balance essentially Nickel plus incidental impurities.The invention also contemplates a heat treatment for the alloy comprising initially heating to 1300.degree.-1320.degree. C. followed by cooling to room temperature and ageing the alloy at a temperature of about 870.degree. C. for 16 hours.

Abstract: Directed to an overaging heat treatment applied to age-hardenable nickel-cobalt-iron controlled expansion alloys so as to contribute high notch strength at temperatures on the order of about 1000.degree. F. thereto.

Abstract: Directed to an overaging heat treatment applied to age-hardenable nickel-iron controlled expansion alloys so as to contribute high notch strength at temperatures on the order of about 1000.degree. F. thereto.

Abstract: New nickel rich metal alloys containing copper along with specific amounts of boron are disclosed. The alloys are subjected to rapid solidification processing (RSP) techniques which produce cooling rates between .about.10.sup.5 .degree. to 10.sup.7 .degree. C./sec. The as-quenched ribbon, powder, etc. consists primarily of a metastable crystalline solid solution phase. The metastable crystalline phases are subjected to suitable heat treatments so as to produce a transformation to a stable multiphase microstructure which includes borides. This heat treated alloy exhibits superior mechanical properties with good corrosion and/or oxidation resistance for numerous engineering applications.

Abstract: A specific composition range and process sequence are described for the production of single crystal superalloy articles which have an exceptional combination of high temperature mechanical properties and resistance to oxidation and hot corrosion. The nominal composition is 6% Ta, 9% Cr, 5% Co, 1% Ti, 1% Mo, 7% W, 5.5% Al, 0.15% Hf balance essentially nickel. Material of this composition is cast and solidifed in single crystal form and heat treated to produce an optimum microstructure.

Abstract: A high strength nickel base superalloy having a novel microstructure is described. The article consists of a gamma matrix containing a oriented gamma prime second phase having a plate or rod form. This noncuboidal gamma prime phase is produced by aging solution treated material under an applied stress. When this process is applied to a certain class of superalloys which are rich in refractory elements, the resultant structure provides exceptional resistance to creep at elevated temperatures.