Nickel-based alloy

Abstract

A nickel-based alloy containing, by weight percentage based on the total alloy weight, 11 to 18 chromium; 16 to 28 cobalt; 1.5 to 7.0 molybdenum; 0 to 6.5 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 2.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.02 boron; 0.001 to 0.1 zirconium; nickel; and impurities is disclosed. A nickel-based alloy containing, by weight percentage based on the total alloy weight, 11 to 18 chromium; 24 to 28 cobalt; 1.5 to 7.0 molybdenum; 2.0 to 6.0 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 2.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.02 boron; 0.001 to 0.1 zirconium; nickel; and impurities is also disclosed.

Description

Technical Field

[0001]

[0001] Cross - Reference This application claims the benefit of priority of U.S. Provisional Patent Application No. 63 / 367,170, filed on June 28, 2022. The content thereof is incorporated herein by reference.

[0002]

[0002] The present invention relates to the field of metallurgy and, more particularly, to nickel - based alloys. Embodiments of the nickel - based alloys according to the present disclosure are suitable for use in structural applications exposed to high temperatures, such as above 649 °C (1200 °F).

Background Art

[0003]

[0003] Various commercially available nickel - based alloys are suitable for static structural applications exposed to temperatures up to about 649 °C (1200 °F). Some of these available alloys are used in static components of turbine engines, including, for example, compressor discharge nozzle (CDN) cases, combustor cases, and high / low - pressure turbine (HPT / LPT) case components. By way of example, Waspaloy alloy (UNS N07001) is used in the CDN and low - pressure turbine cases of the GE9X aircraft turbofan engine of the Boeing 777X aircraft. The Waspaloy alloy has the following composition in broad weight percentages: 18.00 - 21.00 chromium, 3.50 - 5.00 molybdenum, 12.00 - 15.00 cobalt, 1.20 - 1.60 aluminum, 2.75 - 3.25 titanium, 0.003 - 0.01 boron, 0.02 - 0.10 carbon, 0.02 - 0.08 zirconium, up to 2.00 iron, up to 0.10 manganese, up to 0.15 silicon, up to 0.015 phosphorus, up to 0.015 sulfur, up to 0.10 copper, and the balance nickel. The static turbine case component is a seamless part and can be formed by a series of processes including forging, drilling, and ring rolling at high temperatures of approximately 1093 °C (2000 °F).

[0004]

[0004] In the design of next-generation turbine engines, the goal is to increase engine efficiency by increasing the temperature of the components. In certain specific designs under consideration, the temperature may approach 816 °C (1500 °F). At these higher operating temperatures, the mechanical properties of currently commercially available nickel-based alloys may not meet the design requirements. Techniques that have been considered to increase the high-temperature properties of nickel-based alloys include increasing the gamma prime phase and / or the content of alloying elements. However, with those techniques, the resulting alloys may be prone to having an unstable microstructure.

[0005]

[0005] Accordingly, there is a need for a new nickel-based alloy having properties suitable for use in high-temperature environments such as temperatures approaching 816 °C (1500 °F). In particular, there is a need for a new nickel-based alloy having properties suitable for use in structural components of turbine engines that are exposed to temperatures approaching 816 °C (1500 °F).

Summary of the Invention

Means for Solving the Problems

[0006]

[0006] Embodiments of the nickel-based alloy according to the present disclosure include, in weight percentages based on the total alloy weight, 11-18 chromium; 16-28 cobalt; 1.5-7.0 molybdenum; 0-6.5 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 2.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.02 boron; 0.001-0.1 zirconium; nickel; and impurities. Certain non-limiting embodiments of the nickel-based alloy of this embodiment include 16-19 weight percent cobalt. In certain non-limiting embodiments of the nickel-based alloy of this embodiment, the aluminum equivalent number (Al eq ) of the alloy is in the range of 3.6-4.5. Some of the nickel-based alloys of this embodiment include a total concentration of aluminum and titanium of 7.0 weight percent or less based on the total alloy weight.

[0007]

[0007] Additional embodiments of the nickel-based alloy according to the present disclosure include, by weight percentage based on the total alloy weight, 11-16 chromium; 16-28 cobalt; 1.5-7.0 molybdenum; 0-6.5 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 2.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; at least 36 nickel; and impurities. Certain non-limiting embodiments of the nickel-based alloy of this embodiment include 16-19 weight percent cobalt. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments of the nickel-based alloy of this embodiment, the total concentration of aluminum, niobium, and titanium is 7.0 weight percent or less.

[0008]

[0008] Additional embodiments of the nickel-based alloy according to the present disclosure include, by weight percentage based on the total alloy weight, 11-18 chromium; 24-28 cobalt; 1.5-7.0 molybdenum; 2.0-6.0 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 2.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.02 boron; 0.001-0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum and titanium of 7.0 weight percent or less based on the total alloy weight.

[0009]

[0009] Additional embodiments of the nickel-based alloys according to the present disclosure include, by weight percentage based on the total alloy weight, 14-16 chromium; 24-27 cobalt; 1.5-7.0 molybdenum; 0-6.5 tungsten; 0-1.0 niobium; 1.7-2.0 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 7.0 weight percent or less based on the total alloy weight.

[0010]

[0010] Additional embodiments of the nickel-based alloys according to the present disclosure include, by weight percentage based on the total alloy weight, 13-17 chromium; 16-25 cobalt; 1.5-7.0 molybdenum; 0-6.5 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 36 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0011]

[0011] Additional embodiments of the nickel-based alloy according to the present disclosure include, by weight percentage based on the total alloy weight, 13-17 chromium; 16-19 cobalt; 1.5-7.0 molybdenum; 2.0-5.0 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0012]

[0012] Additional embodiments of the nickel-based alloy according to the present disclosure include, by weight percentage based on the total alloy weight, 14-17 chromium; 19-25 cobalt; 2.0-4.0 molybdenum; 0-6.5 tungsten; 0-0.8 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0013]

[0013] Additional embodiments of the nickel-based alloy according to the present disclosure include, by weight percentage based on the total alloy weight, 14-17 chromium; 16-19 cobalt; 2.0-4.0 molybdenum; 2.0-5.0 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; greater than 0 to 2.0 tantalum; 1.0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0014]

[0014] Additional embodiments of the nickel-based alloy according to the present disclosure include, by weight percentage based on the total alloy weight, 15-17 chromium; 22-26 cobalt; 2.0-4.0 molybdenum; 0-2.0 tungsten; 0-1.0 niobium; 1.0-4.0 aluminum; 1.0-6.0 titanium; greater than 0 to 2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0-0.2 carbon; 0-0.02 boron; 0-0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0015]

[0015] Additional embodiments of the nickel-based alloy according to the present disclosure include, by weight percentage based on the total alloy weight, 14 to 17 chromium; 15 to 18 cobalt; 2.0 to 4.0 molybdenum; 1.0 to 4.0 tungsten; 0 to 1.0 niobium; 1.0 to 3.0 aluminum; 2.0 to 4.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0 to 0.2 carbon; 0 to 0.02 boron; 0 to 0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0016]

[0016] The present disclosure also relates to a method of making an alloy having a composition according to the present disclosure, as well as comminution products, powders, and other manufactured articles consisting of or including the alloy according to the present disclosure.

[0017]

[0017] Further areas of applicability of the present invention will become apparent from the detailed description provided hereinafter. It should be understood that the detailed description and any specific examples herein are intended to illustrate certain embodiments of the present invention only and are not intended to limit the scope of the present invention.

[0018]

[0018] The present invention will be more fully understood from the following detailed description and the accompanying drawings, which are not necessarily to scale.

Brief Description of the Drawings

[0019]

Figure 1

[0019] In Example 1 of this specification, it is a photograph showing the configuration of a pair of VIM molds used to cast 11.34 kg (25 lb.) heats.

Figure 2

[0020] In Example 1 of this specification, the dimensions of the configuration of the VIM mold used to cast 11.34 kg (25 lb.) of heat are shown.

Figure 3

[0021] This is a photograph showing the casting of 11.34 kg (25 lb.) of heat produced in Example 1 of this specification.

Figure 4

[0022] This is a graph of yield strength (ksi) as a function of test temperature for a particular alloy heat and for a particular commercially available nickel-based alloy.

Figure 5

[0023] This is a graph of maximum tensile strength (ksi) as a function of test temperature for a particular alloy heat and for a particular commercially available nickel-based alloy.

Figure 6

[0024] This is a graph of elongation versus test temperature for several alloy heats.

Figure 7

[0025] This is a graph of the results of stress rupture under various distinct test conditions.

Figure 8

Figure 9

Figure 10

[0026] This is an electron microscope image of the alloy of Example P2F02.

Figure 11

[0027] This is an electron microscope image of the alloy of Example P2F07.

Best Mode for Carrying Out the Invention

[0020]

[0028] The reader will understand the foregoing details and others upon considering the following detailed description of various non-limiting and non-exhaustive embodiments according to the present disclosure.

[0029] To provide an overall understanding of the disclosed invention, various non-limiting embodiments are described and illustrated herein. It is understood that the various non-limiting embodiments described and illustrated herein are non-limiting and non-exhaustive. Accordingly, the present invention is not limited by the description of the various non-limiting and non-exhaustive embodiments disclosed herein. The features and characteristics illustrated and / or described in connection with the various non-limiting embodiments may be combined with the features and characteristics of other non-limiting embodiments. Such modifications and variations are intended to be included within the scope of this specification. Accordingly, the claims may be amended or supplemented to recite any feature or characteristic that is expressly or inherently described herein, or otherwise expressly or inherently supported by this specification. Further, Applicant reserves the right to amend the claims to affirmatively deny any feature or characteristic that may exist in the prior art. The various non-limiting embodiments disclosed and described herein may include, consist of, or consist essentially of the features and characteristics as variously described herein.

[0021]

[0030] All percentages provided herein with respect to alloy compositions are on a total weight basis of the particular alloy composition, unless otherwise indicated.

[0022]

[0031] Any patent, publication, or other disclosure material that is said to be incorporated by reference in whole or in part herein is incorporated herein only to the extent that the incorporated material does not conflict with the current definitions, descriptions, or other disclosure material set forth in this disclosure. Accordingly, to the extent necessary, the disclosure as set forth herein supersedes any conflicting material incorporated herein by reference. Any material or portion thereof that is said to be incorporated by reference herein but conflicts with the current definitions, descriptions, or other disclosure material set forth in this disclosure is incorporated only to the extent that no conflict arises between the incorporated material and the current disclosure material.

[0023]

[0032] In this specification, unless otherwise indicated, all numerical parameters are understood to be preceded and modified in all instances by the term "about", where the numerical parameters have the inherent variability characteristics of the underlying measurement techniques used to determine the numerical values of the parameters. At least, and not intending to limit the application of the doctrine of equivalents of the claims, each numerical parameter described in this specification should be construed at least in light of the reported significant digits and by applying ordinary rounding methods.

[0024]

[0033] Also, any numerical range described in this specification is intended to include all sub-ranges having the same numerical accuracy that are included within the described range. For example, the range "1 to 10" is intended to include all sub-ranges having a minimum value that is 1 or greater and a maximum value that is 10 or less, i.e., between (and including) the recited minimum value 1 and the recited maximum value 10, such as, for example, 2.4 to 7.6. Any limitation of any maximum numerical value described herein is intended to include all lower numerical limitations subsumed therein, and any limitation of any minimum numerical value described herein is intended to include all higher numerical limitations subsumed therein. Accordingly, the applicant reserves the right to amend this specification, including the claims, to expressly recite any sub-range that is included within the ranges expressly recited herein. Amending to expressly recite any such sub-range is in compliance with the requirements of 35 U.S.C. §§ 112 and 132(a) in that all such sub-ranges are intended to be inherently described herein. Additionally, as used herein when referring to a range of components, the terms "up to", "up to and including" include zero, provided that the particular component is not an unavoidable impurity.

[0025]

[0034] As used herein, the grammatical articles “one,” “a,” “an,” and “the” are intended to include “at least one” or “one or more” unless otherwise indicated. Thus, the grammatical articles are used herein to refer to one, or more than one (i.e., “at least one”), of the grammatical object of the article. By way of example only, “a component” means one or more components, and thus, optionally, more than one component is contemplated and may be employed or used in the implementation of the described embodiments. Further, unless the context of usage otherwise requires, the use of singular nouns includes the plural, and the use of plural nouns includes the singular.

[0026]

[0035] References herein to nickel-based alloys “comprising” a particular composition are intended to encompass alloys “consisting essentially of,” or “consisting of,” the recited composition. It will be understood that nickel-based alloy compositions described herein that “consist of,” or “consist essentially of,” a particular composition may also contain impurities.

[0027]

[0036] Nickel-based alloys suitable for use in static structural components in turbine engines exposed to operating temperatures approaching 816 °C (1500 °F) must maintain suitable mechanical properties at those operating temperatures. Suitable nickel-based alloys must exhibit sufficient ductility to permit a fatigue crack growth rate that provides damage tolerance and containment. Tensile properties must also be sufficient, but not at the expense of imparting sufficient low cycle fatigue (LCF) properties. The alloys should also exhibit suitable high temperature creep properties, fracture toughness, and fatigue crack growth (FCGR) properties. Additionally, the alloys should be formable, for example by ring rolling, when used in turbine case applications. Importantly, the alloys should also be inspectable by non-destructive test methods and weldable to permit repair and readjustment, and preferably, should meet the cost requirements for application. Some of these requirements are described in more detail hereinafter.

[0028]

[0037] The alloys according to the present disclosure should exhibit suitable tensile properties. In various embodiments, the alloys according to the present disclosure exhibit various tensile properties that are at least as high as those of at least Waspaloy alloy (UNS N07001). Higher gamma prime volume fractions can enhance the tensile properties. The gamma prime volume fraction can be adjusted, for example, by adjusting the total content of alloying elements titanium, aluminum, niobium, and tantalum. Generally, as the total content of those elements in the alloy increases, the gamma prime volume fraction increases. The gamma prime content of the alloy can be determined by examining the alloy microstructure. The gamma prime fraction can also be approximated by the Al eq number according to the following equation for the purposes of the present disclosure. Al eq = [Al] + 0.56×[Ti] + 0.3×[Nb] + 0.15×[Ta] where [Al], [Ti], [Nb], and [Ta] are the weight percentage concentrations of the elements in the alloy. However, higher gamma prime volume fractions may reduce the forgeability and may also reduce the fatigue crack propagation resistance properties. The chemical properties of the gamma prime fraction in the alloy can be adjusted by changing the titanium / aluminum ratio, and the adjustment to that ratio can change the coherent strain and the interaction of dislocations with particles in the alloy. The antiphase boundary (APB) energy can control the reduction of precipitates by dislocations, can be controlled by the chemical properties of the gamma prime, and the introduction of elements such as niobium into the alloy can change the APB energy. Smaller grain sizes can improve the tensile properties. The thermomechanical parameters, subsolvus versus supersolvus heat treatments, and carbide / gamma prime content can control the grain growth at high temperatures. The chemical properties of the matrix can be modified by solid solution strengthening and by the addition of elements such as molybdenum and tungsten, which are matrix strengtheners that partition into the gamma phase matrix.

[0029]

[0038] The alloys according to the present disclosure should exhibit suitable creep properties. Larger grain sizes can improve creep properties, but this may be done at the expense of tensile properties. Higher gamma prime volume fractions can also improve creep properties. An increase in the content of refractory elements such as tungsten and molybdenum can also improve creep properties due to their low diffusion rates.

[0030]

[0039] In various non-limiting embodiments, the alloys according to the present disclosure exhibit low cycle fatigue performance that is at least as favorable as that of Waspaloy alloys. Smaller grain sizes can impart better low cycle fatigue properties. For an acceptable low cycle fatigue performance when the grain size is, for example, about ASTM 10 - 12, the carbonitrides can act as crack initiation sites. Nickel-based alloys used in turbine engine case applications typically need to have a grain size of ASTM 4 - 5, and it is generally not known whether the carbonitrides can be detrimental to low cycle fatigue. The balance of the gamma prime volume fraction can also be important in imparting suitable low cycle fatigue properties. In certain non-limiting embodiments, the nickel-based alloys according to the present disclosure can include a grain size in the range of ASTM 2 - 12, such as, for example, ASTM 2 - 3, ASTM 5 - 12, ASTM 4 - 8, ASTM 4 - 5, ASTM 5 - 6, ASTM 5 - 10, or ASTM 6 - 12.

[0031]

[0040] In various embodiments, alloys according to the present disclosure exhibit acceptable fracture toughness and fatigue crack growth rate characteristics. Larger grain sizes can improve (reduce) the fatigue crack growth rate. To improve the fatigue crack growth resistance of nickel-based alloys that are exposed to high temperature conditions during use, the alloys may be heat treated at a temperature higher than their gamma prime solvus temperature (commonly referred to as super solvus heat treatment), which may result in significant and uniform coarsening of the grains. Larger grains can also improve the hold time fatigue performance with a creep component in the matrix. A fine size of gamma prime in the matrix during input can result in a reduction of the precipitate and produce flat slip that reduces the fatigue crack growth rate. Increasing the gamma prime phase content can reduce the K1C (plane strain) fracture toughness, and similarly, the gamma prime content can affect the fatigue crack growth rate.

[0032]

[0041] In various embodiments, alloys according to the present disclosure may be forged by ring rolling. Ring rolling is particularly important in applications for turbine engine cases, which preferably have no seams, for annular components. The larger the forging time range for the alloy, the better the forgeability. Next, the forging time range can be adjusted by adjusting the gamma prime solvus temperature (a function of the chemical properties of gamma prime) and the solidus temperature (a function of the chemical properties of the matrix). The carbonitride content is a result of the content of carbon and carbide forming elements (e.g., niobium, titanium), and the balance of the gamma prime content can also affect the ring rolling forgeability of the alloy.

[0033]

[0042] In various embodiments, the alloys according to the present disclosure exhibit acceptable long-term microstructural stability. In order to inhibit the formation of topologically close-packed (TCP) phases, the chromium content should be limited and it may be necessary to balance heavy elements (e.g., tungsten, molybdenum, and niobium). Excessive chromium can destabilize the microstructure and form sigma phases. The alloys according to the present disclosure also preferably exhibit acceptable aging degradation of mechanical properties. The main reasons for property degradation in nickel-based superalloys are the formation of secondary phases such as sigma phases and the coarsening of gamma prime phases. The improvement of gamma prime stability can be achieved by including a higher aluminum content in the chemical properties of gamma prime. The chemical properties of the alloy should also preferably be controlled to have a lower lattice misfit and stable carbides.

[0034]

[0043] The alloys according to the present disclosure are also preferably inspectable using non-destructive testing (NDT) techniques. Generally, smaller grain sizes improve the NDT inspectability of the alloy. Also, avoiding the formation of carbonitride bands (“carbonitride banding”) improves NDT inspectability.

[0035]

[0044] The alloys according to the present disclosure also preferably have acceptable weldability such that, for example, components formed from the alloy can be repaired and overhauled without unacceptable degradation of the mechanical and other important features of the alloy. Generally, the easier it is to weld a superalloy, the more difficult it is to establish satisfactory creep strength. This problem is particularly acute in alloys for gas turbine applications. Weldability can be improved by reducing the gamma prime content, but there is a risk of adversely affecting certain other features of the alloy.

[0036]

[0045] With the foregoing observations and objectives in mind, non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications include, in weight percentages based on the total alloy weight, 11 to 18 chromium, 16 to 28 cobalt, 1.5 to 7.0 molybdenum, 0 to 6.5 tungsten, 0 to 1.0 niobium, 1.0 to 2.5 aluminum, 2.0 to 6.0 titanium, 0 to 2.0 tantalum, 0 to 4.0 iron, 0 to 0.5 hafnium, 0.01 to 0.2 carbon, 0.001 to 0.02 boron, 0.001 to 0.1 zirconium, nickel, and impurities. Certain non-limiting embodiments of the nickel-based alloys of this embodiment include 16 to 19 weight percent cobalt. In certain non-limiting embodiments, the nickel-based alloys of this embodiment include a total concentration of aluminum and titanium of 7.0 weight percent or less based on the total alloy weight. In certain non-limiting embodiments, the nickel-based alloys of this embodiment have an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5.

[0037]

[0046] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, in weight percentages based on the total alloy weight, 11 to 18 chromium, 16 to 28 cobalt, 1.5 to 7.0 molybdenum, 0 to 6.5 tungsten, 0 to 1.0 niobium, 1.0 to 2.5 aluminum, 2.0 to 6.0 titanium, 0 to 2.0 tantalum, 0 to 4.0 iron, 0 to 0.5 hafnium, 0.01 to 0.2 carbon, 0.001 to 0.02 boron, 0.001 to 0.1 zirconium, nickel, and impurities. Certain non-limiting embodiments of the nickel-based alloys of this embodiment include 16 to 19 weight percent cobalt. In certain non-limiting embodiments, the nickel-based alloys of this embodiment have an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5.

[0038]

[0047] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 11 to 18 chromium, 16 to 28 cobalt, 1.5 to 7.0 molybdenum, 0 to 6.5 tungsten, 0 to 1.0 niobium, 1.0 to 2.5 aluminum, 2.0 to 6.0 titanium, 0 to 2.0 tantalum, 0 to 4.0 iron, 0 to 0.5 hafnium, 0.01 to 0.2 carbon, 0.001 to 0.02 boron, 0.001 to 0.1 zirconium, nickel, and impurities. Certain non-limiting embodiments of the nickel-based alloys of this embodiment include 16 to 19 weight percent cobalt. In certain non-limiting embodiments, the nickel-based alloys of this embodiment have an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5.

[0039]

[0048] Additional non-limiting embodiments of the high-temperature nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 11 to 16 chromium, 16 to 28 cobalt, 1.5 to 7.0 molybdenum, 0 to 6.5 tungsten, 0 to 1.0 niobium, 1.0 to 2.5 aluminum, 2.0 to 6.0 titanium, 0 to 2.0 tantalum, 0 to 4.0 iron, 0 to 0.5 hafnium, 0.01 to 0.2 carbon, 0.001 to 0.015 boron, 0.001 to 0.1 zirconium, at least 36 nickel, and impurities, and the nickel-based alloy includes a total concentration of aluminum, niobium, and titanium that is 5.0 to 7.0 weight percent. Certain non-limiting embodiments of the nickel-based alloys of this embodiment include 16 to 19 weight percent cobalt. In certain non-limiting embodiments, the nickel-based alloys of this embodiment have an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5.

[0040]

[0049] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, by weight percentages based on the total alloy weight, 11-16 chromium, 16-28 cobalt, 1.5-7.0 molybdenum, 0-6.5 tungsten, 0-1.0 niobium, 1.0-2.5 aluminum, 2.0-6.0 titanium, 0-2.0 tantalum, 0-4.0 iron, 0-0.5 hafnium, 0.01-0.2 carbon, 0.001-0.015 boron, 0.001-0.1 zirconium, at least 36 nickel, and impurities, and the nickel-based alloy contains a total concentration of aluminum, niobium, and titanium that is 5.0-7.0 weight percent. Certain non-limiting embodiments of the nickel-based alloy of this embodiment contain 16-19 weight percent cobalt. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5.

[0041]

[0050] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentages based on the total alloy weight, 11-16 chromium, 16-28 cobalt, 1.5-7.0 molybdenum, 0-6.5 tungsten, 0-1.0 niobium, 1.0-2.5 aluminum, 2.0-6.0 titanium, 0-2.0 tantalum, 0-4.0 iron, 0-0.5 hafnium, 0.01-0.2 carbon, 0.001-0.015 boron, 0.001-0.1 zirconium, at least 36 nickel, and impurities, and the total concentration of aluminum, niobium, and titanium is 5.0-7.0 weight percent. Certain non-limiting embodiments of the nickel-based alloy of this embodiment contain 16-19 weight percent cobalt. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5.

[0042]

[0051] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications include, by weight percentage based on the total alloy weight, 11 to 18 chromium, 24 to 28 cobalt, 1.5 to 7.0 molybdenum, 2.0 to 6.0 tungsten, 0 to 1.0 niobium, 1.0 to 2.5 aluminum, 2.0 to 6.0 titanium, 0 to 2.0 tantalum, 0 to 4.0 iron, 0 to 0.5 hafnium, 0.01 to 0.2 carbon, 0.001 to 0.02 boron, 0.001 to 0.1 zirconium, nickel, and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5.

[0043]

[0052] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, by weight percentage based on the total alloy weight, 11 to 18 chromium, 24 to 28 cobalt, 1.5 to 7.0 molybdenum, 2.0 to 6.0 tungsten, 0 to 1.0 niobium, 1.0 to 2.5 aluminum, 2.0 to 6.0 titanium, 0 to 2.0 tantalum, 0 to 4.0 iron, 0 to 0.5 hafnium, 0.01 to 0.2 carbon, 0.001 to 0.02 boron, 0.001 to 0.1 zirconium, nickel, and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5.

[0044]

[0053] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 11 to 18 chromium, 24 to 28 cobalt, 1.5 to 7.0 molybdenum, 2.0 to 6.0 tungsten, 0 to 1.0 niobium, 1.0 to 2.5 aluminum, 2.0 to 6.0 titanium, 0 to 2.0 tantalum, 0 to 4.0 iron, 0 to 0.5 hafnium, 0.01 to 0.2 carbon, 0.001 to 0.02 boron, 0.001 to 0.1 zirconium, nickel, and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Aleq ) has.

[0045]

[0054] Additional non - limiting embodiments of the nickel - based alloys according to the present disclosure suitable for high - temperature applications include, by weight percentage based on the total alloy weight, 14 - 16 chromium, 24 - 27 cobalt, 1.5 - 7.0 molybdenum, 0 - 6.5 tungsten, 0 - 1.0 niobium, 1.7 - 2.0 aluminum, 3.0 - 6.0 titanium, 0 - 2.0 tantalum, 0 - 4.0 iron, 0 - 0.5 hafnium, 0.01 - 0.2 carbon, 0.001 - 0.015 boron, 0.001 - 0.1 zirconium, at least 46 nickel, and impurities, wherein the total concentration of aluminum, niobium, and titanium is 5.0 - 7.0 weight percent. In certain non - limiting embodiments, the nickel - based alloy of this embodiment has an aluminum equivalent number (Al eq ) has.

[0046]

[0055] Additional non - limiting embodiments of the nickel - based alloys according to the present disclosure suitable for high - temperature applications consist essentially of, by weight percentage based on the total alloy weight, 14 - 16 chromium, 24 - 27 cobalt, 1.5 - 7.0 molybdenum, 0 - 6.5 tungsten, 0 - 1.0 niobium, 1.7 - 2.0 aluminum, 3.0 - 6.0 titanium, 0 - 2.0 tantalum, 0 - 4.0 iron, 0 - 0.5 hafnium, 0.01 - 0.2 carbon, 0.001 - 0.015 boron, 0.001 - 0.1 zirconium, at least 46 nickel, and impurities, wherein the total concentration of aluminum, niobium, and titanium is 5.0 - 7.0 weight percent. In certain non - limiting embodiments, the nickel - based alloy of this embodiment has an aluminum equivalent number (Al eq ) has.

[0047]

[0056] Additional non-limiting embodiments of nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 14-16 chromium, 24-27 cobalt, 1.5-7.0 molybdenum, 0-6.5 tungsten, 0-1.0 niobium, 1.7-2.0 aluminum, 3.0-6.0 titanium, 0-2.0 tantalum, 0-4.0 iron, 0-0.5 hafnium, 0.01-0.2 carbon, 0.001-0.015 boron, 0.001-0.1 zirconium, at least 46 nickel, and impurities, with the total concentration of aluminum, niobium, and titanium being 5.0-7.0 weight percent. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5.

[0048]

[0057] Additional non-limiting embodiments of nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 13-17 chromium; 16-25 cobalt; 1.5-7.0 molybdenum; 0-6.5 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 36 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0049]

[0058] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, by weight percentages based on the total alloy weight, 13 to 17 chromium; 16 to 25 cobalt; 1.5 to 7.0 molybdenum; 0 to 6.5 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.015 boron; 0.001 to 0.1 zirconium; optionally trace elements; at least 36 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0050]

[0059] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentages based on the total alloy weight, 13 to 17 chromium; 16 to 25 cobalt; 1.5 to 7.0 molybdenum; 0 to 6.5 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.015 boron; 0.001 to 0.1 zirconium; optionally trace elements; at least 36 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0051]

[0060] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications include, in weight percentages based on the total alloy weight, 13-17 chromium; 16-19 cobalt; 1.5-7.0 molybdenum; 2.0-5.0 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0052]

[0061] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, in weight percentages based on the total alloy weight, 13-17 chromium; 16-19 cobalt; 1.5-7.0 molybdenum; 2.0-5.0 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0053]

[0062] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 13-17 chromium; 16-19 cobalt; 1.5-7.0 molybdenum; 2.0-5.0 tungsten; 0-1.0 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0054]

[0063] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 14-17 chromium; 19-25 cobalt; 2.0-4.0 molybdenum; 0-6.5 tungsten; 0-0.8 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0055]

[0064] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, by weight percentages based on the total alloy weight, 14-17 chromium; 19-25 cobalt; 2.0-4.0 molybdenum; 0-6.5 tungsten; 0-0.8 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0056]

[0065] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentages based on the total alloy weight, 14-17 chromium; 19-25 cobalt; 2.0-4.0 molybdenum; 0-6.5 tungsten; 0-0.8 niobium; 1.0-2.5 aluminum; 3.0-6.0 titanium; 0-2.0 tantalum; 0-3.0 iron; 0-0.5 hafnium; 0.01-0.2 carbon; 0.001-0.015 boron; 0.001-0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0057]

[0066] Additional non-limiting embodiments of nickel-based alloys according to the present disclosure suitable for high-temperature applications include, by weight percentage based on the total alloy weight, 14 to 17 chromium; 16 to 19 cobalt; 2.0 to 4.0 molybdenum; 2.0 to 5.0 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; greater than 0 to 2.0 tantalum; 1.0 to 3.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.015 boron; 0.001 to 0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0058]

[0067] Additional non-limiting embodiments of nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, by weight percentage based on the total alloy weight, 14 to 17 chromium; 16 to 19 cobalt; 2.0 to 4.0 molybdenum; 2.0 to 5.0 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; greater than 0 to 2.0 tantalum; 1.0 to 3.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.015 boron; 0.001 to 0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0059]

[0068] Additional non-limiting embodiments of nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 14 to 17 chromium; 16 to 19 cobalt; 2.0 to 4.0 molybdenum; 2.0 to 5.0 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; greater than 0 to 2.0 tantalum; 1.0 to 3.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.015 boron; 0.001 to 0.1 zirconium; optionally trace elements; at least 46 nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0060]

[0069] Additional non-limiting embodiments of nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 15 to 17 chromium; 22 to 26 cobalt; 2.0 to 4.0 molybdenum; 0 to 2.0 tungsten; 0 to 1.0 niobium; 1.0 to 4.0 aluminum; 1.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0 to 0.2 carbon; 0 to 0.02 boron; 0 to 0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0061]

[0070] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, by weight percentage based on the total alloy weight, 15-17 chromium; 22-26 cobalt; 2.0-4.0 molybdenum; 0-2.0 tungsten; 0-1.0 niobium; 1.0-4.0 aluminum; 1.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0-0.2 carbon; 0-0.02 boron; 0-0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0062]

[0071] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 15-17 chromium; 22-26 cobalt; 2.0-4.0 molybdenum; 0-2.0 tungsten; 0-1.0 niobium; 1.0-4.0 aluminum; 1.0-6.0 titanium; 0-2.0 tantalum; 0-4.0 iron; 0-0.5 hafnium; 0-0.2 carbon; 0-0.02 boron; 0-0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6-4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment contains a total concentration of aluminum, niobium, and titanium of 5.0-7.0 weight percent based on the total alloy weight.

[0063]

[0072] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications include, in weight percentages based on the total alloy weight, 14 to 17 chromium; 15 to 18 cobalt; 2.0 to 4.0 molybdenum; 1.0 to 4.0 tungsten; 0 to 1.0 niobium; 1.0 to 3.0 aluminum; 2.0 to 4.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0 to 0.2 carbon; 0 to 0.02 boron; 0 to 0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0064]

[0073] Additional non-limiting embodiments of the nickel-based alloys according to the present disclosure suitable for high-temperature applications consist essentially of, in weight percentages based on the total alloy weight, 14 to 17 chromium; 15 to 18 cobalt; 2.0 to 4.0 molybdenum; 1.0 to 4.0 tungsten; 0 to 1.0 niobium; 1.0 to 3.0 aluminum; 2.0 to 4.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0 to 0.2 carbon; 0 to 0.02 boron; 0 to 0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0065]

[0074] Additional non-limiting embodiments of nickel-based alloys according to the present disclosure suitable for high-temperature applications consist of, by weight percentage based on the total alloy weight, 14 to 17 chromium; 15 to 18 cobalt; 2.0 to 4.0 molybdenum; 1.0 to 4.0 tungsten; 0 to 1.0 niobium; 1.0 to 3.0 aluminum; 2.0 to 4.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0 to 0.2 carbon; 0 to 0.02 boron; 0 to 0.1 zirconium; nickel; and impurities. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5. In certain non-limiting embodiments, the nickel-based alloy of this embodiment includes a total concentration of aluminum, niobium, and titanium of 5.0 to 7.0 weight percent based on the total alloy weight.

[0066]

[0075] Suitable minimum levels of chromium are included in embodiments of the alloys of the present invention to impart acceptable oxidation and corrosion resistance. However, excessive levels of chromium combined with cobalt can lead to matrix instability and the possibility of sigma phase formation. In certain embodiments of the alloys according to the present disclosure, the chromium content ranges from 11 to 18 weight percent. For example, in some such alloys, it may be within a narrower range of 11 to 16 weight percent, 11 to 15 weight percent, 11 to 14 weight percent, 12 to 16 weight percent, 12 to 15 weight percent, 12 to 14 weight percent, 13 to 18 weight percent, 13 to 17 weight percent, 14 to 17 weight percent, 15 to 17 weight percent, or 14 to 16 weight percent. The chromium content is 11 to 16 weight percent in certain other embodiments of the alloys herein and 14 to 16 weight percent in some embodiments.

[0067]

[0076] Cobalt reduces gamma prime solvus. Cobalt also reduces the stacking fault energy and as a result can increase the number of annealing twins. However, an excessive level of chromium in combination with cobalt can cause the precipitation of a harmful second phase such as the sigma phase, which can lead to a degradation of mechanical properties. To balance these results, in certain embodiments of the alloys according to the present disclosure, the cobalt content ranges from 15 to 28 weight percent. For example, in some of such alloys, it may be in a narrower range of 16 to 28 weight percent, 15 to 18 weight percent, 16 to 27 weight percent, 16 to 26 weight percent, 17 to 27 weight percent, 17 to 26 weight percent, 18 to 26 weight percent, 16 to 25 weight percent, 19 to 25 weight percent, 20 to 25 weight percent, 22 to 26 weight percent, or 19 to 24 weight percent. In certain other embodiments, the cobalt content ranges from 16 to 19 weight percent. For example, in some of such alloys, it may be within a narrower range of 16 to 18 weight percent, 16 to 17 weight percent, 17 to 18 weight percent, 17 to 19 weight percent, or 18 to 19 weight percent. The cobalt content is 24 to 28 weight percent in certain other embodiments of the alloys herein, and in some embodiments is in a narrower range of 24 to 27 weight percent, 24 to 26 weight percent, 25 to 28 weight percent, 25 to 27 weight percent, 26 to 28 weight percent, or 26 to 27 weight percent.

[0068]

[0077] Molybdenum is mainly distributed in the matrix and can strengthen the matrix by a solid solution mechanism. However, excessive molybdenum may lead to the development of excessive levels of TCP phases during use. The molybdenum content in certain alloys according to the present disclosure is from 1.5 to 7.0 weight percent, and for example, in some of such alloys, it may be within a narrower range of 2.0 to 6.0 weight percent, 2.0 to 5.5 weight percent, 2.0 to 5.0 weight percent, 2.0 to 4.0 weight percent, 3.0 to 5.0 weight percent, 3.0 to 6.0 weight percent, 4.0 to 6.0 weight percent, 4.0 to 5.0 weight percent, 4.5 to 5.5 weight percent, 3.0 to 7.0 weight percent, or 4.0 to 7.0 weight percent. A molybdenum content lower than 2.0 weight percent is unlikely to result in a desirable combination of creep resistance, workability, and weldability.

[0069]

[0078] Tungsten is mainly distributed in the gamma matrix phase. The addition of tungsten and / or molybdenum can increase the lattice parameter of the matrix and minimize (or even make it negative) the lattice misfit, thereby reducing the gamma prime coarsening rate and strengthening the matrix by the solid solution mechanism. This increases the creep resistance. However, excessive tungsten leads to the development of excessive levels of TCP phases during use, can increase the density, and may cause the formation of less favorable primary and secondary carbides when added in very large amounts. Tungsten may be present in certain alloys according to the present disclosure at a concentration of 0 to 6.5 weight percent, for example, in some of such alloys, in a narrower range of greater than 0 to 6.5 weight percent, 0 to 5.0 weight percent, greater than 0 to 5.0 weight percent, 0 to 0.5 weight percent, greater than 0 to 0.5 weight percent, 0 to 2.0 weight percent, greater than 0 to 2.0 weight percent, 1.0 to 6.5 weight percent, 1.0 to 4.0 weight percent, 1.5 to 6.5 weight percent, 1.5 to 5.0 weight percent, 2.5 to 6.5 weight percent, 2.5 to 5.0 weight percent, 3.5 to 5.0 weight percent, 4.0 to 6.0 weight percent, or 5.0 to 6.5 weight percent. In various embodiments of the alloys herein, the tungsten content is 2.0 to 6.0 weight percent, for example, in some of such alloys, in a narrower range of 2.0 to 5.0 weight percent, 2.0 to 4.5 weight percent, 3.0 to 5.0 weight percent, 4.0 to 6.0 weight percent, 2.0 to 4.0 weight percent, or 5.0 to 6.0 weight percent.

[0070]

[0079] As used herein, an alloy composition described as containing an element at a concentration “from 0 to”, “from 0 to a maximum”, or simply “up to” a specified weight percentage upper limit means that in certain embodiments of the alloy, the element may be absent or may be present at a non-zero concentration and up to the specified weight percentage upper limit. Applicants reserve the right to amend the claims herein with respect to any element that may be absent in certain other embodiments of the alloys according to the present disclosure to affirmatively recite a non-zero weight percentage lower limit (e.g., “greater than 0”).

[0071]

[0080] In various non-limiting embodiments of the nickel-based alloys according to the present disclosure, the concentrations of molybdenum and tungsten in the alloy satisfy the limitation of 3% < [Mo] + 0.52×[W] < 8% (wherein [Mo] and [W] are the weight percentage concentrations of molybdenum and tungsten in the alloy, respectively). In certain non-limiting embodiments of the nickel-based alloys according to the present disclosure, the concentrations of molybdenum and tungsten in the alloy satisfy the limitation of 3% < [Mo] + 0.52×[W] < 5% (wherein [Mo] and [W] are the weight percentage concentrations of molybdenum and tungsten in the alloy, respectively).

[0072]

[0081] Niobium is preferentially distributed to the gamma prime phase, increasing the creep resistance and high temperature strength by raising the activation energy for dislocation movement in the gamma prime phase. Embodiments of the alloys according to the present disclosure may include up to 2.0 weight percent niobium. Niobium is known to strongly segregate during solidification, and for this reason, in various non-limiting embodiments of the alloys of the present invention, niobium is absent or its content is kept to a minimum. Preferably, the niobium content is 1.5 weight percent, 1.0 weight percent, 0.8 weight percent, or 0.1 weight percent or less. In certain embodiments, niobium contents above 0.2 weight percent, 1.0 weight percent, or 1.5 weight percent may be used to offset some amount of titanium, aluminum, cobalt, molybdenum, and / or tungsten. In various non-limiting embodiments, niobium may be present in certain alloys according to the present disclosure at a concentration of 0 to 2.0 weight percent, such as greater than 0 to 2.0 weight percent, or 0.2 to 1.0 weight percent.

[0073]

[0082] The ratio among aluminum, titanium, niobium, and tantalum controls the solvus temperature of the gamma prime phase in addition to the total content of those elements. This is particularly important for alloys used in structural applications such as turbine engine cases. In increasing the solvus temperature, titanium in the atomic base state is more effective than aluminum. However, excessive levels of titanium can result in the formation of the eta phase instead of the gamma prime phase. Turbine engine cases are currently manufactured by a process involving ring rolling, which conventionally limits the alloy to a gamma prime solvus temperature of about 1038 - 1093 °C (1900 - 2000 °F) in order to maintain sufficient hot workability and allow large plastic strains during forming. At aluminum concentrations above 3.5 weight percent, the solvus temperature of the alloy is too high or the amount of gamma prime is too great to support the acceptable ring rolling ability and / or weldability for certain structural applications such as for turbine engine cases. Aluminum may be present in a concentration of 1.0 - 4.0 weight percent in certain alloys according to the present disclosure, for example, in some alloy embodiments, within a narrower range of 1.0 - 3.0 weight percent, 1.0 - 2.5 weight percent, 1.25 - 2.0 weight percent, 1.25 - 1.9 weight percent, 1.3 - 1.8 weight percent, 1.5 - 2.5 weight percent, 1.0 - 2.0 weight percent, or 1.5 - 2.0 weight percent. In various embodiments of the alloys herein, the aluminum content is 1.7 - 2.0 weight percent.

[0074]

[0083] Titanium strengthens the gamma prime phase, increases the resistance of the gamma prime phase to shear, and raises the solvus temperature and the coherency of the gamma prime phase. These factors strongly influence the strength and creep resistance of the alloy. Titanium is present in certain alloys according to the present disclosure at a concentration of 1.0 to 6.0 weight percent, for example, in some of the alloy embodiments, in a narrower range of 2.0 to 6.0 weight percent, 2.0 to 5.0 weight percent, 2.0 to 4.5 weight percent, 2.0 to 4.0 weight percent, 2.0 to 3.5 weight percent, 2.0 to 3.0 weight percent, 2.5 to 3.5 weight percent, 3.0 to 5.5 weight percent, 3.0 to 4.0 weight percent, 4.5 to 5.5 weight percent, or 3.0 to 6.0 weight percent. In various embodiments of the alloys herein, the titanium content is 3.0 to 4.5 weight percent.

[0075]

[0084] Tantalum can be used to control the solvus temperature of the gamma prime phase and its coherency with the matrix. It is also a strong carbide stabilizer, can be beneficial for oxidation resistance, and can improve the creep resistance of the gamma matrix at high temperatures. The alloys according to the present disclosure may contain up to 2.0 weight percent of tantalum, up to 0.5 weight percent of tantalum, or up to 0.2 weight percent of tantalum. In various non-limiting embodiments of the alloys according to the present disclosure, tantalum is absent. In various embodiments, the tantalum content is greater than 0 to 2.0 weight percent, greater than 0 to 1.0 weight percent, greater than 0 to 0.8 weight percent, 0.2 to 2.0 weight percent, 0.6 to 2.0 weight percent, or 1.0 to 2.0 weight percent.

[0076]

[0085] Increasing the iron content increases the types and amounts of reversion that can exist in the alloy, which helps reduce the production cost of the alloy. The alloys according to the present disclosure may contain up to 4.0 weight percent of iron, or greater than 0 to 4.0 weight percent of iron. In various non-limiting embodiments of the alloys according to the present disclosure, iron is absent. In other alloy embodiments, the iron content may be up to 3.0 weight percent, up to 2.0 weight percent, or up to 1.0 weight percent. In various embodiments of the alloys herein, the iron content is greater than 0 to 3.0 weight percent, or 1.0 to 3.0 weight percent.

[0077]

[0086] Hafnium is a strong carbide stabilizer and improves creep resistance at elevated temperatures at the levels according to the present disclosure. Similar to zirconium, hafnium may also have an adverse effect on weldability due to its strong segregation during solidification. The alloys according to the present disclosure may contain up to 0.5 weight percent of hafnium. In various non-limiting embodiments of the alloys according to the present disclosure, hafnium is absent. In other alloy embodiments, hafnium may be present at concentrations from greater than 0 up to 0.5 weight percent, or from greater than 0 up to 0.25 weight percent.

[0078]

[0087] The alloys according to the present disclosure contain up to 0.2 weight percent of carbon, greater than 0 to 0.2 weight percent of carbon, or 0.01 weight percent to 0.2 weight percent of carbon. As the carbon concentration increases, the average grain size can become smaller and the grain size distribution can become narrower, but there is also a risk of reducing forgeability and low cycle fatigue properties due to the formation of carbonitride stringers. In certain non-limiting embodiments of the alloys according to the present disclosure, the carbon content is from at least 0.02 weight percent up to 0.2 weight percent, or from at least 0.03 weight percent up to 0.2 weight percent. A carbon concentration of about 0.03 weight percent may generate internal oxidation damage that forms and results from decomposition during high temperature exposure M 23The presence of C6 carbide has been observed to be minimized. The carbon content is 0.02 - 0.1 percent in certain preferred embodiments, or in some embodiments, 0.03 - 0.06 weight percent or 0.025 - 0.05 weight percent in order to improve hot workability and reduce the risk of harmful melting structures. The carbon content within the aforementioned ranges balances the ability to generate fine grain sizes for good high cycle fatigue and fatigue crack growth resistance while ensuring good low cycle fatigue and ultrasonic inspectability.

[0079]

[0088] The grain boundary elements zirconium and boron may be present in embodiments of the alloys according to the present disclosure. Zirconium may act as a scavenger for oxygen and sulfur in the alloy. However, zirconium may have an adverse effect on weldability and its maximum level should be controlled. In certain embodiments of the alloys according to the present disclosure, the zirconium content is 0 - 0.1 weight percent, 0 up to 0.1 weight percent, or 0.001 weight percent - 0.1 weight percent. In various embodiments, the zirconium content of the alloys herein is 0.001 - 0.05 weight percent, 0.001 - 0.04 weight percent, or 0.001 - 0.03 weight percent. Boron can improve grain boundary cohesion and hot ductility. However, especially when a high solution treatment temperature is required during alloy processing, boron may promote the formation of grain boundary films. Also, high boron concentrations are known to reduce the ability of alloys produced by ingot metallurgy practices due to an increased risk of harmful melting structures. In certain embodiments of the alloys according to the present disclosure, the boron content is 0 - 0.02 weight percent, 0 up to 0.02 weight percent, or 0.001 weight percent - 0.02 weight percent. In various embodiments, the boron content of the alloys herein is 0.001 - 0.015 weight percent, 0.001 - 0.1 weight percent, 0.02 - 0.04 weight percent, or 0.002 - 0.01 weight percent.

[0080]

[0089] In various embodiments of the alloys according to the present disclosure, the balance of the alloy comprises nickel, trace elements, and impurities. Certain alloy embodiments comprise at least 33 weight percent nickel. Certain alloy embodiments according to the present disclosure comprise at least 36 weight percent nickel, while other embodiments comprise at least 46 weight percent nickel, or at least 48 weight percent nickel. Impurities may also be present, for example, included in the starting materials or as a result of the processing of the alloy.

[0081]

[0090] Various non-limiting embodiments of the alloys according to the present disclosure include one or more trace elements. As used herein, a "trace element" is an element that may be present at a concentration of less than 5 weight percent, or in some cases less than 2 weight percent or less than 1 weight percent, and that imparts some additional advantageous feature or property to the alloy or does not significantly affect the important properties or performance of the alloy. Trace elements may be absent in various embodiments of the alloys herein. Optionally, examples of trace elements that may be present in non-limiting embodiments of the alloys according to the present disclosure and the corresponding maximum contents are manganese up to a maximum of 5.0 weight percent (e.g., up to a maximum of 4.0 weight percent, up to a maximum of 3.0 weight percent, up to a maximum of 2.0 weight percent, or greater than 0 to 5.0 weight percent); magnesium up to a maximum of 0.1 weight percent (e.g., up to a maximum of 0.05 weight percent, up to a maximum of 0.001 weight percent, up to a maximum of 0.05 weight percent, greater than 0 to 0.1 weight percent, greater than 0 to 0.05 weight percent, or 0.0001 to 0.1 weight percent); silicon up to a maximum of 1.0 weight percent (e.g., up to a maximum of 0.8 weight percent, up to a maximum of 0.6 weight percent, up to a maximum of 0.5 weight percent, or greater than 0 to 1.0 weight percent); copper up to a maximum of 5.0 weight percent (e.g., up to a maximum of 4.0 weight percent, up to a maximum of 3.0 weight percent, up to a maximum of 2.0 weight percent, or greater than 0 to 5.0 weight percent); vanadium up to a maximum of 2 weight percent (e.g., up to a maximum of 1.5 weight percent, up to a maximum of 1.0 weight percent, up to a maximum of 0.5 weight percent, or greater than 0 to 2 weight percent); and / or rare earth metals, scandium, and yttrium up to a maximum of 0.2 weight percent (e.g., up to a maximum of 0.1 weight percent, up to a maximum of 0.05 weight percent, up to a maximum of 0.03 weight percent, or greater than 0 to 0.2 weight percent). Magnesium can enhance the cleanliness and hot workability of the melt.

[0082]

[0091] Examples of elements that may be present as impurities in the alloys according to the present disclosure include, for example and without limitation, sodium, magnesium, potassium, calcium, antimony, tin, arsenic, lead, phosphorus, sulfur, fluorine, sulfur, chlorine, oxygen, nitrogen, zinc, and gallium. These impurity elements, when present, typically are present at individual concentrations of about 0.1 weight percent or less, and the total content of such impurities typically is 5.0 weight percent or less.

[0083]

[0092] Increasing the content of the gamma prime phase can increase the microstructural stability of the alloy, which is a significantly important feature in the alloys according to the present disclosure. However, increasing the gamma prime content above a certain level may reduce the alloy forgeability to an unacceptable low level. The gamma prime content can be adjusted, for example, by selecting a suitable total content of aluminum, titanium, tantalum, and niobium in the alloy. For example, nickel-based alloys according to the present disclosure can include a total concentration of aluminum, niobium, and titanium in the range of 5.0 to 7.0 weight percent, such as 5.0 to 6.0 weight percent or 6.0 to 7.0 weight percent. In various non-limiting embodiments, nickel-based alloys according to the present disclosure can include a total concentration of aluminum and titanium of 7.0 weight percent or less. For example, nickel-based alloys according to the present disclosure can include a total concentration of aluminum and titanium in the range of 5.0 to 7.0 weight percent, such as 5.0 to 6.0 weight percent or 6.0 to 7.0 weight percent. In certain non-limiting embodiments, nickel-based alloys according to the present disclosure have an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5, such as 3.6 to 4.2 or 4.0 to 4.5.

[0084]

[0093] The chemical properties of the gamma prime phase can also be important in the alloys of the present invention. For example, changing the chemical properties of the gamma prime can alter the lattice parameters of the phase, thereby affecting gamma prime stability. The titanium / aluminum atomic ratio can affect the characteristics of the gamma prime phase. Higher titanium levels are generally beneficial for mechanical properties, and higher aluminum levels can promote alloy stability. However, a higher titanium / aluminum atomic ratio can increase eta phase formation. To balance the effects of titanium and aluminum on the gamma prime phase in the alloys of the present invention, in various embodiments, the titanium / aluminum atomic ratio corresponds to a titanium / aluminum weight percentage ratio of 1.2 to 4.0, and in some embodiments, the titanium / aluminum weight percentage ratio is 1.5 to 4.0, 2.0 to 4.0, 2.5 to 4.0, 1.5 to 3.0, 1.5 to 2.4, 1.3 to 2.4, 1.7 to 2.2, 3.0 to 4.0, or 1.0 to 2.0.

[0085]

[0094] The addition of niobium can also affect the chemical properties of the gamma prime. Niobium has a tendency to partition into the gamma prime phase, increasing the gamma prime phase fraction and promoting gamma prime formation by reducing the solubility of aluminum in the matrix. Niobium also increases the gamma prime inverse solvus boundary energy, subsequently improving the creep and tensile properties of the alloy. However, higher niobium contents combined with high titanium contents may increase the tendency to form the eta phase or other detrimental phases containing niobium and titanium.

[0086]

[0095] Similarly, the addition of tantalum can affect the chemical properties of gamma prime. Tantalum has a tendency to partition into the gamma prime phase, promoting gamma prime formation by increasing the gamma prime phase fraction and reducing the solubility of aluminum in the matrix. Tantalum also increases the gamma prime inverse coherency boundary energy, which can subsequently improve the creep and tensile properties of the alloy. However, higher tantalum contents combined with high titanium contents may increase the tendency to form the eta phase or other phases containing titanium and tantalum.

[0087]

[0096] The inventors have observed that providing a total concentration of aluminum, niobium, tantalum, and titanium within certain ranges in the alloys according to the present disclosure can provide a particularly advantageous combination of workability and strength at elevated temperatures. In certain non-limiting embodiments, the nickel-based alloy of this embodiment has an aluminum equivalent number (Al eq ) in the range of 3.6 to 4.5, for example, 3.6 to 4.2 or 4.0 to 4.5.

[0088]

[0097] For the alloys according to the present disclosure, the titanium equivalent / aluminum equivalent ratio (Ti eq / Al eq ) can be calculated by the following equation. Ti eq / Al eq =([Ti] + 1.07×[Nb] + 0.54×[Ta]) / ([Al] + 0.56×[Ti] + 0.3×[Nb] + 0.15×[Ta]) Wherein, [Ti], [Nb], [Ta], and [Al] are the weight percentage contents of the elements in the aforementioned alloy. It has been observed that the value of the Ti eq / Al eq ratio can be used to track the relative stability of the gamma prime phase, resistance to shear, and lattice parameters among the chemical properties of the alloy. In various embodiments of the nickel-based alloys according to the present disclosure, Ti eq / Al eqis from 0.9 to 1.25, for example, from 0.9 to 1.0 or from 1.0 to 1.25, etc.

[0089]

[0098] Certain non-limiting embodiments of the nickel-based alloys according to the present disclosure can be solution-treated and / or can be age-treated. For example, the nickel-based alloy can be solution-treated at a temperature in the range of 982 °C (1800 °F) to 1176 °C (2150 °F) for up to 168 hours, for example, from 1 hour to 24 hours or from 4 hours to 12 hours, etc. In various non-limiting embodiments, the nickel-based alloy can be age-treated in one or multiple steps at a temperature in the range of 760 °C (1400 °F) to 982 °C (1800 °F) for up to 72 hours, for example, from 1 to 12 hours, etc. The parameters of the age treatment can be selected based on the desired properties of the nickel-based alloy after heat treatment without undue experimentation.

[0090]

[0099] As understood in the art, "creep" refers to time-dependent strain that occurs under a continuous stress below the yield strength of a material, for example, at elevated temperatures under load. As used herein in relation to creep properties, "elevated temperature" refers to a temperature above 93.3 °C (200 °F). "Stress rupture" is understood to be the time at which a metallic article breaks when subjected to a given sustained load at a given temperature. "Creep strength", also known as "creep limit", is a measure of the resistance of a material to creep. It may also be described as the stress under specific conditions that results in a specific creep rate. In other words, creep strength may be considered as the combination of stress, temperature, and time required to reach a specific percentage of creep or rupture. Stress rupture for an alloy article generally represents its creep strength. A higher stress rupture value indicates a higher creep strength for the alloy article. Embodiments of the nickel-based alloys according to the present disclosure may have enhanced stress rupture at 816 °C (1500 °F).

[0091]

[0100] Certain non-limiting embodiments of nickel-based alloys according to the present disclosure may exhibit a yield strength in the aged state of at least 827 MPa (120 ksi) at room temperature (e.g., 22°C + / - 1.1°C (72°F + / - 2°F)), such as at least 862 MPa (125 ksi), at least 896 MPa (130 ksi), at least 931 MPa (135 ksi), at least 965 MPa (140 ksi), or at least 1000 MPa (145 ksi) at room temperature. Tensile properties at room temperature can be determined in accordance with ASTM E8 / E8M-16.

[0092]

[0101] Certain non-limiting embodiments of nickel-based alloys according to the present disclosure may exhibit a yield strength in the aged state of at least 621 MPa (90 ksi), such as at least 655 MPa (95 ksi), at least 689 MPa (100 ksi), or at least 724 MPa (105 ksi) at 816°C (1500°F). The yield strength at 816°C (1500°F) can be measured in accordance with ASTM E21-20.

[0093]

[0102] Certain non-limiting embodiments of nickel-based alloys according to the present disclosure may exhibit a maximum tensile strength in the aged state of at least 1241 MPa (180 ksi), such as at least 1310 MPa (190 ksi), at least 1344 MPa (195 ksi), at least 1378 MPa (200 ksi), or at least 1413.43 MPa (205 ksi). The maximum tensile strength can be measured in accordance with ASTM E8 / E8M-22.

[0094]

[0103] Certain non-limiting embodiments of nickel-based alloys according to the present disclosure may exhibit a maximum tensile strength at 816 °C (1500 °F) in the aged state of at least 621 MPa (90 ksi), such as at least 655 MPa (95 ksi), at least 689 MPa (100 ksi), at least 724 MPa (105 ksi), at least 758 MPa (110 ksi), or at least 827 MPa (120 ksi). The maximum tensile strength at 816 °C (1500 °F) can be measured in accordance with ASTM E21-20.

[0095]

[0104] Certain non-limiting embodiments of nickel-based alloys according to the present disclosure may exhibit a percent elongation at room temperature in the aged state in the range of 15% to 40%, such as 20% to 35%, or 25% to 35%. The elongation at room temperature can be measured in accordance with ASTM E8 / E8M-22.

[0096]

[0105] Certain non-limiting embodiments of nickel-based alloys according to the present disclosure may exhibit a percent elongation at 816 °C (1500 °F) in the range of 5% to 30%, such as 5% to 25%, 10% to 25%, or 15% to 20%. The elongation at 816 °C (1500 °F) can be measured in accordance with ASTM E8 / E8M-22.

[0097]

[0106] The alloys according to the present disclosure can be fabricated using conventional ingot metallurgy techniques known to those skilled in the art that are applied in the production of nickel-based superalloys. Such techniques include, for example, vacuum induction melting, electro slag remelting, vacuum arc remelting, argon oxygen decarburization melting, vacuum oxygen decarburization melting, electric arc furnace, and crucible furnace melting. Other embodiments of the alloys of the present invention may be produced in powder form using processes such as, for example, vacuum melt inert gas atomization (VIGA), electrode induction gas atomization (EIGA), close-coupled gas atomization, cold-wall inert gas atomization, and rotating electrode process atomization. Subsequent ingot billeting may be performed by thermomechanical processing including homogenization, maintaining sufficient heat for deformation, and heat treatment to refine the microstructure. Mechanical working techniques within the thermomechanical processing that may be applied include, but are not limited to, press forging, radial forging, rotary forging, extrusion, pilgering, swaging, rolling, and drawing. The working of the alloys according to the present disclosure may be performed at a temperature above 816 °C (1500 °F) and below the solidus of the material.

[0098]

[0107] Certain non-limiting embodiments of the nickel-based alloys of the present invention can be additively manufactured to produce additively manufactured parts. In contrast to subtractive manufacturing methodologies, additive manufacturing refers to a process of typically building layer upon layer and joining materials to create an object from three-dimensional model data, as defined in ASTM F2792-12a, "Standard Terminology for Additively Manufacturing Technologies". Non-limiting examples of additive manufacturing processes useful in producing products from metallic feedstocks include, among others, for example, DMLS (direct metal laser sintering), SLM (selective laser melting), SLS (selective laser sintering), laser powder bed fusion (LPBF), and EBM (electron beam melting). Any suitable feedstock including powders, wires, and combinations thereof may be used. In some embodiments, the additive manufacturing feedstock is composed of powder.

[0099]

[0108] Additively manufactured parts that may be made using a suitable powder form of the alloys according to the present disclosure may include, but are not limited to, heat exchangers, nose cones, scramjet engine components, vehicle leading edges, heat pipes, re-entry structures, actively or passively cooled controlled surfaces, vehicle outer panels, RAM jet components, rocket motor components, combined cycle motor components, rotating detonation motor components, gasification facility components, chemical processing facility components, and fastening system components.

[0100]

[0109] Non-limiting examples follow.

Example

[0101] Example 1

[0110] Several experimental "button" samples, each having a weight of approximately 500 grams, were prepared, rolled, heat treated, and tested for tensile properties. Table 1 provides the target compositions of the experimental samples labeled W6, W11 - W13, W20 - W22, and W24 - W26, as well as the target composition of a Waspaloy sample, W0, made for comparison purposes. The samples also contained unavoidable impurities. Table 1 also lists the density, the predicted gamma prime volume percent contents at 538 °C (1000 °F) and 816 °C (1500 °F), and the gamma prime solvus temperature, all calculated using JMatPro software version 4 - 1.

[0102]

[0111] Each button was cold rolled to a thickness of approximately 0.38 cm (0.15 inches) and heat treated as follows. During rolling, it was observed that none of the buttons developed cracks. The rolled buttons were solution treated at 1093 °C (2000 °F) for 2 hours and individually water quenched. The solution treated buttons were subjected to a first aging treatment step at 890 °C (1650 °F) for 4 hours, air cooled, and then subjected to a second aging treatment step at 843 °C (1550 °F) for 12 hours and air cooled. The rolled buttons that were solution treated and aged were tested for tensile properties at room temperature according to ASTM E8-16ae1 and at 816 °C (1500 °F) according to ASTM E21-17e1. The properties tested included maximum tensile strength, 0.2% yield strength, elongation, and reduction of area. The results of the tensile tests are reported in Table 2 (tensile test specimens at room temperature) and Table 3 (tensile test specimens at 816 °C (1500 °F)). The heated tensile test specimens were immersed at 816 °C (1500 °F) for 30 minutes prior to the tensile test.

[0103]

[0112] The tensile test specimen of sample W12 tested at 816 °C (1500 °F) had suspect strain for testing and thus yield could not be reported. However, the UTS reported for sample W12 tested at 816 °C (1500 °F) was considered valid and reported. The tensile test specimen for sample W13 tested at 816 °C (1500 °F) jammed in the clevis after testing and broke during its removal, and elongation and reduction of area (RA) could not be obtained for that sample.

[0104]

Table 1

[0105]

Table 2

[0106]

Table 3

[0107] Example 2

[0113] Several 11.34 kg (25 lb.) heats of nickel-base alloys having different chemical properties were melted by vacuum induction melting and poured into tapered pairs of metal molds. The chemical composition of each heat is shown in Table 3. The values in Table 3 are weight percentages on a total weight basis of the alloy. FIG. 1 is a photograph showing the configuration of a pair of VIM molds used to cast a 11.34 kg (25 lb.) heat in this example. FIG. 2 shows the dimensions of the configuration of the VIM mold used to cast a 11.34 kg (25 lb.) heat in this example. FIG. 3 is a photograph showing a representative casting of a 11.34 kg (25 lb.) heat produced in this example. Each heat was homogenized at a higher temperature to even out any possible chemical differences that could have occurred during solidification.

[0108]

Table 4

[0109]

[0114] The respective chemical properties of the heats listed in Table 3 were selected to include alloying elements that adjust the gamma prime content to levels higher than in certain conventional high-temperature nickel-base alloys (e.g., Waspaloy, 718, and GTD222 alloys), ensuring that the gamma prime content is low enough to ensure acceptable workability. The Al of the alloy eqwas controlled. In heats No. P0F00 to No. P0F03, the contents of molybdenum, tungsten, tantalum, and niobium were varied. Molybdenum and tungsten are substitutional elements that can improve high-temperature mechanical properties. Tungsten and molybdenum can also increase the lattice parameter of the matrix phase, and as a result, minimize the lattice mismatch between the gamma prime phase and the matrix phase, which in turn reduces the coarsening rate of the gamma prime phase. However, tantalum and niobium can form carbides, be distributed in the gamma prime precipitates, and improve stress rupture properties. Adding too high a content of tantalum and / or niobium may increase the tendency to form the eta phase (NiTi3) or other harmful secondary phases in the alloy. In heats No. P0F04 and No. P0F05, the contents of aluminum and titanium were reduced, and the contents of molybdenum and tungsten were adjusted to avoid TCP phase formation. To make it more certain that the alloy is ring-rollable and has good workability, the gamma prime solvus was kept below or near 1121 °C (2050 °F).

[0110]

[0115] Chromium was included in the heat to impart oxidation resistance, but was limited so that the alloy microstructure would not become so unstable as to result in the formation of the TCP phase. Cobalt can reduce the stacking fault energy, increase the solid solubility of aluminum and titanium in the matrix, and improve the workability of the alloy. The presence of grain boundary elements including boron and zirconium improved the fatigue crack propagation rate, high-temperature ductility, and weldability of the alloy. The boron and zirconium contents were limited in consideration that an excess of these elements could result in grain boundary film formation at higher temperatures during solution treatment.

[0111]

[0116] M that can form and generate possible internal oxidation damage when decomposing during high-temperature exposure 23The carbon level in the heat was selected to minimize the presence of C6 carbide. For example, it has been observed that controlling the carbon content to 0.040 - 0.05 weight percent can be effective in controlling grain growth by grain boundary pinning during supersolvus solution heat treatment. Increasing the carbon content in the alloy composition can produce a smaller average grain size, but it can also reduce the workability and low cycle fatigue performance of the alloy due to the formation of carbonitride stringers.

[0112]

[0117] Table 4 provides the gamma prime solvus temperature and aluminum equivalent number for the heats listed in Table 3. The gamma prime solvus temperature was measured by differential thermal analysis (DTA) technique. To more reliably ensure sufficient workability, the gamma prime solvus temperature is preferably less than 1121 °C (2050 °F), more preferably less than 1065 °C (1950 °F), so that gamma prime precipitation does not occur on the surface of the material during ring rolling. The gamma prime content of the alloys according to the present disclosure can be affected by suitably adjusting the aluminum equivalent number of the alloy. The aluminum number (Al eq ) for the purposes of the present disclosure is calculated by the following equation. Al eq = [Al] + 0.56[Ti] + 0.3[Nb] + 0.15[Ta] Where [Al], [Ti], [Nb], and [Ta] are the weight percentage concentrations of the respective elements in the alloy. The inventors have determined that alloys according to the present disclosure having an aluminum equivalent number in the range of 3.6 - 4.5 have advantageous workability characteristics and a gamma prime content at elevated temperatures, such as above 649 °C (1200 °F), which can be advantageous in structural components subjected to stress at those elevated temperatures.

[0113]

Table 5

[0114]

[0118] The VIM samples were subjected to forging, followed by super-solvus solution treatment and two-step aging treatment. After the heat treatment, samples were prepared from each heat and subjected to tensile tests and stress rupture tests under various test conditions. As follows, the test conditions are shown in Table 5, and the test results are shown in Tables 6 to 10. Table 6 lists the tensile test results (yield strength, maximum tensile strength, percent elongation (%El), and percent reduction in cross-sectional area (%RA)) evaluated at room temperature. Table 7 lists the tensile test results evaluated at 816.6 °C (1500 °F). Table 8 lists the stress rupture test results evaluated at 816.6 °C (1500 °F) and 275.8 MPa (40 ksi) for some of the heats.

[0115]

Table 6

[0116]

Table 7

[0117]

Table 8

[0118]

Table 9

[0119]

[0119] For some of the 11.34 kg (25 lb.) heats in this Example 2, the yield strength and maximum tensile strength were determined at 760.0 °C (1400 °F) and 871.1 °C (1600 °F). For some of the heats, the elongation and reduction in cross-sectional area were measured at 760.0 °C (1400 °F). The tensile properties measured at 760.0 °C (1400 °F) for some of the 11.34 kg (25 lb.) heats are included in Table 9.

[0120]

Table 10

[0121]

[0120] Figure 4 is a graph of yield strength (ksi) as a function of test temperature (measured at room temperature and at 760.0 °C (1400 °F), 816.6 °C (1500 °F), and 871.1 °C (1600 °F)) for a heat (batch number provided) and also plots the yield strength at various temperatures for commercially available nickel-based alloys Haynes Waspaloy alloy, ATI Waspaloy alloy, and Haynes 282 alloy. Figure 5 is a graph showing the maximum tensile strength (ksi) as a function of test temperature for the heat (batch number provided) fabricated in this Example 1 and also plots the maximum tensile strength at various temperatures for Haynes Waspaloy alloy, ATI Waspaloy alloy, and Haynes 282 alloy (UNS N07208). The alloy is similar to the Waspaloy alloy in forgeability, but at 816.6 °C (1500 °F) it was observed to act significantly superior to the Waspaloy alloy.

[0122]

[0121] In addition to testing at room temperature and 816.6 °C (1500 °F), elongation was evaluated at 760.0 °C (1400 °F) for an 11.34 kg (25 lb.) heat. Figure 6 plots elongation versus test temperature for each of the heats (batch numbers are listed).

[0123]

[0122] The stress rupture tests at 816.6 °C (1500 °F) and 275.8 MPa (40 ksi) were carried out on only some of the heats because the stress rupture times were very long. For some of the chemical compositions, after the stress rupture tests were carried out at 816.6 °C (1500 °F) and 275.8 MPa (40 ksi), the stress rupture test conditions were changed to 816.6 °C (1500 °F) / 344.7 MPa (50 ksi) and 816.6 °C (1500 °F) / 413.7 MPa (60 ksi). The test results under those additional conditions are shown in Table 10 and Table 11, respectively. Figures 7 to 9 graph the stress rupture results for each of the test conditions. As expected, the stress rupture times at higher stresses are generally shorter. Table 10 and Table 11 also provide the stress rupture time and elongation results under the test conditions shown for Waspaloy alloy production materials heat-treated in the order of the following steps: (1) heating at 1079 °C (1975 °F) for 4 hours and air cooling; (2) heating at 843 °C (1550 °F) for 24 hours and air cooling; (3) heating at 760 °C (1400 °F) for 16 hours and air cooling.

[0124]

Table 11

[0125]

Table 12

[0126] Example 3

[0123] After examining the mechanical and microstructural results for the 11.34 kg (25 lb.) heat of Example 2, seven 136.08 kg (300 lb.) experimental heats (from P0F15 to P0F19) were melted by vacuum induction melting and then remelted using vacuum arc remelting. Table 12 provides the chemical composition of each of the 136.08 kg (300 lb.) heats, where all contents are weight percentages on the total weight basis of the alloy heat.

[0127]

Table 13

[0128]

[0124] Heat P0F14 contains a relatively high cobalt content, increases the titanium solubility, and is prevented from contributing to TCP phase formation. This also enables a relatively high titanium / aluminum ratio and imparts favorable tensile properties (high strength and ductility at room temperature). The tungsten content in Heat P0F18 is relatively high, and the chromium content is low compared to P0F14. The lower chromium content reduces the likelihood of sigma phase precipitation and improves the solid solubility limits of tungsten and molybdenum in Heat P0F18. Heat P0F19 was similar to Heat P0F16 but had a higher tungsten content and a lower molybdenum content, which could improve creep properties and potentially reduce the tendency to form the TCP phase.

[0129]

[0125] The gamma prime solvus temperatures from Heat No. P0F14 to No. P0F19 were determined by DTA, and the results are shown in Table 13. As already discussed, the preferred gamma prime solvus for the alloys according to the present disclosure is 1121 °C (2050 °F) or lower, and in Table 10, all results except for Heat No. P0F19 meet that preferred characteristic.

[0130]

Table 14

[0131]

[0126] After homogenization, the alloy samples were heat-treated. Table 14 provides the steps of the heat treatment applied to the heat. In Table 14, "AC" refers to air cooling.

[0132]

Table 15

[0133]

[0127] Test specimens were prepared from the heat-treated alloy and tested for tensile and forming properties at various test specimen temperatures. The tensile and formability test results are presented in Table 15. Heat-treated production specimens of the Waspaloy alloy were also tested and the results are shown in Table 15.

[0134]

Table 16-1

Table 16-2

[0135]

[0128] Specimens of the heat-treated alloy and Waspaloy alloy production material were also tested for stress rupture time and elongation at elevated temperatures at a specimen temperature of 816 °C (1500 °F) and with a stress of 345 MPa (50 ksi) or 414 MPa (60 ksi) applied. The test results are shown in Table 16.

[0136]

Table 17

[0129] All of the experimental alloys in this example showed a significant improvement in creep rupture properties and tensile strength compared to Waspaloy.

[0137] Example 4

[0130] Nickel-based alloy heats having the chemical compositions listed in Table 17 were prepared by vacuum induction melting the feedstock. The values in Table 17 are weight percentages on an all alloy weight basis. "NM" means that the content was not measured. Each alloy heat also contained unavoidable impurities and the balance nickel. The heats were gas atomized to form powders for metallurgy.

[0138]

Table 18

[0139] Example 5

[0131] Nickel-based alloy ingots having the chemical compositions listed in Table 18 were prepared by vacuum induction melting and vacuum arc remelting of the feedstock. Each heat weighed approximately 136.08 kg (300 lb.). The values in Table 18 are weight percentages based on the total alloy weight. Each alloy also contained unavoidable impurities.

[0140]

Table 19

[0141]

[0132] Samples of the heat-treated alloy were tested at room temperature and elevated temperatures with respect to yield strength, maximum yield strength, and percent elongation. Additionally, samples were tested with respect to stress rupture time and rupture elongation at a sample temperature of 816 °C (1500 °F) and a stress of 345 MPa (50 ksi). The stress rupture tests were conducted in accordance with ASTM E139-11. The room temperature tensile tests were conducted in accordance with ASTM E8 / E8M-22. The tensile tests at elevated temperatures were conducted in accordance with ASTM E21-20. The test results are shown in Table 19.

[0142]

Table 20

[0143]

[0133] Additionally, as shown in Figures 10 - 11, samples of heats P2F02 and P2F07 were analyzed with respect to microstructural features. The grain size of P2F02 in Figure 10 is 8.1 ASTM grain size. The grain size of P2F07 in Figure 11 is 8.2 ASTM grain size.

[0144] Example 6

[0134] Nickel-based alloy heats having the chemical compositions listed in Table 20 were prepared by vacuum induction melting a feedstock followed by gas atomization to produce metal powders. After gas atomization, the powder heats were sieved for use in LPBF printing. The values in Table 20 are weight percentages on an all alloy weight basis. “NM” means that the content was not measured. Each alloy heat also contained inevitable impurities and the balance nickel.

[0145]

[0135] Test bars for mechanical testing were additively manufactured using powders for metallurgy. The SLM 125HL LPBF machine (SLM Solutions, Lubeck, Germany), and the EOS M290 LPBF machine (EOS GmbH, Krailling, Germany) were used to print test bars using various orientations of the test bars. The SLM machine has a build volume of 125 mm × 125 mm × 125 mm, and the EOS machine has a build volume of 250 mm × 250 mm × 325 mm. Both instruments use similar laser and inert gas (argon) systems. After printing, the test bars were subjected to tensile tests at different temperatures, as well as stress rupture tests at different temperatures and stresses. The machining and mechanical test results of the test bars are shown in Tables 21 and 22.

[0146]

Table 21

[0147]

Table 22-1

Table 22-2

Table 22-3

Table 22-4

[0148]

Table 23

[0149]

[0136] The following numbered clauses are directed to various non-limiting embodiments according to the present disclosure.

[0150] Clause 1. By weight percentage based on the total alloy weight, 11 to 18 chromium; 16 to 28 cobalt; 1.5 to 7.0 molybdenum; 0 to 6.5 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 2.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.02 boron; 0.001 to 0.1 zirconium; nickel; and a nickel-based alloy containing impurities.

[0151] Clause 2. The nickel-based alloy of Clause 1, wherein the aluminum equivalent number (Al eq ) of the nickel-based alloy is in the range of 3.6 to 4.5.

[0152] Clause 3. The nickel-based alloy according to any one of Clauses 1 and 2, wherein the total concentration of aluminum and titanium is 7.0 weight percent or less based on the total alloy weight.

[0153] Clause 4. The nickel-based alloy according to any one of Clauses 1 and 2, wherein the total concentration of aluminum and titanium is 5.0 to 7.0 weight percent based on the total alloy weight.

[0154] Clause 5. The nickel-based alloy according to any one of Clauses 1 to 4, containing 11 to 16 weight percent chromium based on the total alloy weight.

[0155] Item 6. A nickel-based alloy according to any one of Items 1 to 5, containing 0.001 to 0.015 weight percent of boron based on the total alloy weight.

[0156] Item 7. A nickel-based alloy according to any one of Items 1 to 6, containing at least 36 weight percent of nickel based on the total alloy weight.

[0157] Item 8. A nickel-based alloy according to any one of Items 1 to 7, containing 16 to 19 weight percent of cobalt based on the total alloy weight.

[0158] Item 9. A nickel-based alloy according to any one of Items 1 to 8, containing 2.0 to 4.5 weight percent of titanium based on the total alloy weight.

[0159] Item 10. By weight percentage based on the total alloy weight, 11 to 16 of chromium; 16 to 28 of cobalt; 1.5 to 7.0 of molybdenum; 0 to 6.5 of tungsten; 0 to 1.0 of niobium; 1.0 to 2.5 of aluminum; 2.0 to 6.0 of titanium; 0 to 2.0 of tantalum; 0 to 4.0 of iron; 0 to 0.5 of hafnium; 0.01 to 0.2 of carbon; 0.001 to 0.015 of boron; 0.001 to 0.1 of zirconium; at least 36 of nickel; and impurities A nickel-based alloy according to any one of Items 1 to 7, comprising the total concentration of aluminum, niobium, and titanium is 7.0 weight percent or less, the aluminum equivalent number (Al eq ) of the nickel-based alloy is in the range of 3.6 to 4, a nickel-based alloy.

[0160] Item 11. Any nickel-based alloy of Item 10, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy.

[0161] Item 12. By weight percentage based on the total weight of the alloy, 11 to 18 of chromium; 24 to 28 of cobalt; 1.5 to 7.0 of molybdenum; 2.0 to 6.0 of tungsten; 0 to 1.0 of niobium; 1.0 to 2.5 of aluminum; 2.0 to 6.0 of titanium; 0 to 2.0 of tantalum; 0 to 4.0 of iron; 0 to 0.5 of hafnium; 0.01 to 0.2 of carbon; 0.001 to 0.02 of boron; 0.001 to 0.1 of zirconium; nickel; and impurities comprising a nickel-based alloy.

[0162] Item 13. A nickel-based alloy of Item 12, wherein the aluminum equivalent number (Al eq ) is in the range of 3.6 to 4.

[0163] Item 14. Any nickel-based alloy of Items 12 to 13, wherein the total concentration of aluminum and titanium is 7.0 weight percent or less based on the total weight of the alloy.

[0164] Item 15. Any nickel-based alloy of Items 12 to 14, wherein the total concentration of aluminum and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy.

[0165] Item 16. Any nickel-based alloy of Items 12 to 15, comprising 14 to 16 weight percent of chromium based on the total weight of the alloy.

[0166] Item 17. A nickel-based alloy according to any of Items 12 to 16, containing 24 to 27 weight percent cobalt based on the total alloy weight.

[0167] Item 18. A nickel-based alloy according to any of Items 12 to 17, containing 3.0 to 4.5 weight percent titanium based on the total alloy weight.

[0168] Item 19. A nickel-based alloy according to any of Items 12 to 18, containing 1.7 to 2.0 weight percent aluminum based on the total alloy weight.

[0169] Item 20. A nickel-based alloy according to any of Items 12 to 19, containing 0.001 to 0.015 weight percent boron based on the total alloy weight.

[0170] Item 21. A nickel-based alloy according to any of Items 12 to 20, containing at least 46 weight percent nickel based on the total alloy weight.

[0171] Item 22. By weight percentage based on the total alloy weight, 14 to 16 of chromium; 24 to 27 of cobalt; 1.5 to 7.0 of molybdenum; 0 to 6.5 of tungsten; 0 to 1.0 of niobium; 1.7 to 2.0 of aluminum; 3.0 to 4.5 of titanium; 0 to 2.0 of tantalum; 0 to 4.0 of iron; 0 to 0.5 of hafnium; 0.01 to 0.2 of carbon; 0.001 to 0.015 of boron; 0.001 to 0.1 of zirconium; at least 46 of nickel; and impurities A nickel-based alloy according to Item 12, containing The total concentration of aluminum, niobium, and titanium is 7.0 weight percent or less, The aluminum equivalent number of the nickel-based alloy (Aleq ) is in the range of 3.6 to 4, Nickel-based alloy.

[0172] Clause 23. The nickel-based alloy of Clause 22, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy.

[0173] Clause 24. By weight percentage based on the total weight of the alloy, 11 to 18 chromium; 16 to 28 cobalt; 1.5 to 7.0 molybdenum; 0 to 6.5 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 2.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.02 boron; 0.001 to 0.1 zirconium; Nickel; and Impurities Nickel-based alloy containing.

[0174] Clause 25. The nickel-based alloy of Clause 24, wherein the aluminum equivalent number (Al eq ) is in the range of 3.6 to 4.5.

[0175] Clause 26. The nickel-based alloy of any one of Clauses 24 to 25, wherein the total concentration of aluminum and titanium is 7.0 weight percent or less based on the total weight of the alloy.

[0176] Clause 27. The nickel-based alloy of any one of Clauses 24 to 26, wherein the total concentration of aluminum and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy.

[0177] Item 28. A nickel-based alloy according to any one of Items 24 to 27, containing 13 to 17 weight percent chromium based on the total alloy weight.

[0178] Item 29. A nickel-based alloy according to any one of Items 24 to 28, containing 0.001 to 0.015 weight percent boron based on the total alloy weight.

[0179] Item 30. A nickel-based alloy according to any one of Items 24 to 29, containing at least 36 weight percent nickel based on the total alloy weight.

[0180] Item 31. A nickel-based alloy according to any one of Items 24 to 30, containing 16 to 25 weight percent cobalt based on the total alloy weight.

[0181] Item 32. A nickel-based alloy according to any one of Items 24 to 31, containing 3.0 to 6.0 weight percent titanium based on the total alloy weight.

[0182] Item 33. A nickel-based alloy according to any one of Items 24 to 32, containing 13 to 17 weight percent chromium based on the total alloy weight.

[0183] Item 34. A nickel-based alloy according to any one of Items 24 to 33, containing 1 to 6.5 weight percent tungsten based on the total alloy weight.

[0184] Item 35. A nickel-based alloy according to any one of Items 24 to 34, containing 0 to 0.05 weight percent magnesium based on the total alloy weight.

[0185] Item 36. By weight percentage based on the total alloy weight, 13 to 17 chromium; 16 to 25 cobalt; 1.5 to 7.0 molybdenum; 0 to 6.5 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; 0 to 2.0 tantalum; Iron from 0 to 4.0; Hafnium from 0 to 0.5; Carbon from 0.01 to 0.2; Boron from 0.001 to 0.015; Zirconium from 0.001 to 0.1; Optional trace elements; At least 36 nickel; and Impurities A nickel-based alloy according to clause 24, containing the above.

[0186] Clause 37. A nickel-based alloy according to clause 36, wherein the total concentration of aluminum, niobium, and titanium is 7.0 wt% or less.

[0187] Clause 38. A nickel-based alloy according to any of clauses 36 to 37, wherein the aluminum equivalent number (Al eq ) is in the range of 3.6 to 4.5.

[0188] Clause 39. A nickel-based alloy according to any of clauses 36 to 38, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 wt% based on the total weight of the alloy.

[0189] Clause 40. A nickel-based alloy according to any of clauses 36 to 39, containing 16 to 19 wt% of cobalt based on the total weight of the alloy.

[0190] Clause 41. A nickel-based alloy according to any of clauses 36 to 39, containing 19 to 25 wt% of cobalt based on the total weight of the alloy.

[0191] Clause 42. A nickel-based alloy according to any of clauses 36 to 41, containing 2.0 to 4.0 wt% of molybdenum based on the total weight of the alloy.

[0192] Clause 43. A nickel-based alloy according to any of clauses 36 to 41, containing 4.0 to 6.0 wt% of molybdenum based on the total weight of the alloy.

[0193] Clause 44. A nickel-based alloy according to any one of Clauses 36 to 43, containing 0 to 0.5 weight percent of tungsten based on the total alloy weight.

[0194] Clause 45. A nickel-based alloy according to any one of Clauses 36 to 43, containing 2.0 to 5.0 weight percent of tungsten based on the total alloy weight.

[0195] Clause 46. A nickel-based alloy according to any one of Clauses 36 to 45, containing 1.25 to 1.9 weight percent of aluminum based on the total alloy weight.

[0196] Clause 47. A nickel-based alloy according to any one of Clauses 36 to 46, containing 1.0 to 3.0 weight percent of iron based on the total alloy weight.

[0197] Clause 48. A nickel-based alloy according to any one of Clauses 36 to 47, containing 0.6 to 2.0 weight percent of tantalum based on the total alloy weight.

[0198] Clause 49. A nickel-based alloy according to any one of Clauses 36 to 47, containing 0 to 0.5 weight percent of tantalum based on the total alloy weight.

[0199] Clause 50. A nickel-based alloy according to any one of Clauses 36 to 49, containing 3.0 to 4.0 weight percent of titanium based on the total alloy weight.

[0200] Clause 51. A nickel-based alloy according to any one of Clauses 36 to 49, containing 4.5 to 5.5 weight percent of titanium based on the total alloy weight.

[0201] Clause 52. A nickel-based alloy according to any one of Clauses 36 to 51, containing 14 to 17 weight percent of chromium based on the total alloy weight.

[0202] Clause 53. A nickel-based alloy according to any one of Clauses 36 to 52, containing 0.2 to 1.0 weight percent of niobium based on the total alloy weight.

[0203] Article 54. A nickel-based alloy according to any one of Articles 36 to 53, containing at least 46 weight percent nickel based on the total alloy weight.

[0204] Article 55. A nickel-based alloy according to any one of Articles 36 to 54, wherein the aluminum equivalent number (Al eq ) of the nickel-based alloy is in the range of 3.6 to 4.2.

[0205] Article 56. A nickel-based alloy according to any one of Articles 36 to 55, wherein the aluminum equivalent number (Al eq ) of the nickel-based alloy is in the range of 4.0 to 4.5.

[0206] Article 57. A nickel-based alloy according to any one of Articles 36 to 56, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 6.0 weight percent based on the total alloy weight.

[0207] Article 58. A nickel-based alloy according to any one of Articles 36 to 57, wherein the total concentration of aluminum, niobium, and titanium is 6.0 to 7.0 weight percent based on the total alloy weight.

[0208] Article 59. A nickel-based alloy according to any one of Articles 36 to 58, wherein the trace element contains 0 to 0.05 weight percent magnesium based on the total alloy weight.

[0209] Article 60. By weight percentage based on the total alloy weight, 13 to 17 of chromium; 16 to 19 of cobalt; 1.5 to 7.0 of molybdenum; 2.0 to 5.0 of tungsten; 0 to 1.0 of niobium; 1.0 to 2.5 of aluminum; 3.0 to 6.0 of titanium; 0 to 2.0 of tantalum; 0 to 3.0 of iron; 0 to 0.5 of hafnium; 0.01 to 0.2 of carbon; 0.001 to 0.015 of boron; 0.001 to 0.1 zirconium; Optionally, trace elements; At least 46 nickel; and Impurities A nickel-based alloy comprising The aluminum equivalent number (Al eq ) of the nickel-based alloy is in the range of 3.6 to 4.5, The total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy, Nickel-based alloy.

[0210] Clause 61. By weight percentage based on the total weight of the alloy, 14 to 17 chromium; 19 to 25 cobalt; 2.0 to 4.0 molybdenum; 0 to 6.5 tungsten; 0 to 0.8 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 3.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.015 boron; 0.001 to 0.1 zirconium; Optionally, trace elements; At least 46 nickel; and Impurities A nickel-based alloy comprising The aluminum equivalent number (Al eq ) of the nickel-based alloy is in the range of 3.6 to 4.5, The total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy, Nickel-based alloy.

[0211] Clause 62. By weight percentage based on the total weight of the alloy, 14 to 17 chromium; 16 to 19 cobalt; 2.0 to 4.0 molybdenum; 2.0 to 5.0 tungsten; 0 to 1.0 niobium; 1.0 to 2.5 aluminum; 3.0 to 6.0 titanium; Greater than 0 to 2.0 tantalum; 1.0 to 3.0 iron; 0 to 0.5 hafnium; 0.01 to 0.2 carbon; 0.001 to 0.015 boron; 0.001 to 0.1 zirconium; Optionally trace elements; At least 46 nickel; and Impurities A nickel-based alloy comprising, The aluminum equivalent number (Al of the nickel-based alloy eq ) is in the range of 3.6 to 4.5, The total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy, Nickel-based alloy.

[0212] An additive manufacturing part comprising the nickel-based alloy of any one of clauses 63. to 62.

[0213] Clause 64. An additive manufacturing part of clause 63. comprising at least one part selected from the group consisting of a heat exchanger, a nose cone, a scramjet engine member, a vehicle leading edge, a heat pipe, a reentry structure, an actively or passively cooled controlled surface, a vehicle outer panel, a ramjet member, a rocket motor member, a combined cycle motor member, a rotating detonation motor member, a gasification facility member, a chemical treatment facility member, and a fastening system member.

[0214] Clause 65. The yield strength in the aged state of at least 827 MPa (120 ksi) at room temperature, and The yield strength in the aged state of at least 621 MPa (90 ksi) at 816 °C (1500 °F), and The maximum tensile strength in the aged condition at room temperature of at least 1241 MPa (180 ksi), the maximum tensile strength in the aged condition at 816 °C (1500 °F) of at least 621 MPa (90 ksi), the percent elongation in the aged condition at room temperature in the range of 15% to 40% and a nickel-based alloy according to any of clauses 24 to 62.

[0215] Clause 66. The yield strength in the aged condition at room temperature of at least 862 MPa (125 ksi), the yield strength in the aged condition at 816 °C (1500 °F) of at least 689 MPa (100 ksi), the maximum tensile strength in the aged condition at room temperature of at least 1344 MPa (195 ksi), the maximum tensile strength in the aged condition at 816 °C (1500 °F) of at least 724 MPa (105 ksi), the percent elongation in the aged condition at room temperature in the range of 25% to 35% and a nickel-based alloy according to any of clauses 24 to 62.

[0216] Clause 67. By weight percentage on an all-alloy weight basis, 15 to 17 chromium; 22 to 26 cobalt; 2.0 to 4.0 molybdenum; 0 to 2.0 tungsten; 0 to 1.0 niobium; 1.0 to 4.0 aluminum; 1.0 to 6.0 titanium; 0 to 2.0 tantalum; 0 to 4.0 iron; 0 to 0.5 hafnium; 0 to 0.2 carbon; 0 to 0.02 boron; 0 to 0.1 zirconium; nickel; and impurities and a nickel-based alloy containing the same.

[0217] Clause 68. By weight percentage based on the total alloy weight, 14 - 17 chromium; 15 - 18 cobalt; 2.0 - 4.0 molybdenum; 1.0 - 4.0 tungsten; 0 - 1.0 niobium; 1.0 - 3.0 aluminum; 2.0 - 4.0 titanium; 0 - 2.0 tantalum; 0 - 4.0 iron; 0 - 0.5 hafnium; 0 - 0.2 carbon; 0 - 0.02 boron; 0 - 0.1 zirconium; nickel; and a nickel-based alloy containing impurities.

[0218]

[0137] It will be readily understood by those skilled in the art that the present invention is capable of a wide range of practical uses and applications. Many embodiments and modifications of the present invention, as well as many variations, corrections, and equivalent arrangements other than those described herein, will become apparent from, or are reasonably suggested by, the present invention and its foregoing description without departing from the spirit or scope of the present invention. Accordingly, although the present invention has been described in detail herein in connection with its preferred embodiments, it is to be understood that this disclosure is only illustrative and exemplary of the present invention and is made for the purpose of providing a complete and enabling disclosure of the present invention. It should be understood that the foregoing disclosure is not intended, nor should it be construed, to limit the present invention or, in other cases, to exclude any such other embodiments, modifications, variations, corrections, and equivalent arrangements.

Claims

1. By weight percentage based on the total alloy weight, 11 - 18 chromium; 16 - 28 cobalt; 1.5 - 7.0 molybdenum; 0 - 6.5 tungsten; 0 - 1.0 niobium; 1.0 - 2.5 aluminum; 2.0 - 6.0 titanium; 0 - 2.0 tantalum; 0 - 4.0 iron; 0 - 0.5 hafnium; 0.01 - 0.2 carbon; 0.001 - 0.02 boron; 0.001 - 0.1 zirconium; nickel; and impurities A nickel-based alloy containing them.

2. The aluminum equivalent number (Al ｅｑ ) of the nickel-based alloy is in the range of 3.6 to 4.5, and the nickel-based alloy according to claim 1.

3. The nickel-based alloy according to Claim 1, wherein the total concentration of aluminum and titanium is 7.0 weight percent or less based on the total alloy weight.

4. The nickel-based alloy according to Claim 1, wherein the total concentration of aluminum and titanium is 5.0 - 7.0 weight percent based on the total alloy weight.

5. The nickel-based alloy according to Claim 1, containing 13 - 17 weight percent of chromium based on the total alloy weight.

6. The nickel-based alloy according to Claim 1, containing 0.001 - 0.015 weight percent of boron based on the total alloy weight.

7. The nickel-based alloy according to Claim 1, containing at least 36 weight percent of nickel based on the total alloy weight.

8. The nickel-based alloy according to Claim 1, containing 16 - 25 weight percent of cobalt based on the total alloy weight.

9. The nickel-based alloy according to Claim 1, containing 3.0 - 6.0 weight percent of titanium based on the total alloy weight.

10. The nickel-based alloy according to Claim 1, containing 1 - 6.5 weight percent of tungsten based on the total alloy weight.

11. The nickel-based alloy according to Claim 1, containing 0 - 0.05 weight percent of magnesium based on the total alloy weight.

12. By weight percentage based on the total alloy weight, 13 - 17 chromium; 16 - 25 cobalt; 1.5 - 7.0 molybdenum; 0 - 6.5 tungsten; 0 - 1.0 niobium; 1.0 - 2.5 aluminum; 3.0 - 6.0 titanium; 0 - 2.0 tantalum; 0 - 4.0 iron; 0 - 0.5 hafnium; 0.01 - 0.2 carbon; 0.001 - 0.015 boron; 0.001 - 0.1 zirconium; Optionally trace elements; at least 36 nickel; and impurities A nickel-based alloy containing them, according to Claim 1.

13. The nickel-based alloy according to claim 12, wherein the total concentration of aluminum, niobium, and titanium is 7.0 wt% or less.

14. The aluminum equivalent number (Al ｅｑ ) of the nickel-based alloy is in the range of 3.6 to 4.5, and the nickel-based alloy according to claim 12.

15. The nickel-based alloy according to claim 12, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 wt% based on the total weight of the alloy.

16. The nickel-based alloy according to claim 12, comprising 16 to 19 wt% of cobalt based on the total weight of the alloy.

17. The nickel-based alloy according to claim 12, comprising 19 to 25 wt% of cobalt based on the total weight of the alloy.

18. The nickel-based alloy according to claim 12, comprising 2.0 to 4.0 wt% of molybdenum based on the total weight of the alloy.

19. The nickel-based alloy according to claim 12, comprising 4.0 to 6.0 wt% of molybdenum based on the total weight of the alloy.

20. The nickel-based alloy according to claim 12, comprising 0 to 0.5 wt% of tungsten based on the total weight of the alloy.

21. The nickel-based alloy according to claim 12, comprising 2.0 to 5.0 wt% of tungsten based on the total weight of the alloy.

22. The nickel-based alloy according to claim 12, comprising 1.25 to 1.9 wt% of aluminum based on the total weight of the alloy.

23. The nickel-based alloy according to claim 12, comprising 1.0 to 3.0 wt% of iron based on the total weight of the alloy.

24. The nickel-based alloy according to claim 12, comprising 0.6 to 2.0 wt% of tantalum based on the total weight of the alloy.

25. The nickel-based alloy according to claim 12, comprising 0 to 0.5 wt% of tantalum based on the total weight of the alloy.

26. The nickel-based alloy according to claim 12, comprising 3.0 to 4.0 wt% of titanium based on the total weight of the alloy.

27. The nickel-based alloy according to claim 12, comprising 4.5 to 5.5 wt% of titanium based on the total weight of the alloy.

28. The nickel-based alloy according to claim 12, comprising 14 to 17 wt% of chromium based on the total weight of the alloy.

29. The nickel-based alloy according to claim 12, comprising 0.2 to 1.0 wt% of niobium based on the total weight of the alloy.

30. The nickel-based alloy according to claim 12, comprising at least 46 wt% of nickel based on the total weight of the alloy.

31. The aluminum equivalent number (Al ｅｑ ) of the nickel-based alloy is in the range of 3.6 to 4.2, and the nickel-based alloy according to claim 12.

32. The aluminum equivalent number (Al ｅｑ ) of the nickel-based alloy is in the range of 4.0 to 4.

5. The nickel-based alloy according to claim 12.

33. The nickel-based alloy according to claim 12, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 6.0 weight percent based on the total weight of the alloy.

34. The nickel-based alloy according to claim 12, wherein the total concentration of aluminum, niobium, and titanium is 6.0 to 7.0 weight percent based on the total weight of the alloy.

35. The nickel-based alloy according to claim 12, wherein the trace element contains magnesium in an amount of 0 to 0.05 weight percent based on the total weight of the alloy.

36. By weight percentage based on the total weight of the alloy, 13 to 17 of chromium; 16 to 19 of cobalt; 1.5 to 7.0 of molybdenum; 2.0 to 5.0 of tungsten; 0 to 1.0 of niobium; 1.0 to 2.5 of aluminum; 3.0 to 6.0 of titanium; 0 to 2.0 of tantalum; 0 to 3.0 of iron; 0 to 0.5 of hafnium; 0.01 to 0.2 of carbon; 0.001 to 0.015 of boron; 0.001 to 0.1 of zirconium; Optionally trace elements; At least 46 of nickel; and Impurities comprising, The aluminum equivalent number (Al ｅｑ ) of the nickel-based alloy is in the range of 3.6 to 4.5, The nickel-based alloy according to claim 1, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy. Nickel-based alloy.

37. By weight percentage based on the total weight of the alloy, 14 to 17 of chromium; 19 to 25 of cobalt; 2.0 to 4.0 of molybdenum; 0 to 6.5 of tungsten; 0 to 0.8 of niobium; 1.0 to 2.5 of aluminum; 3.0 to 6.0 of titanium; 0 to 2.0 of tantalum; 0 to 3.0 of iron; 0 to 0.5 of hafnium; 0.01 to 0.2 of carbon; 0.001 to 0.015 of boron; 0.001 to 0.1 of zirconium; Optionally trace elements; At least 46 of nickel; and Impurities comprising, The nickel-based alloy according to claim 1, wherein the total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy. The aluminum equivalent number (Al ｅｑ ) of the nickel-based alloy is in the range of 3.6 to 4.5, Nickel-based alloy.

38. By weight percentage based on the total weight of the alloy, 14 to 17 of chromium; 16 to 19 of cobalt; 2.0 to 4.0 of molybdenum; 2.0 to 5.0 of tungsten; 0 to 1.0 of niobium; 1.0 to 2.5 of aluminum; 3.0 to 6.0 of titanium; Greater than 0 to 2.0 of tantalum; 1.0 to 3.0 of iron; 0 to 0.5 of hafnium; 0.01 to 0.2 of carbon; 0.001 to 0.015 of boron; 0.001 to 0.1 of zirconium; Optionally trace elements; ​ At least 46 nickel; and impurities The nickel-based alloy according to claim 1, comprising The aluminum equivalent number (Al ｅｑ ) of the nickel-based alloy is in the range of 3.6 to 4.5, The total concentration of aluminum, niobium, and titanium is 5.0 to 7.0 weight percent based on the total weight of the alloy, nickel-based alloy.

39. An additive manufacturing part comprising the nickel-based alloy according to claim 37.

40. At least one part selected from the group consisting of a heat exchanger, a nose cone, a scramjet engine member, a vehicle leading edge, a heat pipe, a reentry structure, an actively or passively cooled and controlled surface, a vehicle outer panel, a ramjet member, a rocket motor member, a compound cycle motor member, a rotating detonation motor member, a gasification facility member, a chemical treatment facility member, and a fastening system member, the additive manufacturing part according to claim 39.

41. An additive manufacturing part comprising the nickel-based alloy according to claim 38.

42. At least one part selected from the group consisting of a heat exchanger, a nose cone, a scramjet engine member, a vehicle leading edge, a heat pipe, a reentry structure, an actively or passively cooled and controlled surface, a vehicle outer panel, a RAM jet member, a rocket motor member, a compound cycle motor member, a rotating detonation motor member, a gasification facility member, a chemical treatment facility member, and a fastening system member, the additive manufacturing part according to claim 41.

43. The yield strength in the aged state at least 827 MPa (120 ksi) at room temperature, The yield strength in the aged state at least 621 MPa (90 ksi) at 816 °C (1500 °F), The maximum tensile strength in the aged state at least 1241 MPa (180 ksi) at room temperature, The maximum tensile strength in the aged state at least 621 MPa (90 ksi) at 816 °C (1500 °F), The percent elongation in the aged state in the range of 15% to 40% at room temperature and showing, any of the nickel-based alloys according to claim 1.

44. The yield strength in the aged state at least 862 MPa (125 ksi) at room temperature, The yield strength in the aged state at least 689 MPa (100 ksi) at 816 °C (1500 °F), The maximum tensile strength in the aged state at least 1344 MPa (195 ksi) at room temperature, The maximum tensile strength in the aged condition at 816 °C (1500 °F) of at least 724 MPa (105 ksi), and The percent elongation in the aged condition in the range of 25% to 35% at room temperature, and The nickel-based alloy according to any one of claims 1, showing

45. By weight percentage based on the total alloy weight, 15 - 17 chromium; 22 - 26 cobalt; 2.0 - 4.0 molybdenum; 0 - 2.0 tungsten; 0 - 1.0 niobium; 1.0 - 4.0 aluminum; 1.0 - 6.0 titanium; 0 - 2.0 tantalum; 0 - 4.0 iron; 0 - 0.5 hafnium; 0 - 0.2 carbon; 0 - 0.02 boron; 0 - 0.1 zirconium; Nickel; and Impurities A nickel-based alloy containing

46. By weight percentage based on the total alloy weight, 14 - 17 chromium; 15 - 18 cobalt; 2.0 - 4.0 molybdenum; 1.0 - 4.0 tungsten; 0 - 1.0 niobium; 1.0 - 3.0 aluminum; 2.0 - 4.0 titanium; 0 - 2.0 tantalum; 0 - 4.0 iron; 0 - 0.5 hafnium; 0 - 0.2 carbon; 0 - 0.02 boron; 0 - 0.1 zirconium; Nickel; and Impurities A nickel-based alloy containing

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