A high melt superalloy powder mixture is provided for use with additive manufacturing or welding metal components or portions thereof. The high melt superalloy powder may include by weight about 7.7% to about 18% chromium, about 10.6% to about 11% cobalt, about 4.5% to about 6.5% aluminum, about 10.6% to about 11% tungsten, about 0.3% to about 0.55% molybdenum, about 0.05% to about 0.08% carbon, and at least 40% nickel.

A corrosion-resistant nickel alloy, a preparation method thereof and, and a use thereof are provided. The alloy includes the following components in percentage by mass: 4.68-5.35% of B, 5.69-6.41% of W, 27.68-28.39% of Cr, 12.65-13.42% of Al, and the balance of Ni and inevitable impurities. The alloy disclosed by the present invention is a Ni—W—B ternary alloy with main components of Ni, W and B, wherein the three elements have strong high-temperature corrosion resistance at a temperature of about 600° C., and have the potential of solid solution hardening and precipitate formation because all belong to solid solution forming elements, so that a creep strength of a nickel alloy matrix is improved. Meanwhile, Al and Cr are further added in the alloy formula, so that Al.sub.2O.sub.3 and Cr.sub.2O.sub.3 oxide layers can be formed, which play a role as a physical diffusion barrier against chlorine gas and other corrosive gases.

Nickel-base precipitation hardenable alloys with enhanced hydrogen embrittlement resistance and desired yield strength have critical ranges of titanium and iron, among other elements. One of the nickel-base precipitation hardenable alloys has a composition, in wt.%, of Cr from about 18.0% to about 23.0%, Fe from about 7.0% to about 12.0%, Mo from about 6.5% to about 9.5%, Nb from about 3.2% to about 5.2%, Ti from about 0.3% to about 1.3%, Al up to about 0.4%, with a balance of Ni and incidental impurities. This alloy has a yield strength (0.2% offset) greater than or equal to 120 ksi (827 MPa), a plastic strain ratio greater than or equal to 0.35, and a plastic strain to failure greater than or equal to 9.0%.

Provided are a Ni-based heat resistant superalloy for aircraft engine cases excellent in high-temperature characteristic such as tensile characteristics and low-cycle fatigue characteristics in a high-temperature range and also excellent in workability, and an aircraft engine case formed of the same. The Ni-based heat resistant superalloy has composition containing, by mass, Co: 4.0 to 11.0%, Cr: 12.0 to 17.0%, Al: 2.0 to 4.0%, Ti: 2.0 to 4.0%, Al+Ti: 4.6 to 6.7%, Mo: more than 5.5 to 10.0%, W: more than 0 to 4.0%, B: 0.001 to 0.040%, C: 0.02 to 0.06%, Zr: 0 to 0.05%, Mg: 0 to 0.005%, P: 0 to 0.01%, Nb: 0 to 1.0%, Ta: 0 to 1.0%, and Fe: 0 to 2.0%, and the balance of Ni with inevitable impurities, and is suitable for aircraft engine cases.

A precipitation hardenable, cobalt-nickel base superalloy is disclosed. The is characterized by the following weight percent composition. C about 0.01 to about 0.15 Cr about 6.00 to about 15.00 Ni about 30.00 to about 45.00 W about 3.00 to about 15.00 Ti about 0.50 to about 4.00 Al about 3.00 to about 7.00 Nb up to about 2.50 Ta up to about 6.00 Hf up to about 1.50 Zr up to about 1.50 B up to about 0.20 Mo up to about 2.50 Si up to about 1.50
The balance of the alloy is cobalt and usual impurities. The alloy provides a novel combination of strength and ductility after long-term exposure to elevated operating temperatures as found in gas turbines and jet engines. A fine-grain steel article made from the alloy is also disclosed. The steel article is also characterized by a continuous surface layer of Al.sub.2O.sub.3 and Cr.sub.2O.sub.3 that protects the alloy from oxidation at the elevated operating temperatures.

The present invention provides an alloy, an alloy powder, an alloy member, and a composite member which are excellent in corrosion resistance and wear resistance, have crack resistance, and are suitable for an additive manufacturing method and the like. An alloy and an alloy powder include, by mass %, Cr: 18 to 22%, Mo: 18 to 28%, Ta: 1.5 to 57%, C: 1.0 to 2.5%, Nb: 0 to 42%, Ti: 0 to 15%, V: 0 to 27%, Zr: 0 to 29%, and a remainder consisting of Ni and unavoidable impurities, where a molar ratio of (Ta+0.7Nb+Ti+0.6V+Zr)/C=0.5 to 1.5 is satisfied. An alloy member is an additively manufactured product or a cast having such a solidification structure, and the solidification structure is a dendrite-like crystal structure having a metal phase having a face-centered cubic structure and carbides.

Provided are a Ni-based heat resistant superalloy for aircraft engine cases excellent in high-temperature characteristic such as tensile characteristics and low-cycle fatigue characteristics in a high-temperature range and also excellent in workability, and an aircraft engine case formed of the same. The Ni-based heat resistant superalloy has composition containing, by mass, Co: 4.0 to 11.0%, Cr: 12.0 to 17.0%, Al: 2.0 to 4.0%, Ti: 2.0 to 4.0%, Al+Ti: 4.6 to 6.7%, Mo: more than 5.5 to 10.0%, W: more than 0 to 4.0%, B: 0.001 to 0.040%, C: 0.02 to 0.06%, Zr: 0 to 0.05%, Mg: 0 to 0.005%, P: 0 to 0.01%, Nb: 0 to 1.0%, Ta: 0 to 1.0%, and Fe: 0 to 2.0%, and the balance of Ni with inevitable impurities, and is suitable for aircraft engine cases.

Provided are: an alloy member that is excellent in homogeneity of both the alloy composition and microstructure and excellent in shape controllability and includes a high entropy alloy having high mechanical properties and high corrosion resistance, a process for producing the same, and a product including the alloy member. In the present invention, the alloy member having a chemical composition comprising elements of Co, Cr, Fe, Ni, and Ti each in an amount within a range of 5 atomic % or more and 35 atomic % or less and Mo in an amount within a range of more than 0 atomic % and 8 atomic % or less, the reminder consisting of unavoidable impurities, wherein ultrafine grains having an average grain diameter of 100 nm or less are dispersed and precipitated in a parent phase crystal.

The present invention relates to a Co-based alloy product including a polycrystal of a Co-based alloy, the Co-based alloy including: 0.001 mass %≤C<0.100 mass %; 9.0 mass %≤Cr<20.0 mass %; 2.0 mass %≤Al<5.0 mass %; 13.0 mass %≤W<20.0 mass %; and 39.0 mass %≤Ni<55.0 mass %, with the balance being Co and unavoidable impurities, in which the Co-based alloy product comprises segregated cells formed inside a crystal grain of the polycrystal, the segregated cells have an average size of 1 μm or larger and 100 μm or smaller, and the segregated cells contain Al and Cr, and a method for producing the Co-based alloy product.

Inventive techniques for forming unique compositions of matter are disclosed, as well as various advantageous physical characteristics, and associated properties of the resultant materials. In particular, metal(s) (including various alloys, such as Inconel superalloys) are characterized by having carbon disposed within the metal lattice structure thereof. The carbon is primarily, or entirely, present at interstitial sites of the metal lattice, and may be present in amounts ranging from about 15 wt % to about 90 wt %. The carbon, moreover, forms non-polar covalent bonds with both metal atoms of the lattice and other carbon atoms present in the lattice. This facilitates substantially homogeneous dispersal of the carbon throughout the resultant material, conveying unique and advantageous properties such as strength-to-weight ratio, density, mechanical toughness, sheer strength, flex strength, hardness, anti-corrosiveness, electrical and/or thermal conductivity, etc. as described herein. In some approaches, the composition of matter may be powderized, or the powder may be pelletized.