A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any.

The present invention relates to a tube member having excellent local bending properties that is capable of being freely bent only on a given region thereof at a working temperature, thereby enabling the bending angle thereof to be freely adjusted by a user, and a method for manufacturing the tube member. According to the present invention, the tube member having excellent local bending properties, which is made of an alloy, may include a first region and a second region having different alloy structures from each other. According to the present invention, the first region may be in a cold-worked state or have an austenite phase at a given working temperature, and the second region may have a martensite phase at the given working temperature and a yield stress value lower than a yield stress value of the first region.

The present invention relates to a tube member having excellent local bending properties that is capable of being freely bent only on a given region thereof at a working temperature, thereby enabling the bending angle thereof to be freely adjusted by a user, and a method for manufacturing the tube member. According to the present invention, the tube member having excellent local bending properties, which is made of an alloy, may include a first region and a second region having different alloy structures from each other. According to the present invention, the first region may be in a cold-worked state or have an austenite phase at a given working temperature, and the second region may have a martensite phase at the given working temperature and a yield stress value lower than a yield stress value of the first region.

The present invention provides a Ni-based alloy, a heat-resistant and corrosion-resistant component, and a heat treatment furnace component, all of which have excellent corrosion resistance and mechanical strength at high temperatures. The Ni-based alloy of the present invention consists of, by mass %, Al: more than 5.0% and up to 26.0%, and Zr: more than 0% and up to 5.0%, the balance being Ni and unavoidable impurities. The Ni-based alloy preferably contains more than 0% and up to 5.0% of B, by mass %, in a combined amount with Zr. Moreover, it is preferable that the Ni-based alloy has P value and Q value and satisfies a relationship of Q value ≥ 0.89 × P value - 0.53, when the P value is obtained from a formula -18.95 + 0.1956 × Ni% + 0.1977 × Al% + 0.2886 × Zr% + 12.4 × B%, and the Q value is obtained by dividing an area percentage of Ni.sub.3Al precipitated on the surface of the alloy by 100.

The present invention provides a Ni-based alloy, a heat-resistant and corrosion-resistant component, and a heat treatment furnace component, all of which have excellent corrosion resistance and mechanical strength at high temperatures. The Ni-based alloy of the present invention consists of, by mass %, Al: more than 5.0% and up to 26.0%, and Zr: more than 0% and up to 5.0%, the balance being Ni and unavoidable impurities. The Ni-based alloy preferably contains more than 0% and up to 5.0% of B, by mass %, in a combined amount with Zr. Moreover, it is preferable that the Ni-based alloy has P value and Q value and satisfies a relationship of Q value ≥ 0.89 × P value - 0.53, when the P value is obtained from a formula -18.95 + 0.1956 × Ni% + 0.1977 × Al% + 0.2886 × Zr% + 12.4 × B%, and the Q value is obtained by dividing an area percentage of Ni.sub.3Al precipitated on the surface of the alloy by 100.

The present invention provides a friction material and a brake pad having excellent wear resistance while exhibiting a high friction coefficient under high-temperature and high-speed conditions. A friction material containing: 40 mass % or more and 80 mass % or less of a matrix containing at least one kind selected from the group consisting of Ni and Fe; 10 mass % or more and 30 mass % or less of inorganic particles containing zircon particles, titania particles, and mullite particles; and 10 mass % or more and 30 mass % or less of a lubricant containing at least one kind selected from the group consisting of graphite, molybdenum disulfide, boron nitride and calcium fluoride, wherein a content of the zircon particles is 30 vol % or more and 36 vol % or less, a content of the titania particles is 30 vol % or more and 36 vol % or less, and a content of the mullite particles is 30 vol % or more and 36 vol % or less with respect to a total content of 100 vol % of the zircon particles, the titania particles, and the mullite particles.

Embodiments of the present disclosure generally relate to protective coatings on aerospace components and methods for depositing the protective coatings. In one or more embodiments, a method for producing a protective coating on an aerospace component includes depositing a metal oxide template layer on the aerospace component containing nickel and aluminum (e.g., nickel-aluminum superalloy) and heating the aerospace component containing the metal oxide template layer during a thermal process and/or an oxidation process. The thermal process and/or oxidation process includes diffusing aluminum contained within the aerospace component towards a surface of the aerospace component containing the metal oxide template layer, oxidizing the diffused aluminum to produce an aluminum oxide layer disposed between the aerospace component and the metal oxide template layer, and removing at least a portion of the metal oxide template layer while leaving the aluminum oxide layer.

Embodiments of the present disclosure generally relate to protective coatings on aerospace components and methods for depositing the protective coatings. In one or more embodiments, a method for producing a protective coating on an aerospace component includes depositing a metal oxide template layer on the aerospace component containing nickel and aluminum (e.g., nickel-aluminum superalloy) and heating the aerospace component containing the metal oxide template layer during a thermal process and/or an oxidation process. The thermal process and/or oxidation process includes diffusing aluminum contained within the aerospace component towards a surface of the aerospace component containing the metal oxide template layer, oxidizing the diffused aluminum to produce an aluminum oxide layer disposed between the aerospace component and the metal oxide template layer, and removing at least a portion of the metal oxide template layer while leaving the aluminum oxide layer.

An electronic component includes a component body, a base electrode that has a surface exposed from the component body and contains at least one of silver and copper, an alloy layer deposited on the surface of the base electrode, and a nickel layer deposited on a surface of the alloy layer. The material of the alloy layer is an alloy containing nickel and tin.

An electronic component includes a component body, a base electrode that has a surface exposed from the component body and contains at least one of silver and copper, an alloy layer deposited on the surface of the base electrode, and a nickel layer deposited on a surface of the alloy layer. The material of the alloy layer is an alloy containing nickel and tin.