A steam turbine member has suppressed adhesion of scale for a long time without deterioration of corrosion resistance and the like of a turbine. A steam turbine member includes a hard layer 2 and a deposited amorphous carbon film 3 on a base material 1, in that order.

An exhaust hood (Ec) of the present invention is provided with an inner casing (21), an outer casing (30), and a diffuser (26). The inner casing (21) surrounds a rotor from the outside in a radial direction, and forms a first space (21s) in which a fluid flows in an axial direction (Da) between the rotor and the inner casing (21). The diffuser (26) is provided with a bearing cone (29) that has a diameter that gradually widens moving towards an axial downstream side (Dad) and forms a cylindrical shape extending to the axial downstream side (Dad) to be continuous with the outer circumferential surface of a rotor shaft that forms the first space (21s). An end edge (29a) on the axial downstream side (Dad) of the bearing cone (29) forms an oval shape in which, in a direction orthogonal to an axial line (Ar), a distance (R2an) between the axial line (Ar) and a second cone end part (29ab) of a second side (Dan) is greater than a distance (R2ex) between the axial line (Ar) and a first cone end part (29aa) of a first side (Dex).

An exhaust hood (Ec) of the present invention is provided with an inner casing (21), an outer casing (30), and a diffuser (26). The inner casing (21) surrounds a rotor from the outside in a radial direction, and forms a first space (21s) in which a fluid flows in an axial direction (Da) between the rotor and the inner casing (21). The diffuser (26) is provided with a bearing cone (29) that has a diameter that gradually widens moving towards an axial downstream side (Dad) and forms a cylindrical shape extending to the axial downstream side (Dad) to be continuous with the outer circumferential surface of a rotor shaft that forms the first space (21s). An end edge (29a) on the axial downstream side (Dad) of the bearing cone (29) forms an oval shape in which, in a direction orthogonal to an axial line (Ar), a distance (R2an) between the axial line (Ar) and a second cone end part (29ab) of a second side (Dan) is greater than a distance (R2ex) between the axial line (Ar) and a first cone end part (29aa) of a first side (Dex).

Provided is a Ni-based alloy having a composition consisting of, by mass %, Cr: 14.0% to 17.0% (preferably, not less than 14.0% and less than 15.0%), Fe: 5.0% to 9.0%, Ti: 2.2% to 2.8%, Al: 0.40% to 1.00%, a total amount of Nb+Ta: 0.7% to 1.2%, B: 0.001% to 0.010%, Zr: 0.01% to 0.15%, Mg: 0.001% to 0.050%, Mn: 0.01% to 0.20%, Cu: 0.005% to 0.300%, Mo: 0.01% to 0.30%, C: 0.01% to 0.05%, and the balance of Ni with inevitable impurities. In a creep test under conditions of a test temperature of 750° C. and a test load of 330 MPa, the Ni-based alloy preferably has a creep rupture life of not less than 120 hours and an elongation of not less than 16%, i.e., has good high-temperature creep characteristics. The Ni-based alloy is suitable for a gas turbine member.

To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. In a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor, the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle, and an interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.

A bearing assembly for a turbine engine includes a first gas bearing configured to receive a load from a rotating shaft of the turbine engine, a transmission disk configured to receive the load from the first gas bearing, and a damping member coupled to a casing of a combustor section of the turbine engine. The transmission disk includes a gas delivery disk, which includes an axial opening configured to facilitate an axial flow through the gas delivery disk and a duct configured to facilitate a radial flow through the gas delivery disk to form the first gas bearing. The damping member is configured to receive the load from the transmission disk.

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

The present disclosure generally relates to methods for additive manufacturing (AM) that utilize integrated ribs to support thin walled annular structures. An annular wall fabricated using AM has a thickness less than 0.022 inches across a majority of a surface of the annular wall and a plurality of ribs having a thickness greater than 0.030 inches. The annular wall has a mean thickness less than 0.100 inches. The annular wall conforms to a surface of the component and a mean distance between the annular wall and the component is less than 0.080 inches.

The present disclosure generally relates to methods for additive manufacturing (AM) that utilize integrated ribs to support thin walled annular structures. An annular wall fabricated using AM has a thickness less than 0.022 inches across a majority of a surface of the annular wall and a plurality of ribs having a thickness greater than 0.030 inches. The annular wall has a mean thickness less than 0.100 inches. The annular wall conforms to a surface of the component and a mean distance between the annular wall and the component is less than 0.080 inches.