An erosion and CMAS resistant coating arranged on a TBC coated substrate and including at least one porous vertically cracked (PVC) coating layer providing lower thermal conductivity and being disposed over a layer of MCrAlY wherein M represents Ni, Co or their combinations. At least one dense vertically cracked (DVC) erosion and CMAS resistant coating layer is deposited over the at least one PVC coating layer.

A rotor for a turbomachine and a method of manufacturing the same. The method includes providing a lug with a lug body and an interface material disposed on the lug body. The method also includes friction welding the lug to a hub member via the interface material to define a projected structure for an outer radial area of a disc assembly of the rotor. The projected structure is configured to support a first side of a rotor blade of the rotor in cooperation with a second projected structure of the disc assembly supporting a second side of the rotor blade. The lug body and the hub member are made from different materials.

A ceramic matrix composite (CMC) center body may be positioned around an austenitic nickel-chromium-based superalloy attachment ring. The attachment ring may be integrally formed with a turbine engine case. The attachment ring may have a greater coefficient of thermal expansion than the center body. A plurality of pins may be inserted through apertures in the center body and coupled to the attachment ring. The pins may slide within the apertures, allowing the attachment ring to expand without applying a load on the center body.

In a manufacturing method of a turbine rotor blade using an Ni-based forged alloy, provided is a turbine rotor blade and a member of a turbine rotor blade having an excellent workability and a high degree of freedom in the design of a cooling structure. The turbine rotor blade includes at least two members, including a first member and a second member, and each member is provided with cooling structural parts acting as cooling flow passages. The turbine rotor blade has a joint that integrates the first member and the second member, wherein the joint has a forged structure and the whole turbine rotor blade including the joint has a uniform forged structure.

The present disclosure relates to a metallic shaft for connecting components of a gas turbine engine. Example embodiments include a metallic shaft (400) for connecting components of a gas turbine engine, the shaft (400) having a longitudinal axis (410) and comprising: a first section (401) extending from a first end (403) of the shaft (400) to a joint (405), the first section (401) composed of a material having a first thermal expansion coefficient along the longitudinal axis (410); a second section (402) extending from a second opposing end (404) of the shaft to the joint (405), the second section (402) composed of a material having a second thermal expansion coefficient along the longitudinal axis (410) that is different to the first thermal expansion coefficient.

A rotary device for a nuclear power facility, the rotary device being placed in a circuit for coolant containing radioactive nuclides in the nuclear power facility. The rotary device includes: a casing; and a rotary mechanism provided with, in the casing, a rotor and a rotor shaft that come into contact with the coolant containing the radioactive nuclides passing through the casing. Regarding the casing and the rotary mechanism, at least the rotor and the rotor shaft of the rotary mechanism comprise a low-effective diffusion coefficient alloy having a lower effective diffusion coefficient than a polycrystalline alloy.

An austenitic stainless steel alloy and turbocharger kinematic components are provided. An austenitic stainless steel alloy includes, by weight, about 23% to about 27% chromium, about 18% to about 22% nickel, about 0.5% to about 2.0% manganese, about 1.2% to about 1.4% carbon, about 1.6% to about 1.8% silicon, about 0% to about 0.5% molybdenum, sulfur in an amount of less than about 0.01%, phosphorous in an amount of less than about 0.04%, and a balance of iron, and other inevitable/unavoidable impurities that are present in trace amounts. The turbocharger kinematic components are made at least in part using this stainless steel alloy.

A method (400) for coating a tip (106) of an aerofoil (100) is provided. The method (400) includes depositing a layer of nickel-based gamma/gamma prime chemistry (112) on the tip (106) of the aerofoil (100). The method (400) further includes depositing plurality of abrasive particles (114) on the layer of nickel-based gamma/gamma prime chemistry (112) to form a coating matrix (116). The method (400) further includes heating the tip (106) of the aerofoil (100) at a predetermined temperature in order to perform heat treatment of the coating matrix (116) and increase the strength of the coating (110) on the tip (106) of the aerofoil (100).

A rotor for a turbomachine and a method of manufacturing the same. The method includes providing a lug with a lug body and an interface material disposed on the lug body. The method also includes friction welding the lug to a hub member via the interface material to define a projected structure for an outer radial area of a disc assembly of the rotor. The projected structure is configured to support a first side of a rotor blade of the rotor in cooperation with a second projected structure of the disc assembly supporting a second side of the rotor blade. The lug body and the hub member are made from different materials.

An erosion and CMAS resistant coating arranged on a TBC coated substrate and including at least one porous vertically cracked (PVC) coating layer providing lower thermal conductivity and being disposed over a layer of MCrAlY wherein M represents Ni, Co or their combinations. At least one dense vertically cracked (DVC) erosion and CMAS resistant coating layer is deposited over the at least one PVC coating layer.