Abstract: A rotatable engine component, coating and method of coating the rotatable component includes a substrate, a transitional zone applied to the substrate, and an abradable zone applied to the transitional zone. During operation of an engine in a turbine, the abradable zone is consumed upon contact with a static portion of the engine preventing damage to the rotatable component.

Abstract: A rotatable engine component, coating and method of coating the rotatable component includes a substrate, a transitional zone applied to the substrate, and an abradable zone applied to the transitional zone. During operation of an engine in a turbine, the abradable zone is consumed upon contact with a static portion of the engine preventing damage to the rotatable component.

Abstract: A coating system and process capable of providing erosion and corrosion-resistance to a component, particularly a steel compressor blade of an industrial gas turbine. The coating system includes a metallic sacrificial undercoat on a surface of the component substrate, and a ceramic topcoat deposited by thermal spray on the undercoat. The undercoat contains a metal or metal alloy that is more active in the galvanic series than iron, and electrically contacts the surface of the substrate. The ceramic topcoat consists essentially of a ceramic material chosen from the group consisting of mixtures of alumina and titania, mixtures of chromia and silica, mixtures of chromia and titania, mixtures of chromia, silica, and titania, and mixtures of zirconia, titania, and yttria.

Abstract: A multi-part cast component for a turbine engine includes a first component section having a main body portion including at least one cooling flow passage section, and a second component section having a main body including at least one cooling flow passage section. The first and second component sections are joined along a parting line to form a turbine engine component with the at least one cooling flow passage section of the first component section aligning with the at least one cooling flow passage of the second component section to form a cooling flow channel.