A ceramic matrix composite blade may include an airfoil and a root. A protective metallic layer may be coupled to the root. The protective metallic layer may be plasma sprayed on the root. A portion of the protective metallic layer may be removed.

A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100 F. higher than that of the second material. A gas turbine engine is also disclosed.

A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge. One of the leading and trailing edge portions also includes the platform. The leading edge portion is formed of a first material distinct from a second material forming the trailing edge portion. The first material has an operating temperature capability at least 100F higher than that of the second material. A gas turbine engine is also disclosed.

A variable-pitch vane system for a gas turbine engine includes a plurality of vanes and a synchronization ring assembly operably connected to the plurality of vanes. The synchronization ring assembly includes a first synchronization ring, a second synchronization ring and a bridge bracket connecting the first synchronization ring to the second synchronization ring. The bridge bracket includes a first face sheet, a second face sheet, a honeycomb core located between the first face sheet and the second face sheet, a first attachment feature located at a first end of the bridge bracket at which the first synchronization ring is secured, and a second attachment feature located at a second end of the bridge bracket at which the second synchronization ring is secured.

Embodiments of the disclosure provide a shaft assembly including: a first shaft extending through a compressor and a turbine of the turbomachine; a second shaft coupled to the first shaft through a load coupling component; a generator mounted on the second shaft, wherein the turbine drives the generator; a plurality of mono-type low-loss bearings supporting the first and second shafts at the compressor, turbine, and generator; and a plurality of rotating blade structures within the compressor and the turbine of the turbomachine, wherein at least one of the plurality of rotating blade structures in the compressor includes a low-density material, and at least one of the plurality of rotating blade structures in the turbine includes the low-density material.

A method of fabricating an abradable coating of varying density, and an abradable coating of varying density. The method comprises the following steps: providing a substrate having a first portion and a second portion; depositing a first precursor material on the first portion of the substrate compressing the first precursor material between the substrate and a first bearing surface; sintering the first precursor material as compressed in this way in order to obtain a first abradable coating portion on the first portion of the substrate, and possessing a first density; depositing a second precursor material on the second portion of the substrate; and compressing the second precursor material between the substrate and a second bearing surface.

A non-contact seal assembly is provided. The non-contact seal assembly includes a plurality of seal shoes arranged about a centerline in an annular array, the seal shoes including a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end; a seal base circumscribing the annular array of the seal shoes; and a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the seal shoes with the seal base, where the seal base and the plurality of spring elements are formed of a first material and the plurality of seal shoes are formed of a second material, where the first and second materials are joined together and the second material has a density lower than the first material.

Coating systems for components of a gas turbine engine, such as a compressor case, are provided. The coating system can include a dense layer disposed along the inner surface of the compressor case as well as an abradable, top coat disposed along the dense layer. The combination of dense layer and abradable top coat can reduce the occurrence of galvanic corrosion of the coating system and thereby increase the lifetime of the coating system and preserve blade clearances within the compressor. Methods are also provided for applying the coating system onto a compressor case.

A fan blade for an aircraft engine, including a leading edge, a trailing edge, a suction side, a pressure side and a blade tip, is provided. The fan blade has a large-area elastomer layer which takes up at least 20% of the surface of the suction side of the fan blade.

A flow rotor (1), in particular a turbine wheel, having a wheel core (2) and an outer part (3) which surrounds the wheel core (2) and is connected thereto. The wheel core (2) and the outer part (3) are constructed from different materials.