An intermediate casing includes an inner wall having an outer surface extending along a longitudinal axis, the outer surface having a first profile in a first plane, an outer wall having an inner surface a second profile in the first plane, and first through fourth arms each extending radially. The outer and inner surfaces and the first and second arms delimit a first cavity, the first cavity having a first area and the outer and inner surfaces being separated by a first distance. The outer and inner surfaces and the third and fourth arms delimit a second cavity, the second cavity having a second area and the outer and inner surfaces being separated by a second distance. The first and second profiles are such that the first area is substantially identical to the second area and the first distance is different from the second distance.

A steam turbine according to the present invention comprises: a shaft which rotates about the rotation axis thereof; a plurality of moving blades which extend in the radial direction from the outer peripheral surface of the shaft and which are arranged along the circumferential direction; a casing main body which covers the shaft and the moving blades from the outer peripheral side; a plurality of stationary blades which are arranged on the inner circumferential surface of the casing main body; and a substance supply unit which supplies, to the surfaces of the moving blades and/or the surfaces of the stationary blades, a film forming substance that is hydrophobic, wherein the substance supply unit has a storage unit, a supply passage which is formed inside the casing and through which the film forming substance flows, and discharge units which are formed inside the moving blades and/or the stationary blades and which guide the film forming substance to the surfaces.

A steam turbine according to the present invention comprises: a shaft which rotates about the rotation axis thereof; a plurality of moving blades which extend in the radial direction from the outer peripheral surface of the shaft and which are arranged along the circumferential direction; a casing main body which covers the shaft and the moving blades from the outer peripheral side; a plurality of stationary blades which are arranged on the inner circumferential surface of the casing main body; and a substance supply unit which supplies, to the surfaces of the moving blades and/or the surfaces of the stationary blades, a film forming substance that is hydrophobic, wherein the substance supply unit has a storage unit, a supply passage which is formed inside the casing and through which the film forming substance flows, and discharge units which are formed inside the moving blades and/or the stationary blades and which guide the film forming substance to the surfaces.

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features.

A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features.

A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

The present invention relates to a housing arrangement for a turbomachine, comprising a support element, which is configured to bear a shaft, and a housing, which is centered at the support element. The housing is composed of an inner housing and an outer housing fastened at the support element, the housings being connected to each other by at least one connecting strut. A press fit is provided between the support element and the inner housing, in order to center the inner housing at the support element.

The present invention relates to a housing arrangement for a turbomachine, comprising a support element, which is configured to bear a shaft, and a housing, which is centered at the support element. The housing is composed of an inner housing and an outer housing fastened at the support element, the housings being connected to each other by at least one connecting strut. A press fit is provided between the support element and the inner housing, in order to center the inner housing at the support element.