A bearing assembly installed within a turbocharger housing between a turbine wheel and a compressor impeller mounted for rotation together on a turbocharger shaft may include a journal bearing disposed on a corresponding portion of the turbocharger shaft, a thrust bearing having a thrust bearing surface, and a bearing carrier. The bearing carrier may include a carrier body, a carrier body bore extending axially through the carrier body and receiving the journal bearing therein, and a thrust bearing seat on the exterior of the carrier body facing the turbine wheel. The thrust bearing seat may have a complimentary shape to the thrust bearing surface of the thrust bearing, the thrust bearing disposed between the carrier body and the turbine wheel and engaging the thrust bearing seat. The bearing assembly may further include an anti-thrust bearing surface facing the compressor impeller, and an anti-thrust bearing mounted to the anti-thrust bearing surface.

An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.

An outlet guide vane (OGV) structure for a gas turbine engine can comprise a plurality of radially extending guide vanes having inlets and outlets to allow cooling of a medium within the guide vanes.

Counter-rotating turbine of a turbomachine extending about an axis of rotation and comprising an inner rotor having 5 at least one inner moving blade supported in rotation by a first shaft, an outer rotor rotating in an opposite direction to the inner rotor, and comprising at least one outer moving blade supported in rotation by a second shaft coaxial with the first shaft, the first 10 and second shafts extending axially from upstream to downstream of the turbine, the first shaft being guided in rotation by a first bearing disposed between the first shaft and an upstream casing of the turbine, and the second shaft being guided in rotation by a second bearing disposed between the second 15 shaft and said upstream casing of the turbine, the first bearing and the second bearing being disposed upstream of a first stage of the inner rotor.

The present application and the resultant patent provide an exhaust frame for a gas turbine engine. The exhaust frame may include an inner casing extending along a longitudinal axis of the exhaust frame, an outer casing positioned radially outward from the inner casing, a strut extending radially from the inner casing to the outer casing, and a relief groove defined in the inner casing or the outer casing and positioned about the strut. The present application and the resultant patent further provide a method for distributing stress concentrations in an exhaust frame of a gas turbine engine.

Methods, apparatus, systems, and articles of manufacture are disclosed to implement an integrated stator-fan frame assembly. An integrated fan exit stator-fan frame strut assembly for a gas turbine engine includes a fan exit stator portion having an airfoil including a leading edge and a trailing edge, and a fan frame strut portion including a leading edge and a trailing edge, the leading edge of the fan frame strut portion aerodynamically integrated with the trailing edge of the fan exit stator portion.

An assembly includes a gas turbine engine component and a plate. The plate is spaced from a surface of the component and generally conforms to the shape of the surface. The plate and component form a passageway that allows for passage of a secondary gas flow between the component and the plate.

Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.

A gas turbine engine having a bearing housing with a housing cavity and a shaft rotating about a rotation axis. One or more bearings support the shaft. A housing supporting the bearing and defining a chamber axially adjacent to the bearing. A seal assembly is in the housing between the chamber and an exterior of the chamber. The seal assembly includes a seal supported by the housing and surrounding the shaft so as to define an annular gap between an inner surface of the seal and an outer surface associated to the shaft, the gap defining a part of a sealing path of the seal assembly for air to flow from said exterior into the chamber. An impeller rotates with the shaft and located radially inward of the gap relative to the rotation axis, the impeller oriented to drive oil toward the bearing.

The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings and means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.