An orifice pack is provided for delivering pressurized air to a compressor bleed valve of a gas turbine engine. The orifice pack has a diffusion chamber in serial flow communication with a tapering passage and a first outlet passage for venting a first portion of the pressurized air from the diffusion chamber. A second outlet passage branches off from the diffusion chamber at an axial location between the inlet and the tapering passage. The second outlet passage is fluidly connected to the compressor bleed valve for directing a second portion of the pressurized air from the diffusion chamber to the compressor bleed valve.

A turbomachine includes a housing with an e-machine housing. Also, the turbomachine includes a rotating group supported for rotation within the housing. Moreover, the turbomachine includes an e-machine that is configured as at least one of an electric motor and an electric generator, that is operatively coupled to the rotating group, and that includes a stator that is housed within the e-machine housing. Furthermore, the turbomachine includes a thermal bridge member that extends between the stator and the e-machine housing to define a thermal path for heat to transfer from the stator to the e-machine housing. The e-machine housing includes a thermal bridge retainer member that defines an outer boundary of the thermal bridge member.

A turbomachine includes a housing with an e-machine housing. Also, the turbomachine includes a rotating group supported for rotation within the housing. Moreover, the turbomachine includes an e-machine that is configured as at least one of an electric motor and an electric generator, that is operatively coupled to the rotating group, and that includes a stator that is housed within the e-machine housing. Furthermore, the turbomachine includes a thermal bridge member that extends between the stator and the e-machine housing to define a thermal path for heat to transfer from the stator to the e-machine housing. The e-machine housing includes a thermal bridge retainer member that defines an outer boundary of the thermal bridge member.

A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

The present disclosure is directed to turbine engines and systems for active stability control of rotating compression systems utilizing an electric machine operatively coupled thereto. In one exemplary aspect, an electric machine operatively coupled with a compression system, e.g., via a shaft system, is controlled to provide shaft damping for instability fluctuations of the pressurized fluid stream within the compression system. Based on control data indicative of a system state of the compression system, a control parameter of the electric machine is adjusted to control or change an output of the shaft system. Adjusting the shaft system output by adjusting one or more control parameters of the electric machine allows the compression system to dampen instability fluctuations of the fluid stream within the compression system. A method for active stability control of a compression system operatively coupled with an electric machine via a shaft system is also provided.

A forced induction device for an internal combustion engine is provided, which includes a shaft, and a compressor wheel that is threadably mounted to the shaft, and a tool that is configured to engage one or more through bores in the compressor wheel to thread and unthread the compressor wheel onto and off of the shaft. The compressor wheel has a plurality of blades with leading edges that converge at an apex. The apex is aligned with a centerline of the shaft. The tool allows a technician to rotate the compressor wheel relative to the shaft to install or remove the compressor wheel from the shaft without applying any pressure to the blades of the compressor wheel. An associated assembly method is also provided.

An axial piston machine has a swash plate and an adjusting device having an adjusting cylinder and a double-acting adjusting piston which is longitudinally movable in the adjusting cylinder and includes a piston and a piston rod, which is fixedly connected to the piston and is articulated to the swash plate. The joint between the adjusting piston and the swash plate is a movable swivel joint having a joint body receptacle on one part and a joint body on the other part of the adjusting piston and the swash plate. The joint body is closely guided in the joint body receptacle in the direction of movement of the adjusting piston, is rotatable about an axis of rotation running parallel to the pivot axis of the swashplate, and is movable with a directional component perpendicular to the direction of movement of the adjusting piston and perpendicular to the axis of rotation.

An axial piston machine has a swash plate and an adjusting device having an adjusting cylinder and a double-acting adjusting piston which is longitudinally movable in the adjusting cylinder and includes a piston and a piston rod, which is fixedly connected to the piston and is articulated to the swash plate. The joint between the adjusting piston and the swash plate is a movable swivel joint having a joint body receptacle on one part and a joint body on the other part of the adjusting piston and the swash plate. The joint body is closely guided in the joint body receptacle in the direction of movement of the adjusting piston, is rotatable about an axis of rotation running parallel to the pivot axis of the swashplate, and is movable with a directional component perpendicular to the direction of movement of the adjusting piston and perpendicular to the axis of rotation.

The invention relates to a compression system for a gas turbine, in particular for an aircraft gas turbine, wherein the compression system comprises a flow duct. The flow duct includes cross-sectional areas that are aligned perpendicular to the axial direction along the flow duct length and have the respective predetermined sizes, where the inlet cross-sectional area has a size that is 15.3 to 16.1 times a size of the outlet cross-sectional area, and/or a cross-sectional area arranged at a distance of 40% of the flow duct length from the inlet cross-sectional area has a size that is 5.0 to 5.2 times the size of the outlet cross-sectional area.

A diffuser and deswirl system associated with an engine includes a throat ring defining a plurality of passages spaced apart about a perimeter of the throat ring, a plurality of pockets and a support flange. Each passage of the plurality of passages is to receive a working fluid and each pocket of the plurality of pockets is defined about a portion of a respective passage of the plurality of passages. The diffuser and deswirl system includes a plurality of conduits, with each conduit including a first conduit end and a second conduit end opposite the first conduit end. The first conduit end of each conduit is received within and coupled to the pocket of a respective one of the plurality of passages to receive the working fluid, and each conduit includes a mating feature defined between the first conduit end and the second conduit end coupled to the support flange.