A variable geometry turbine is disclosed comprising: a housing; a turbine wheel supported in the housing for rotation about an axis; a movable wall member; a cavity provided in the housing; and an inlet passageway extending radially inwards towards the turbine wheel. The movable wall member comprises a generally annular wall and radially inner and outer flanges extending axially from the generally annular wall, inner surfaces of the generally annular wall and radially inner and outer flanges defining an interior surface of the movable wall member. The cavity is suitable for receipt of the radially inner and outer flanges of the moveable member, the movable wall member being axially movable relative to the housing to vary the extent to which the radially inner and outer flanges of the moveable member are received in the cavity.

Assemblies and methods for directing a flow of air through a compressor section of a gas turbine engine are disclosed. A method includes receiving the flow of air over a strut extending radially across a substantially annular gas path of the gas turbine engine, and at least partially confining and modifying a strut wake generated in the flow of air by the strut using one or more variable orientation guide vanes.

An apparatus is provided for an aircraft propulsion system. This apparatus includes a variable area nozzle apparatus. The variable area nozzle apparatus includes a plurality of panels, a plurality of inter-panel members and an actuation system. The panels are arranged circumferentially about an axial centerline. The panels include a first panel and a second panel. The inter-panel members are arranged circumferentially about the axial centerline. The inter-panel members include a first inter-panel member between and connected to the first panel and the second panel. The first inter-panel member is configured from or otherwise includes an elastomeric material. The actuation system is configured to move the panels and the inter-panel members between a restricted flow arrangement and an unrestricted flow arrangement. The actuation system includes a first linkage and a second linkage. The first linkage is coupled to the first panel. The second linkage is coupled to the second panel.

A powered augmented fluid turbine for generating electricity from a fluid in motion comprising: a central annular ducted channel extending between an inlet distribution header and an outlet distribution header, the channel comprising a converging section configured to accelerate the fluid received at the inlet distribution header, a turbine assembly for generating electricity, and a diffuser section configured to decelerate the fluid before it exits at the outlet distribution header; a recycle line for transporting the exiting fluid to the inlet distribution header in a closed-loop configuration, the recycle line comprising a recycle line propulsor controllable by a recycle line controller and a recycle line heat exchanger; and a compressed fluid distribution line configured to pressurize the fluid in motion by transporting a compressed fluid from a compressed fluid source to the inlet and outlet distribution headers, the compressed fluid distribution line controllable by at least one pressure controller.

Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

An aircraft engine, has: an inlet extending circumferentially around a central axis; an annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet; a flow restrictor extending across the annular inlet duct and being movable within the annular inlet duct; an actuator engaged to the flow restrictor and operable to move the flow restrictor; and a controller operatively connected to at least one sensor and the actuator, the controller having a processing unit and a computer-readable medium operatively connected to the processing unit and containing instructions for: receiving a signal indicative of a pressure difference between opposite sides of the flow restrictor; and powering the actuator to move the flow restrictor with the actuator from a first position to a second position offset from the first position as a function of the pressure difference.

A radial compressor has an iris diaphragm mechanism for a pressure-charging device of an internal combustion engine. The radial compressor has a bearing assembly, in which a rotor shaft is rotatably mounted, having a compressor impeller arranged in a compressor housing for conjoint rotation on the rotor shaft and having a fresh air supply channel for carrying a fresh air mass flow to the compressor impeller. The iris diaphragm mechanism is upstream of the compressor impeller, allowing variable adjustment of a flow cross section for the fresh air mass flow for admission to the compressor impeller, at least over a partial region. The iris diaphragm mechanism has a plurality of blades, each having at least one first and one second blade section, wherein an offset is formed between the first blade section and the second blade section of the respective blade.

A valve assembly for a turbine engine includes a valve arranged in an air flow path. The valve has a shaft. The valve is movable between an open position and a closed position. A hydraulic actuator is coupled to the shaft. The hydraulic actuator is configured to utilize fuel as a working fluid. The hydraulic actuator is configured to move the valve between the open position and the closed position.

The present invention is related to the housing (60) of an exhaust turbine (32) of a turbocharger comprising a first volute (61) and a second volute (62), each of the volutes (61,62) ending in respective first and second guide tongues (64,66). The gap between the first guide tongue (64) and turbine wheel is smaller than the gap between the second guide tongue (66) and turbine wheel. This tongue asymmetry allows for control of the pulse amplitude emitted when a blade of the turbine wheel passes by each respective tongue. Moreover, by increasing the wheel-to-tongue distance of only the second guide tongue (66) durability requirements can be met.

A centrifugal compressor includes: a housing including an intake flow path; a compressor impeller disposed in the intake flow path; an accommodation chamber formed upstream of the compressor impeller in the housing; a movable member disposed in the accommodation chamber and configured to be movable between a retracted position where the movable member is retracted from the intake flow path and a protruding position where the movable member protrudes from the accommodation chamber into the intake flow path, the protruding position being located closer to the intake flow path with respect to the retracted position, and a contacting portion and a non-contacting portion provided on an accommodation chamber opposing surface of the accommodation chamber, the accommodation chamber opposing surface being positioned upstream of the movable member, the contacting portion being contactable with the movable member, the non-contacting portion being non-contactable with the movable member.