Systems are provided for a crankcase ventilation duct. In one example, the crankcase ventilation duct is integrally formed with a compressor housing wherein surfaces of the compressor housing shape a passage of the crankcase ventilation duct.

A compressor of a turbocharger is provided. The compression pipe of the compressor is connected to the intake pipe thereof by a return flow duct, in which an air recirculation valve is arranged for controlling the return flow of already compressed fresh air. The return flow duct opens into a groove of an intake manifold receptacle of the compressor, and at least one return flow opening adjoining the groove and facing an interior of the intake pipe is arranged on an intake manifold of the intake pipe.

A compressor 1 includes a casing 2 that covers a rotating shaft 4 and an impeller 6 and is provided with a diffuser 66 for guiding the working fluid discharged from the impeller 6 to an outside in a radial direction, a heat exchanger 71 that is cools at least a portion of the working fluid compressed by the impeller 6, a cooling fluid supplying unit 7 that supplies the working fluid cooled by the heat exchanger 71 into the casing 2 as a cooling fluid for cooling a motor 5 disposed in the casing 2, and a cooling fluid circulating unit 8 that discharges the cooling fluid that has passed through the motor 5 to an outside of the casing 2, and supplies the discharged cooling fluid downstream of an outlet 6o of a first impeller 6A and upstream of the diffuser 66.

The invention relates to a diffuser for a radial compressor, comprising a flow channel defined by a first side wall and a second side wall, a diffuser vane ring with a plurality of diffuser vanes that are at least partially arranged in the flow channel, each of the diffuser vanes having a pressure side and a suction side, a plurality of diffuser passages, said diffuser passages being formed between every two adjacent diffuser vanes of the plurality of diffuser vanes, and circuation openings, each circulation opening connecting the flow channel to a diffuser cavity, at least two circulation openings being associated with one diffuser passage, and a circulation opening associated with a diffuser passage being fluidically connected to another circulation opening associated with the same diffuser passage or to a circulation opening associated with another diffuser passage, via the diffuser cavity.

In order for charge air to be conducted with the lowest possible losses in pressure in a turbocharger including a blow-off valve, a flow-guiding element in an inlet region is designed such that neutral zones are formed at the flow openings. The flow openings recirculate charge air from the pressure side to the suction side when the blow-off valve is opened. The flow-guiding element avoids vortices and therefore losses in pressure in the region of the flow openings.

A fan assembly for a gas turbine engine includes a fan rotor having a hub and fan blades protruding from the hub. A fan stator is located downstream of the fan rotor and has vanes extending between radially inner ends and radially outer ends. A flow recirculation circuit has an inlet located downstream of the vanes of the fan stator and adjacent the radially inner ends thereof. The flow recirculation circuit has an outlet located upstream of the inlet. The outlet is located at the hub of the fan rotor and upstream of trailing edges of the fan blades.

Systems and methods are provided that use compressed gas from a tank in an aircraft to avoid and/or recover from a compressor surge. Systems and methods are provided that use compressed gas from a tank to startup a gas turbine engine in an aircraft, where the gas turbine engine is configured as a prime power engine for the aircraft.

A system for delivering a flow stream of a gas to a compressor. A shroud extends from an inlet to the compressor and defines a main inlet passage configured to direct the flow stream from the inlet to the compressor. A communication plenum is separated from the main inlet passage. A port system includes first and second port subsystems that each provide an opening between the main inlet passage and the communication plenum. The first port subsystem is disposed further from the compressor than the second port subsystem. The port system is configured so that a portion of the gas enters or exits the compressor through the second port subsystem, depending on operating conditions of the compressor.

A centrifugal compressor for a chiller includes a casing, an inlet guide vane, an impeller downstream of the inlet guide vane, a motor and a diffuser. The casing has inlet and outlet portions with the inlet guide vane disposed in the inlet portion. The impeller is rotatable about a rotation axis defining an axial direction. A liquid injection passage is provided to inject liquid refrigerant into an area between the impeller and the diffuser. The motor rotates the impeller. The diffuser is disposed in the outlet portion downstream from the impeller with an outlet port of the liquid injection passage being disposed between the impeller and the diffuser. A controller is programmed to control an amount of the liquid refrigerant injected into the area between the impeller and the diffuser.

An assembly is provided for an aircraft propulsion system. This assembly includes an engine core, a bypass duct and a bleed circuit. The engine core includes a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The bypass duct includes a bypass flowpath outside of the engine core. The bleed circuit includes a bleed passage and a flow regulator. The bleed circuit is configured to direct bypass gas through the bleed passage from the bypass flowpath into the core flowpath when the flow regulator is in an open position. The bleed circuit is configured to cutoff gas flow through the bleed passage between the bypass flowpath and the core flowpath when the flow regulator is in a closed position.