A turbocharger (1) includes a wastegate valve (30) supported on the turbine housing (8), and a pneumatic actuator (100) configured to actuate the wastegate valve (30). The pneumatic actuator (100) includes a housing (101) separated into compartments (104, 108) by a separating member (110, 112). The actuator (100) includes a piston (112) disposed in the housing (101) that defines at least a portion of the separating member (110, 112), a piston-biasing spring (120) disposed in the housing (101), a first in let (126) that is in fluid communication with the first compartment (104), the first inlet configured to be connected to a non-zero-pressure fluid source (8), and a second inlet (116) that is in fluid communication with the second compartment (108), the second inlet (116) configured to be connected to a non-zero-pressure fluid source (104).

A fan blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, and extends radially between a root portion and a tip portion. A tip pocket is defined by collapsible external walls of the tip portion, and has a pocket opening at a radially outer face of the tip portion.

A turbine assembly can include a turbine wheel, a shroud component, a turbine housing and a seal that includes a wall and a lower lip that that extends radially outwardly from the wall where the seal is disposed, at least in part, between an outer surface of the shroud component and an inner surface of the turbine housing and where the lower lip is in contact with the turbine housing.

An impeller wheel of a turbocompressor, for rotation about an axis, has an inflow cross-section for inflow of a process fluid into the impeller wheel, an outflow cross-section for outflow of the process fluid from the impeller wheel, a wheel disk that defines a hub-side deflection contour from the axial flow direction into the radial flow direction. Blades are applied to the wheel disk, which define flow channels through the impeller wheel, each blade defining a linear inner track and a linear outer track. A meridional angle is defined for each position of a track as the upstream included angle between a meridional plane through the position and a tangent on the track. So that the flow passes through the impeller wheel with improved efficiency, as far as possible without separation, a local extremum of the meridional angle of the inner track is defined.

A turbopump includes a turbine fed with hot gas, a pump driven by the turbine and fed with liquid fluid, and a hot gas exhaust pipe situated downstream from the turbine. The turbopump includes a bleed-and-injection circuit including a bleeder for bleeding the liquid fluid at the outlet from the pump, a heater for heating the liquid fluid as bled off in this way so as to transform it into gaseous fluid, and an injector for injecting the gaseous fluid into an interface region of the turbopump situated between the pump and the turbine, so as to optimize the flow and temperature conditions of the fluid entering into the turbine cavity in order to eliminate the vibratory phenomena that result from interaction between the fluid and the turbine disk.

A method of manufacturing a turbocharger which allows easy performance of assembly operations of a motor rotor and a stator in a motor overhang structural turbocharger is provided. In a method of manufacturing a turbocharger in which a motor is attached to an end portion of a rotor shaft (15) connected to a compressor portion, the motor includes a cylindrical housing (33), a stator (32) accommodated inside the housing (33), and a motor rotor (31) which is connected to an end portion of the rotor shaft (15) with permanent magnets rotating inside the stator (32), and the method includes a rotor installation step of connecting and attaching the motor rotor (31) to the rotor shaft (15), a housing installation step of fixing and supporting the housing (33) coaxial to the rotor shaft (15), and a stator installation step of using the housing (33) as a guide, and inserting the stator (32) into the housing (33) such that the stator (32) does not directly come into contact with the motor rotor (31) to incorporate the stator (32) into the housing (33).

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

A compressor wheel of a fluid compression device includes a wheel part, a shaft part and a plurality of connection parts. The wheel part includes a main body formed with a through hole, and a plurality of blades protruded from an outer side of the main body. The shaft part is accommodated in the through hole and configured to connect to a rotor shaft. The plurality of connection parts is connected between an inner side of the main body and the shaft part. Wherein, a fluid passage is formed between the inner side of the main body and the shaft part to allow fluid to flow to a rear side of the compressor wheel from a front side of the compressor wheel via the fluid passage.

A lubrication system includes a shaft rotatable about an axis, a lubrication pump configured to supply a lubricant flow to a gear system, and a gear train coupled to the shaft and configured to drive the lubrication pump in a first direction responsive to rotation of the shaft in both the first direction and a second direction. A gas turbine engine and method are also disclosed.