A compressor includes: an impeller including a hub and a plurality of blades disposed on an outer surface of the hub; and a housing which houses the impeller. The housing includes: a shroud section facing the outer surface of the hub to form a fluid flow path between the shroud section and the outer surface, and surrounding the impeller; and a casing section formed integrally with the shroud section and supporting the shroud section. The shroud section includes a first resin-based material having a static tensile strength of at least 65 MPa and no more than 200 MPa and a breaking strain of no more than 0.3 mm/mm at a temperature of 100 C. The casing section includes a second resin-based material having a static tensile strength of at least 40 MPa and a breaking strain of at least 0.1 mm/mm at a temperature of 100 C.

A gear assembly support for a gas turbine engine includes a first portion engageable to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support includes a torque reacting portion for transferring torque from the second portion to the first portion, a forward flange disposed forward of the torque reacting portion, the forward flange defining a first interface to the case and an aft flange disposed aft of the torque reacting portion, the aft flange defining a second interface to the case.

A compressor section for use in a gas turbine engine is comprised of a plurality of compressor stages, with each stage including a disk having an inner periphery defining a bore that faces a shaft. A flow path flows in a generally axial direction between the shaft and the bores of each disk. At least one deflector is positioned between a pair of adjacent bores to direct the air flow radially outwardly into a cavity formed between an associated pair of adjacent disks.

A pump device may include a side channel compressor that may include a housing having a conveying chamber and a fluid inlet and outlet. The compressor may include an impeller having blades radially on an outside and which may be mounted rotatably in the housing, the blades lying in the conveying chamber, and a shaft mounted rotatably about an axis of rotation and on which the impeller may be fastened. The conveying chamber may have at least one side channel running in a region of the blades and connecting the fluid inlet and outlet to one another in a circumferential direction. An intermediate region may be formed in the circumferential direction between the fluid inlet and outlet and in which a distance of the blades in an axial direction to the nearest wall may be such that no more than a predetermined amount of fluid flows in the intermediate region.

An air conditioning system for an aircraft is provided. The air conditioning system includes a first rotating component and a second rotating component. The first rotating component includes a compressor and a turbine. The compressor pressurizes a first medium. The first turbine receives a mixture of a second medium and a pressurized form of the first medium. The second rotating component includes a fan.

The invention relates to a conveying device (1) for a fuel cell system (31) for conveying and/or recirculating a gaseous medium, in particular hydrogen, comprising: a side channel compressor (2), the conveying device (1) being driven at least partially by means of a metering valve (6) having a propulsion jet (12) of a pressurized gaseous medium, and the pressurized gaseous medium being fed to the side channel compressor (2) at least indirectly by means of the metering valve (6); a compressor chamber (30) which extends around an axis of rotation (23) in the housing (17) and has at least one circumferential side channel (19); an impeller (14) which is located in the housing (17), is rotatable about the axis of rotation (23) and is driven by the drive (10), the side channel compressor (2) having a housing (17) with a gas inlet opening (20) formed on the housing (17) and a gas outlet opening (22), which are fluidically connected to one another via the compressor chamber (30), in particular the at least one first side channel (19).

According to the invention, the gaseous medium is fed by means of the metering valve (6) to the side channel compressor (2) via the impeller (14), the feed taking place at least almost in the direction of the axis of rotation (23) on the side of the impeller (14) facing away from the drive (10).

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.

A fuel cell system includes a bypass passage, a flow path selector portion that selects a flow path of oxidation gas, and a valve opening adjusting portion that adjusts an opening of a pressure adjusting valve. Until a rotation speed of a rotary shaft reaches a separation rotation speed at which the rotary shaft is separated from an aerodynamic bearing, the flow path selector portion permits flow of the oxidation gas from an electric compressor to a fuel cell stack through a supply passage and flow of the oxidation gas from the electric compressor to a discharge passage through the supply passage and the bypass passage, and the valve opening adjusting portion adjusts the opening of a pressure adjusting valve so that an efficiency of a turbine is maximized by the discharge gas.

According to one embodiment of this disclosure an integrated fuel cell and environmental control system includes a turbo-compressor. The turbo-compressor includes a rotatable shaft, a compressor rotatable with the shaft to generate a flow of compressed air, a motor connected to the shaft, and a turbine connected to the shaft. The system further includes a fuel cell connected to the compressor by a first compressed air supply line that supplies a first portion of the flow of compressed air to the fuel cell. The fuel cell is connected to the turbine by a fuel cell exhaust line that supplies a flow of fuel cell exhaust to the turbine and causes the turbine to rotate. The system further includes an environmental control system connected to the compressor by a second compressed air supply line that supplies a second portion of the flow of compressed air to the environmental control system.

An axleless blade set includes an annular frame and a driving structure. The driving structure serves to drive the annular frame. Blades extend from an inner wall of the annular frame and an outer wall of the annular frame is formed with a plurality of driving sheets. The driving structure serves to drive the driving sheets so as to drive the annular frame and the blades therein to rotate. As a result, wind blows from one side to another side along an axial direction with a large strength. Therefore defects of wind blowing from prior art fans of low strength and dispersing randomly are resolved.