An air cycle machine is provided. The air cycle machine can be included an environmental control system of an aircraft. The air cycle machine can include a turbine comprising a plurality of inlet gas flow paths, a compressor driven by the turbine from a shaft, and a fan driven by the turbine from the shaft.

An airplane is provided. The airplane includes a compressing device. The compressing device includes a turbine with a first inlet and a second inlet. The turbine provides energy by expanding mediums. The first inlet is configured to receive a first medium of the mediums. The second inlet is configured to receive a second medium of the mediums. The compressing device includes a compressor and a motor. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode. The motor provides a supplementary energy to the compressor

An air cycle machine is provided. The air cycle machine can be included an environmental control system of an aircraft. The air cycle machine can include a turbine comprising a plurality of inlet gas flow paths, a compressor driven by the turbine from a shaft, and a fan driven by the turbine from the shaft.

A system is provided. The system includes a first medium at a first pressure, a second medium at a second pressure, and a medium conditioning sub-system. The medium conditioning sub-system includes a compressor, a first heat exchanger, a second heat exchanger, and a turbine. The turbine receives the first medium and the second medium.

A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

The present invention relates to a method for designing a flow channel for a turbomachine, in particular a gas turbine that comprises a guide vane cascade having a plurality of guide vanes, which are distributed in the peripheral direction, and flow passages, each of which is bounded by two successive guide vanes, and a support rib arrangement having at least one support rib, wherein a design of one of the flow passages is adapted to this support rib, that it is situated downstream of, in order to reduce a pressure loss and/or a vibrational stimulation.

This invention relates to a turbocharger (210). More specifically, the invention relates to an axial-entry type turbocharger, where the exhaust gases are directed to meet the turbine wheel at least front-on, having a variable volume for controlling pressure, allowing for a substantially uniform pressure and uniform velocity to act simultaneously on and around the turbine wheel, while enabling the volume of the turbocharger to be adjusted under predetermined set pressure conditions. The turbocharge includes: a turbine housing defining a substantially axial primary flow duct, a primary turbine wheel (216) mounted along such primary flow duct (214), and a diverter (218) for diverting flow passing thereover into a primary annular flow path directed to impinge the primary turbine wheel (216). The turbine housing of the turbocharger defines a secondary flow duct (222) for directing some flow to: (i) impinge the primary turbine wheel (216); and/or (ii) bypass the primary turbine wheel (216). A secondary flow duct gate (223) controls flow through the secondary flow duct (222) and is movable between a closed position, wherein under low pressure conditions flow is restricted from flowing through the secondary flow duct (222), and an open position, wherein flow though the secondary flow duct (222) is enabled such that operative flow passes through both the primary and the secondary flow ducts (216, 222) under high pressure conditions. The turbocharger further includes at least one compressor coupled to the primary turbine wheel (216) via a primary transmission thereby to transmit drive from the primary turbine wheel (216) to the compressor.

A steam turbine system 1 includes a steam turbine 10 including a plurality of rotor blades 16; a first mixed steam supply pipe 21 that supplies the steam, which is supplied from a steam supply source 40 capable of supplying the steam with fluctuating pressure, to an upstream stage Sa within the casing 11; a second mixed steam supply pipe 22 that supplies the steam to the second stepped part Sb; an adjusting unit 25 that adjusts a flow rate of the steam supplied to the first stepped part Sa and the second stepped part Sb; and a control unit 30 that controls the adjusting unit 25 on the basis of a differential pressure between a pressure P0 of the steam supplied from the steam supply source 40 and a pressure in the first stepped part Sa.

An impulse turbine of a turbine device includes a cylindrical body having an axial hole, and a blade unit arranged to surround the periphery of the body. The blade unit includes a cylindrical base arranged to surround the periphery of the body, and a plurality of unit blades radially arranged in a line along the periphery of the base. Each of the unit blades includes an outlet that discharges fluid, injected onto the unit blade, in a direction different from the fluid spray direction, but does not discharge the fluid toward the other unit blades.

An impulse turbine of a turbine device includes a cylindrical body having an axial hole, and a blade unit arranged to surround the periphery of the body. The blade unit includes a cylindrical base arranged to surround the periphery of the body, and a plurality of unit blades radially arranged in a line along the periphery of the base. Each of the unit blades includes an outlet that discharges fluid, injected onto the unit blade, in a direction different from the fluid spray direction, but does not discharge the fluid toward the other unit blades.