The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first heat exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

An environmental control system for providing a conditioned medium to one or more loads of an aircraft includes a compressing device including a compressor and a turbine operably coupled to the compressor. The turbine is arranged downstream from the compressor relative to a flow of first medium. At least one power turbine is operably coupled to the compressor. The at least one power turbine is configured to receive a flow of a second medium, and the flow of second medium includes a cabin discharge air.

The liquid level of a liquid supply type compressor including a gas-liquid separator is dynamically monitored. A liquid supply type gas compressor includes a compressor body of a liquid supply type; a gas-liquid separator that separates a liquid from a compressed gas, which is discharged, to store the liquid; a liquid piping system that supplies the liquid stored to the compressor body; an internal pipe that extends in an internal space of the gas-liquid separator, and includes at least two hole portions, of which disposition positions are different from each other in a height direction, on an internal space side to communicate with the liquid piping system; and a detector that detects a pressure or a temperature of a fluid flowing through the liquid piping system. At least one of a determination as to whether or not the pressure or the temperature detected by the detector is more than a first set value set in advance and a determination as to whether or not the pressure or the temperature detected by the detector is less than a second set value which is set in advance to be less than the first set value is performed to determine which one of the gas and the liquid is the fluid flowing through the liquid piping system.

A filtering apparatus formed by a plurality of channel systems. Each of the channel systems include an inlet port formed on an inlet side of the plate; no more than one outlet port formed on an outlet side of the plate; and a channel formed in the plate, the channel coupled to the inlet port and to the outlet port, wherein the ratio of the product of the capture area of the inlet ports of a channel system with the first transmissivity associated with the inlet ports to the product of the capture area of the outlet ports of a channel system with the second transmissivity associated with the outlet ports is greater than one. The channel system is configured to interact with objects of interest on a scale which is smaller than a value several orders of magnitude larger than the mean free path of an object of interest. Some plate embodiments are configured to interact with particles, such as air molecules, water molecules, or aerosols. Other plate embodiments are configured to interact with waves or wavelike particles, such as electrons, photons, phonons or acoustic waves.

An airplane is provided. The airplane includes an environmental control system coupled to an engine and an inlet. The engine provides a bleed. The inlet provides a fresh medium. The environmental control system includes a compressing device comprising a compressor and a turbine. The environmental control system also includes a moisture removal circuit that separately removes moisture from each of the first and second mediums prior to combining the first medium and the second medium to form mixed air.

A gas refrigerating machine comprising: an input (2) for gas; a recuperator (10); a compressor (40) having a compressor input (41), the compressor input (41) being coupled to a first recuperator output (12); a heat exchanger (60); a turbine (70); and a gas output (5), wherein the gas refrigerating machine is configured as open system, and wherein the gas refrigerating machine is configured such that a working medium in at least one element of the group of elements comprising the recuperator (10), the compressor (40), the heat exchanger (60) and the turbine (70), is the gas, and wherein the input (2) is arranged at a first portion of a housing (100) of the gas refrigerating machine where the input (2) and the gas output (5) are configured, wherein the gas output (5) is arranged at a second portion of the housing (100) of the gas refrigerating machine, and wherein the first portion is arranged above the second portion in an operating direction in which the gas refrigerating machine is set up for an operation of the gas refrigerating machine.

An air cycle machine includes an air inlet connected to an air cycle compressor. Air downstream of the air cycle compressor is connected to be delivered across a first turbine. The air cycle compressor is driven by the first turbine through a shaft. Air downstream of the first turbine is connected to a second turbine. The second turbine is connected to deliver air downstream. The second turbine is connected with a second shaft to drive a fan rotor. The fan rotor delivers a source of air across a primary heat exchanger positioned between the inlet and the air cycle compressor. The air cycle compressor and the first turbine are formed of a metal. The second turbine and the fan rotor are formed of non-metallic materials.

A cooling system for a vehicle includes an inlet configured to receive a medium and a compression device including a shaft, a compressor connected to the shaft and having a compressor outlet, an electric motor connected to the shaft and configured to drive the compressor, and a turbine connected to the shaft and also configured to drive the compressor upon receipt of a compressed medium (to create an expanded medium). The turbine includes a turbine inlet and a turbine outlet. A load heat exchanger is connected to the turbine outlet and receives expanded medium therefrom. The load heat exchanger has a load heat exchanger outlet. At least one cooling heat exchanger has a heated flow inlet connected to the compressor outlet, a heated flow outlet connected to the turbine inlet, and a cooling flow inlet that receives a cooling medium from the load heat exchanger outlet.

An additively manufactured component includes an outer shell, the outer shell enclosing a space therein. An inner lattice structure is in the space of the outer shell. Interspaces are formed in the inner lattice structure. A method of forming an additively manufactured component includes evacuating a chamber in which the additively manufactured component will be formed, and forming in the chamber layer by layer an outer shell enclosing a core. The core includes a lattice structure with interspaces formed in the lattice structure.

Apparatus for treating gas having: a compressor with a compressor input and a compress output; a heat exchanger with a first heat exchanger input, a first heat exchanger output, a second heat exchanger input and a second heat exchanger output, wherein the heat exchanger is configured as gas-gas heat exchanger; a turbine with a turbine input and a turbine output, wherein the compressor output is connected to the second heat exchanger input and wherein the second heat exchanger output is connected to the turbine input; an input interface for coupling the compressor input and the first heat exchanger input to a gas supply; and an output interface for coupling the turbine output and the first heat exchanger output to a gas exhaust.