Abstract: A refrigeration arrangement for traction vehicles includes a first closed circuit configured as a compression refrigeration machine containing a refrigerant as a first carrier medium, evaporator and condenser. The evaporator absorbs heat into the first circuit. The condenser transfers heat from the first circuit. The first circuit is coupled, via the evaporator, to a closed second circuit containing a liquid second carrier medium for heat transport. The second circuit, for cooling, takes heat and transfers it to the second carrier medium. The heat is conveyed, by the second carrier medium, to the evaporator for transfer to the first circuit. The first circuit is coupled, via the condenser, to a closed third circuit containing a liquid third carrier medium for heat transport. The third circuit causes heat from the first circuit, transferred into the third circuit by the condenser, to be transferred to surroundings with heat from traction systems.

Abstract: A mine cooling and dehumidifying system includes a compressor, a gas-liquid separator, an evaporator, a condenser and an expansion valve. The evaporator is in an air supply well, and the condenser is in a return air well; the compressor, the gas-liquid separator and the expansion valve are all between the air supply well and the return air well; an inlet of the compressor is connected to a refrigerant outlet of the evaporator through the gas-liquid separator, and a refrigerant inlet of the evaporator is connected with an outlet of the expansion valve; an inlet of the expansion valve is connected with a refrigerant outlet of the condenser, and a refrigerant inlet of the condenser is connected with an outlet of the compressor. In the present disclosure, by vapor compression type refrigeration cycle, the downhole air heat is transferred to the return air and then discharged to the ground.

Abstract: An air cycle machine for an environmental control system for an aircraft includes at least one turbine configured to receive and extract work from a first medium and a third medium. A compressor is configured to compress a second medium and a shaft mechanically couples the at least one turbine and the compressor. A mixing point is located downstream of at least one turbine. A mixture of the first medium and the third medium generated at the mixing point is provided to another component of the environmental control system.

Abstract: The invention relates to a fluid-compression device including a compression chamber comprising a movable piston, the device comprising a first end housing a first end of the compression chamber, the device comprising a second end housing a second end of the compression chamber, the piston being translatable between the first and second ends of the compression chamber, the device comprising a regeneration pipe connecting the first and second ends of the compression chamber and including a regenerator, the device comprising a supply pipe comprising an upstream end intended to be connected to a source of fluid to be compressed and a downstream end opening into the first end of the compression chamber, the supply pipe comprising a valve assembly, the device comprising a pipe for discharging the compressed fluid comprising an upstream end connected to the compression chamber and a downstream end intended to be connected to a receiver of the compressed fluid, the discharge pipe comprising a valve assembly, characte

Abstract: A turbo compressor assembly of a cooling machine has a shaft mounted in a common housing with first and second radial dynamic gas bearings and a thrust bearing. A supply stream of working gas supplied to the first radial bearing is formed between an inner wall of a compressor body and the shaft, and a supply stream of working gas from a turbo expander supplied to the second radial bearing and to the thrust bearing is formed between an inner wall of a turboexpander body and the shaft. The first radial dynamic gas bearing is sealed towards the electric motor rotor by a shaft seal. A surface in a shape of an annulus is formed on the shaft between the first radial bearing and the shaft seal, the annulus perpendicular to an axis of the shaft and functioning as a piston for balancing an axial force acting on the shaft.

Abstract: A cooling apparatus includes a cold plate made of a metal, a casing, a pump, a ground wire, and a conductive component. The pump includes a motor to drive an impeller, and a circuit board to control the motor. The circuit board is connected to the ground wire. The conductive component electrically connects the cold plate to the ground wire.

Abstract: An environmental control system includes an ambient air conduit and a bleed air conduit, an electric compressor connected to the ambient air conduit and a mechanical compressor connected to the electric compressor. The electric compressor is supported for rotation independent of the mechanical compressor. A turbine is operatively connected to the mechanical compressor, the turbine connected to both the ambient air conduit and the bleed air conduit to provide conditioned air to a conditioned air conduit. Computer program products and methods of providing conditioned air to conditioned air loads are also described.

Abstract: An air conditioning system is provided. The system includes an air compressor configured to pull in ambient air and generate pressurized air from the ambient air, a blower, a generator, and a turboexpander. The turboexpander is coupled to the air compressor, the blower, and the generator. The turboexpander includes a turbine wheel configured to generate boosted air from the pressurized air from the air compressor, and an expander wheel coupled to the turbine wheel and configured to: a) generate expanded and cooled air from the boosted air, and b) create mechanical work in the generator in order to generate electricity for powering the air compressor and/or an electrical apparatus. The blower is configured to receive the expanded and cooled air from the turboexpander and deliver the expanded and cooled air to an environment.

Abstract: A turbo-Brayton refrigeration machine (11) includes a first circulation path (L1) in which a first refrigerant circulates, a second circulation path (L2) in which a second refrigerant which is a cooling target circulates, a subcooler (22) disposed over the first circulation path (L1) and the second circulation path (L2) and configured to have a single heat-exchanging unit, and an expansion turbine (21) positioned on a primary side of the subcooler (22) in the first circulation path (L1), in which the pressure ratio of the expansion turbine (21) is the pressure ratio at which the outlet temperature of the expansion turbine (21) is higher than a freezing point of the second refrigerant.

Abstract: A refrigeration unit with dynamic air cooling is described. It includes a centrifugal compressor with an electric drive, whose outlet is connected to a working element, whose outlet is connected to the inlet of a turbine. The turbine is connected to an electrical energy generator, where the outlet of the turbine is directed towards a wall-pipe heat exchanger. The heat exchanger is connected to a pump. Between the centrifugal compressor and the working element there is a pipe-wall exchanger of the air-air type, to which a fan is connected. The working element of the unit has a cylindrical hollow profile comprising helical recesses with a substantially oval shape.

Abstract: In a coolant circulation system of a vehicle, a connecting unit is connected to a coolant line of a vehicle circulating through a battery of the vehicle. When connected to the coolant line, the connecting unit allows coolant to be discharged from the vehicle or be introduced into the coolant line. A supply unit includes a cooling tank in which the coolant is stored or circulates and a heating tank. The cooling tank includes an evaporation core, and the heating tank includes a condensing core. The evaporation core and the condensing core are connected to the coolant line on which a compressor, an expansion valve, and an external condenser are provided. When the connecting unit is connected to the coolant line, the supply unit is configured to supply the coolant from the cooling tank or the heating tank to the coolant line of the vehicle, cooling or heating the battery.

Abstract: A coolant circulation system for a vehicle performs heat management of a high voltage battery provided in an electric vehicle. The coolant circulation system is configured to be connected to the high voltage battery of the electric vehicle to combine coolant managed outside the electric vehicle and coolant circulated in the high voltage battery of the electric vehicle with each other to supply cooled or heated coolant to the high voltage battery. Thus, the charging efficiency is improved through temperature management of the high voltage battery when the high voltage battery is charged.

Abstract: According to one embodiment, a rotary compressor includes a compression mechanism unit. When H is the length of a middle shaft part, Hp is the length of a bearing hole, Dp is the inner diameter of the bearing hole, Dc is the outer diameter of a crank part, Dm is the outer diameter of the middle journal part, C1 is the axial length of a first chamfered part provided to a middle shaft part-side end edge of the crank part, C2 is the axial length of a second chamfered part, C3 is the axial length of a third chamfered part, and C4 is the axial length of a fourth chamfered part, Dp is larger than Dc and Dm, and the relationships of [Equation 1] H?Hp, [Equation 2] H>Hp?C1?C2??{square root over ((Dp2?Dc2))}, and [Equation 3] H>Hp?C3?C4??{square root over ((Dp2?Dm2))} are all satisfied.

Abstract: A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.

Abstract: A regenerative filter system includes a regenerative filter material arranged to filter air recirculated from an aircraft interior and means for passing a regeneration air stream through the regenerative filter material to regenerate the filter material by removing adsorbed contaminant therefrom, whereby the means for passing the regeneration air stream comprises means for expanding air exhausted from the aircraft interior and using the expanded air to drive a compressor for compressing and conditioning ram air to provide the regeneration air stream to the filter material.

Abstract: A nucleic acid loading device, including a housing, a carrying module, a motion module, a liquid circuit module and a control module. The motion module includes a support platform, first and second driving mechanisms, and a carrying member. The liquid circuit module is configured to control a reagent to flow into and out of a reactor. The control module is connected with the motion module and the liquid circuit module, and the control module is configured to control the first and second driving mechanisms, the liquid circuit module and the temperature control unit. A first face of a semiconductor cooler heats or refrigerates during operation, providing heat for an accommodating seat through a heat conducting body such that the reactor can be at different ambient temperatures. The cooperation between the motion and liquid circuit modules may achieve automation and industrialization of loading a sample into the reactor.

Abstract: An aircraft environmental control system includes means for mixing and conditioning bleed air from a bleed air input and recirculation air from an aircraft interior to provide mixed, conditioned air to the aircraft interior. The system also includes a first contaminant removal device and a second contaminant removal device arranged in a path of at least part of the recirculation air, prior to the means for mixing and conditioning, and a valve (SV1) arranged to alternate flow of recirculation air through the first and second contaminant removal devices.

Abstract: A ventilation fan includes a shaft, a rotor, a motor housing, a bearing housing, and an air bearing. The shaft has a shaft body that extends between a first shaft end and a second shaft end. The shaft body defines a first port and a bore. The rotor is disposed about the shaft. The motor housing is disposed about the shaft and is axially spaced apart from the rotor. The bearing housing is disposed about the shaft. The air bearing is disposed proximate the second shaft end and is disposed between the bearing arm and the second shaft end.

Abstract: A system includes a first fluid flow path configured to condition a pressurized medium and deliver the pressurized medium to one or more loads. The first fluid flow path including an air cycle machine. A second fluid flow path is configured to circulate a working fluid. The second fluid flow path includes a heat exchanger thermally coupled to the first fluid flow path. Within the heat exchanger, heat extracted from the pressurized medium is transferred to the working fluid. The second fluid flow path additionally includes a turbine operably coupled to the air cycle machine, a condenser, and a pump operable to circulate the working fluid through at least a portion of the second fluid flow path. The turbine is rotationally driven by expanding the working fluid across the turbine.

Abstract: This disclosure describes novel hybrid energy storage systems for providing short-term and long-term storage and delivery of electricity generated by any energy source including renewable energy sources such as solar energy and wind energy. The hybrid energy storage systems described herein have a higher overall real-world efficiency than energy storage systems currently available.

Abstract: A vehicle comprising a compressor and a manifold physically and fluidly coupled to the compressor.

Abstract: A compressor includes three suction pipes. A first center of a first suction pipe, a second center of a second suction pipe, and a third center of a third suction pipe are positioned at vertices of a triangle. A first distance between the first center and a center of a compressor main body is smaller than a second distance between the second center and the center of the compressor main body and a third distance between the third center and the center of the compressor main body. A second flow path cross section and a third flow path cross section are positioned on opposite sides of a center connection line sandwiched therebetween. The first suction pipe is connected to a suction port which is at an uppermost position among three suction ports provided in a case.

Abstract: A waste-heat recovery system includes a compressor main body; a gas piping, a waste-heat-recovery heat exchanger, a circulation circuit, and a tank with a water inlet piping and a water outlet piping that stores water that exchanges heat with the heat medium by connecting to the circulation circuit. The waste-heat recovery system also includes an inlet valve, a circulation pump, and a gas temperature sensor that detects the temperature of the compressed gas by arranging in the gas piping. The waste-heat recovery system also includes a water temperature sensor that detects the temperature of the water in the tank, and a control device that controls the inlet valve and the outlet valve according to detection temperature of the gas temperature sensor and the water temperature sensor.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit and the at least one dehumidification system.

Abstract: In the two-cylinder hermetic compressor, a first compression mechanism unit includes a first cylinder and a first piston, and a second compression mechanism unit includes a second cylinder and a second piston. A main bearing is disposed on one surface of the first cylinder, and an intermediate plate is disposed on another surface of the first cylinder. The intermediate plate is disposed on one surface of the second cylinder, and an auxiliary bearing is disposed on another surface of the second cylinder. A shaft is constituted by a main shaft portion which has a rotor attached thereto and is supported by the main bearing, a first eccentric portion having a first piston attached thereto, a second eccentric portion having a second piston attached thereto, and an auxiliary shaft portion supported by the auxiliary bearing. The diameter of the auxiliary shaft portion is set larger than the diameter of the main shaft portion.

Abstract: A method of operating a RAM inlet header (RIH) is provided. The method includes determining a temperature of RAM air flows in a body through which RAM air flows from an inlet toward a heat exchanger, determining a temperature of excess air for use in an environmental control system (ECS) and, in an event the temperature of the excess air is less than the temperature of the RAM air flows, directing a curtain of the excess air from a nozzle body and along a wall of the body into flows of the RAM air and toward the heat exchanger.

Abstract: A cryogenic refrigerator system with heaters is constructed in modular form to serve as a portable servicing system to warm up and then cool down a target object by circulating a gaseous cryogen through a target object cryostat without moving the target object or breaking its vacuum. The main module is a refrigerator cryostat containing a fan that circulates gas through one or more heat exchangers which can warm or cool the gas by heaters and by one or more GM or Brayton cycle expanders. Additional components including one or more compressors, a gas charge and vent assembly, a control system, gas lines, power lines, and vacuum jacketed transfer lines can be assembled in the main module or additional modules. An example is a system that can be wheeled through a hospital to service a MRI cryostat.

Abstract: An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine.

Abstract: Disclosed is a method for ventilating a ram air channel for a vehicle—in particular an aircraft—including at least one heat exchanger. The ram air channel is provided with a jet pump including a plurality of compressed air inlets connected to a plurality of separate compressed air sources of the vehicle, and a plurality of compressed air outlet nozzles. At least two nozzles are independently connected to at least two separate compressed air sources of the vehicle.

Abstract: An integrated fuel and environmental control system is provided and includes a first heat exchanger in which fuel and oil thermally communicate and a second heat exchanger disposable in a super-cooled fluid flow. The second heat exchanger is receptive of at least one of the fuel and oil from the first heat exchanger whereby the at least one of the fuel and oil thermally communicate with the super-cooled fluid flow. The second heat exchanger is also receptive of a second fluid whereby the second fluid thermally communicates with the super-cooled fluid flow downstream from the thermal communication of the super-cooled fluid flow with the at least one of the fuel and oil.

Abstract: An exhaust system for an aircraft galley chiller is provided. The exhaust system includes a galley having a chiller that includes an inlet, a condenser fan inlet, a condenser fan outlet proximate to chiller inlet, and a first flow of air through the condenser, an air ventilation outlet conduit that includes a second flow of air therethrough, and an ejector pump. The ejector pump includes a first airflow inlet, a second airflow inlet and an airflow outlet, wherein the first airflow inlet is coupled in flow communication with the condenser fan outlet, the second inlet is coupled in flow communication with the air ventilation outlet conduit. As the second airflow increases, the first velocity increases in a direction away from the galley chiller facilitating a decrease in temperature at the condenser fan inlet.

Abstract: A system comprising a cryogenic engine system and a refrigeration system, wherein the cryogenic engine system and the refrigeration system are mechanically and/or thermally coupled with each other. The refrigeration system is driven by the cryogenic engine system and the cryogenic engine system enhances cooling of the refrigeration system.

Abstract: A method and apparatus for cooling compressed air include the following. Compressed air is introduced into a vortex tube where cold air and warm air are generated. The cold air and warm air are introduced into a pressure vessel where the temperature and moisture of the compressed air are adjusted. The adjusted compressed air is fed to a downstream side of the pressure vessel. Before the generated cold air and warm air are introduced into the pressure vessel, the warm air is introduced into a pre-pressure vessel disposed at an upstream side of the pressure vessel. The cold air is introduced into a cooling tube or cooling chamber which is disposed inside the pre-pressure vessel which is disposed at the upstream side of the pressure vessel. The warm air is adjusted by cooling. The adjusted warm air is introduced into the pressure vessel from the pre-pressure vessel together with the cold air.

Abstract: A pressure regulating system that is suited to regulate the pressure of a gas includes a regulating device suited to regulate the pressure of a first gas stream, provided with an inlet for the gas at a supply pressure and with an outlet for the gas at a regulated pressure that is lower than the supply pressure; a vortex tube suited to receive a gas stream through an inlet, separate it into a hot portion and a cold portion and deliver the hot and cold portions through corresponding outlets; a heat exchanger coupled with the vortex tube in order to heat the first gas stream before it flows into the regulating device; a recovery duct suited to collect a first portion of the first gas stream at a collection point located downstream of the heat exchanger and to convey it to the inlet of the vortex tube.

Abstract: An aircraft air conditioning system comprising an ambient air supply line with a first end connected to an ambient air inlet and a second end connected to a mixing chamber. A first electrically driven ambient air compressor in the ambient air supply line compresses the ambient air flowing therethrough. A first ambient air branch line branches off from the ambient air supply line upstream of the first ambient air compressor and rejoins the supply line downstream of the air compressor. A second ambient air compressor in the first ambient air branch line compresses the ambient air flowing therethrough. A cabin exhaust air line has a first end connected to an air conditioned aircraft area. A cabin exhaust air turbine in the exhaust air line is driven by the exhaust air flowing through the cabin exhaust air line and is coupled to drive the second ambient air compressor.

Abstract: An on-board aircraft inert gas system includes a source of hydrocarbon, a source of gas comprising oxygen, and a first fluid flow path between the source of gas comprising oxygen and an inert gas output. A reactor is disposed along the first fluid flow path that reacts oxygen and hydrocarbon from the fuel tank gas space to produce an oxygen-depleted gas. A heat exchanger condenser removes some water from the oxygen-depleted gas. A water-permeable gas membrane separator receives the oxygen-depleted gas from the heat exchanger and outputs dried oxygen-depleted gas.

Abstract: A combination includes a selectively driven fan and a bypass flow passage for bypassing the fan. The bypass flow passage communicates with a first check valve to allow air to flow from the bypass passage to a downstream location. A second check valve allows air driven by the fan to pass into a return passage and return to an inlet of the fan in the event that the discharge pressure from the fan overcomes a spring force associated with the second check valve. A heat exchanger pack and an environmental control system for use on an aircraft, and a method are all also disclosed.

Abstract: 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.

Abstract: Closed thermodynamic cycle systems, such as closed Brayton cycle systems, with regenerative heat exchangers are disclosed. Embodiments include dual regenerators and regenerators with buffer tank systems. Regenerators may be used instead of or in addition to one or more recuperators within the systems, and may be used as a means of gas-gas heat exchange for different streams of a working fluid.

Abstract: An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets.

Abstract: An environmental control system (ECS) pack is provided including a primary heat exchanger, a secondary heat exchanger, and an air cycle machine. The air cycle machine includes a compressor and a turbine. The compressor is fluidly coupled to an outlet of the primary heat exchanger and to an inlet of the secondary heat exchanger. The outlet of the secondary heat exchanger is fluidly coupled to the turbine. A first conduit connects the outlet of the primary heat exchanger and the inlet of the secondary heat exchanger. The first conduit includes a first valve. A second conduit connects the outlet of the secondary heat exchanger to an air load. The second conduit includes a second valve.

Abstract: A mist cooling system that includes a casing and a liquid inlet. The casing is configured to receive a liquid flow from a source through the liquid inlet and then provide the liquid flow as a mist to a housing of a motor so as to increase a cooling of the motor and prevent any failure of the motor due to overheating.

Abstract: A Brayton cycle type refrigerating apparatus using multiple stages of compressors and having a good response without reduction in efficiency due to change in heat load of the object to be cooled is provided. The Brayton cycle type refrigerating apparatus includes on a refrigerant line on which multiple stages of compressors are arranged in series. The apparatus also includes a temperature sensor for detecting heat load of an object to be cooled and a buffer tank provided between a low pressure line and a high pressure line. A flow rate of the refrigerant in the refrigerant line is controlled by controlling opening degrees of valves to adjust the cooling capacity.

Abstract: A method of controlling an outlet temperature of a heat exchanger of an aircraft includes operating an air cycle machine at a first operating speed. The air cycle machine is operatively coupled to an air cycle machine bypass valve at a first position. The air cycle machine is fluidly connected to a first heat exchanger disposed adjacent to a second heat exchanger. In response to a second heat exchanger outlet temperature less than a second heat exchanger outlet temperature threshold while the aircraft is operating at an altitude less than an altitude threshold, the method moves the air cycle bypass valve from the first position toward a second position.

Abstract: It is a purpose for the invention to provide a rotating device (107) to generate heat, cold and pressure from the outlet at the rotation axis, by centrifugation pressurized fluid in that it include at least two under-supported U-channel structures (107) where one of the channels (104, 105) from each U-channel structure (107) toward the periphery (107) is in thermal contact, forming a heat exchanger (106) where one of the channels (105) contains a compressible cooling fluid which develops heat from the centrifugal compression in the channel (105), and the heat is transferred to a heating fluid with a lower temperature in the second channel (104) in heat exchanger (106) toward the periphery (107) where heat exchanging ceases, and the U-channels (107) is connected to its inlet—(101, 102) and outlet channels (111, 112) at the rotation axis for the transport of said fluid through the U-channels (104, 105, 108, 109) via the periphery (107), which after the outlet (111) for heating fluid is heat-exploited, and cooli

Abstract: The invention relates to a compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system comprising a process air supply line which is designed to supply process air generated by a process air source to a compressor. A detection device is designed to detect a characteristic signal for the temperature of the process air flowing through the process air supply line. A turbine is designed to drive the compressor. A cooling device is disposed in a process air line connecting the compressor to the turbine and is designed to cool the process air coming out of the compressor and flowing through the process air line in the direction of the turbine. Downstream of the cooling device a connecting line branches off from the process air line and opens into the process air supply line. A control device is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device.

Abstract: An environmental control system, includes an air cycle machine for conditioning an interior space with cooling air, the air cycle machine including a fan coupled to a shaft that rotates about a shaft axis, the fan being located at a distal end of the air cycle machine; a speed sensor module having a speed sensor for sensing a rotational speed of the shaft; wherein the speed sensor module includes an outer portion having a first bore aligned on the shaft axis, an intermediate portion having a second bore aligned on the shaft axis, and an inner portion aligned on the shaft axis; and a diffuser assembly including a cylindrical assembly for ducting a first portion of the cooling air to an inlet side of the fan and for communicating a second portion of the cooling air directly to a discharge side of the fan without passing the inlet side.

Abstract: A method for operating an air-conditioning system for an aircraft includes compressing ambient air with a compressor driven by a shaft in communication with a motor and a turbine. The method includes forwarding the compressed air to an aircraft cabin for circulation and removing circulated compressed air from the aircraft cabin. The method also includes forwarding the circulated compressed air to the turbine, depressurizing the circulated compressed air in the turbine and capturing energy created by depressurizing the circulated compressed air.

Abstract: The apparatus has a cooling arrangement with an expander/compressor system, condenser and evaporator primarily for air conditioning. An external heat source is provided for transfer of heat to the expander housing. For example, this heating medium is an electrical heat source in thermal contact with the outer side of the expander housing. Alternatively, the expander is provided inside an externally heated liquid buffer tank.

Abstract: An aircraft system for improved cooling efficiency comprises at least one air conditioning pack, coupled to an aircraft, having at least one air compression device powered by at least one power source and having an air compression device inlet. The system further comprises at least one air flow path for redirecting a first portion of a first volume of aircraft interior outflow air from an aircraft interior to the air compression device inlet. The air flow path includes a shutoff valve to enable the air flow path during ground operation of the aircraft and to disable the air flow path for flight operation of the aircraft. The air compression inlet mixes the first volume of aircraft interior outflow air with a second volume of aircraft exterior inflow air to form an air mixture. The air conditioning pack conditions and circulates the air mixture into the aircraft interior.