Abstract: A cryocooler includes a cold head including a displacer movable in an axial direction, a drive piston connected to the displacer to move the displacer in the axial direction, an expansion chamber formed with the displacer, a piston drive chamber formed with the drive piston, a spool valve including a valve drive chamber, a spool that moves between a first position and a second position in response to a pressure of the valve drive chamber, and a pressure control mechanism configured to control a pressure of the valve drive chamber so that the spool reciprocates between the first position and the second position, and to generate a pressure fluctuation having an opposite phase to the pressure fluctuation in the expansion chamber in the piston drive chamber in synchronization with the reciprocation of the spool.

Abstract: A process of transferring heat from a first relatively cold medium to a second relatively hot medium features rotating a contained amount of a compressible fluid about an axis of rotation, thus generating a radial temperature gradient in the fluid, and heating the second medium by the fluid in a section of the fluid relatively far from the axis of rotation. An apparatus for carrying out the process includes a gastight drum rotatably mounted in a frame, and a first heat exchanger mounted inside the drum relatively far from the axis of rotation of the drum.

Abstract: A system for air-conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer, a first recirculation system designed to remove exhaust air from a first aircraft cabin region and connected to the central mixer, and a second recirculation system designed to remove exhaust air from a second aircraft cabin region and connected to a local mixer. A control device is designed to control the second recirculation system to reduce an air volume flow being removed from the second aircraft cabin region when shifting from a first operating state (e.g., normal operation) to a second operating state (e.g., defined operating situations such as when quick cooling is desired). The air volume being removed from the first aircraft cabin region may be increased accordingly in the second operating state.

Abstract: An environmental control systems (ECS) for an aircraft in which bleed air is cooled with ram air, the ECS may include a ram air controller configured to control a rate of ram air flow responsively to a desired temperature of bleed air at a bleed air outlet and a bleed air controller configured to control a rate of bleed air flow responsively to a temperature lower than the desired temperature of the bleed air at the bleed air outlet. Collectively the two controllers may provide a minimizing of ram air usage for cooling the bleed air.

Abstract: Embodiments of a heat transfer apparatus, and related methods, involve at least one boundary wall defining a first flow path through a neck portion, a first heat source external to and in thermal communication with the boundary wall, and a working fluid (e.g., a first fluid component with a second fluid component entrained therein). The neck portion may be shaped such that at least a portion of the second fluid component impinges upon at least a portion of the boundary wall as the working fluid flows therethrough, whereby heat is transferred from the first heat source to the working fluid through the boundary wall.

Abstract: The present disclosure relates to a method and an arrangement for expanding a gas stream comprising carbon dioxide, CO2. The method includes: removing CO2 from a process gas to produce a CO2 lean gas stream comprising residual CO2; monitoring a temperature of the gas stream downstream of an expander; controlling a pressure of the gas stream downstream of the expander by means of a pressure controller; and overriding the pressure controller when the temperature downstream of the expander is below a predefined minimum temperature; whereby deposition of solid CO2 from the residual CO2 in the gas stream is avoided. The disclosure also relates to a gas cleaning system and a power plant, such as an oxy-combustion power plant, associated with the arrangement.

Abstract: An aircraft adaptive power thermal management system for cooling one or more aircraft components includes an air cycle system, a vapor cycle system, and a fuel recirculation loop operably disposed therebetween. An air cycle system heat exchanger is between the air cycle system and the fuel recirculation loop, a vapor cycle system heat exchanger is between the vapor cycle system and the fuel recirculation loop, and one or more aircraft fuel tanks are in the fuel recirculation loop. An intercooler including a duct heat exchanger in an aircraft gas turbine engine FLADE duct may be in the air cycle system. The system is operable for providing on-demand cooling for one or more of the aircraft components by increasing heat sink capacity of the fuel tanks.

Abstract: An air-cycle air conditioning system and method, using an automotive turbocharger as the core of the system, was designed and tested. Effects on engine performance were minimized while maximizing the possible cooling possible and also minimizing weight and space requirements. An unmodified automotive turbocharger was tested initially as a baseline in a Reversed-Brayton Cycle air cooling system. A second air-cycle machine, assembled from commercial turbocharger components chosen individually to optimize their performance for cooling purposes, was tested to improve the overall cycle efficiency. An optimized air-cycle air conditioning system was tested on an internal combustion engine to simulate more realistic operating conditions and performance.

Abstract: A system for improving the thermal efficiency of a thermal control loop in which refrigerant after compression and condensation is applied to an evaporator employs a subsidiary counter-current heat exchange intercepting refrigerant flow to maintain the quality of the refrigerant by exchanging thermal energy between the input flow and the output flow from the evaporator. The same principle is effective, with particular advantage when small connections have to be made, in systems using mixed phase media and using the concept of direct energy transfer with saturated fluid.

Abstract: This invention relates to an aircraft air conditioning system with at least one compressor, a first conduit connected with a pressure side of the compressor and at least one cooling unit provided downstream of the compressor. A second bypass conduit is connected with the pressure side of the compressor to conduct at least part of the compressed air around at least one cooling unit and has a throttle for varying air flow therethrough.

Abstract: In a method for controlling an aircraft air conditioning system, a correlation is established between a plurality of values of a process air mass flow supplied to an air conditioning unit of the aircraft air conditioning system and the fuel consumption of the aircraft. A correlation is also established between a plurality of values of an ambient air mass flow which is used to cool the process air mass flow supplied to the air conditioning unit of the aircraft air conditioning system and the fuel consumption of the aircraft. The process air mass flow and the ambient air mass flow are controlled in dependence on a predetermined cooling capacity of the aircraft air conditioning system such that the fuel consumption of the aircraft is minimized.

Abstract: Method for converting thermal energy at a low temperature into thermal energy at a relatively high temperature by means of mechanical energy, and vice versa, with a working medium which runs through a closed thermodynamic circulation process, wherein the circulation process has the following working steps: —reversible adiabatic compression of the working medium, —isobaric conduction away of heat from the working medium, —reversible adiabatic relaxing of the working medium, —isobaric supply of heat to the working medium, and wherein the increase or decrease in pressure of the working medium is produced during the compression or relaxing, increasing or decreasing the centrifugal force acting on the working medium, with the result that the flow energy of the working medium is essentially retained during the compression or relaxing process.

Abstract: Apparatus to control a temperature of a device that includes: a thermal head adapted to be thermally contacted to the device; a combined path to the thermal head; a first path maintained at a first temperature and connected to the combined path; a second path maintained at a second temperature different from the first temperature and connected to the combined path; a third path connected to the combined path; a pump assembly operable to circulate thermal transfer fluid: from the thermal head, through each of the first, second and third paths, from each of the first, second and third paths, through the combined path, and from the combined path, to and through the thermal head; and a valve assembly operable to control amounts of thermal transfer fluid that flow into the first and second paths, thereby controlling the temperature.

Abstract: A humidity control system (10) is disclosed which includes a refrigerant circuit (60). The refrigerant circuit (60) includes first and second absorbent-supported heat exchangers (61, 62) and performs a refrigeration cycle by the circulation of refrigerant. In addition, in the refrigerant circuit (60), the circulation direction of refrigerant is reversible. The first and second heat exchangers (61, 62) are disposed in a casing (11). In the humidity control system (10), the distribution route of air is changed such that a first air stream is passed through either one of the first and second heat exchangers (61, 61) that is functioning as an evaporator while a second air stream is passed through the other heat exchanger that is functioning as a condenser. A compressor (63), an expansion mechanism (65), and a four-way valve (64) in the refrigerant circuit (60) are disposed together with the heat exchangers (61, 62) in the casing (11).

Abstract: A method for controlling a flow of refrigerant to an evaporator (1) arranged in a refrigeration system is disclosed. The refrigeration system further comprises an expansion valve (12) and a compressor, the expansion valve (12), the evaporator (1) and the compressor being arranged in a refrigerant flow path having refrigerant flowing therein. The method comprises the steps of increasing an opening degree of the expansion valve (12), thereby increasing a flow of refrigerant to the evaporator (1) sufficiently to substantially eliminate a dry zone (3) of the evaporator (1), decreasing the opening degree of the expansion valve (12) after a period of time has lapsed, and repeating the steps of increasing and decreasing the opening degree of the expansion valve (12). Thus, the opening degree of the expansion valve (12) is ‘pulsated’. This causes the superheat value of refrigerant leaving the evaporator (1) to ‘toggle’ between a zero level and a low, but positive, level.

Abstract: A method of manufacturing a frozen or partially-frozen product which method includes: a) providing a liquid material in a substantially sealed vessel; b) subjecting liquid material to a negative pressure; and c) subjecting the liquid material, whilst under the negative pressure, to a temperature substantially less than 0° C.

Abstract: A system and method is provided for capturing a carbonous gas and using the captured carbonous gas for cooling purposes. For example, a system may include a carbon capture system configured to collect a carbonous gas from a syngas, and a cooling system having the carbonous gas in a coolant circuit.

Abstract: A method and a system for the preparation of compressed air having a heat exchanger (system heat exchanger) which is in communication with a pressure source on the inlet side on the compressed air side and which is in communication with a system or unit on the outlet side on the compressed air side which is to be supplied with cooled compressed air and including at least one heat exchanger (air conditioning system heat exchanger) which is in communication with a pressure source on the inlet side on the compressed air side and which is in communication with additional components of an aircraft air conditioning system on the outlet side on the compressed air side.

Abstract: A rigid or semi-rigid demister pad is positioned between an air turbine and an inertial water removal device such as extractor in an air conditioning system for an aircraft. The demister pad comprises packed fibers or strands whose diameter typically ranges from approximately 10 or fewer microns to approximately 280 microns. The demister is capable of catching very small droplets discharged from the air turbine that coalesce into larger droplets that exit the demister pad and enter an adjacent water removal device downstream from the pad to separate the larger water droplets from the stream of air. This avoids using a water separator containing a coalescer bag that requires frequent maintenance and is sensitive to dirt and freezing. The demister can operate at freezing temperature, is not dirt-sensitive and requires no maintenance.

Abstract: A system for air conditioning at least one partial region of an aircraft comprises an air providing device for providing air to be supplied to a region of the aircraft to be ventilated at a desired temperature and pressure. A supply air duct is connected at a first end to the air providing device. A second end of the supply air duct is connected to an air inlet which opens near the floor into the aircraft region to be ventilated. A control device is set up to ensure that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a speed that the air is distributed near the floor in the aircraft region to be ventilated and rises at heat sources present in the aircraft region to be ventilated, and that the air provided by the air providing device enters the aircraft region to be ventilated via the air inlet at such a temperature that a desired ambient temperature is set in the aircraft region to be ventilated.

Abstract: A compressor, a radiator, an expander, and an evaporator are connected in series to define a refrigerating cycle. A bypass circuit that bypasses the expander, an on-off valve disposed in the bypass circuit, and a controller C1 for controlling an opening of the on-off valve are provided in the refrigerating cycle. During defrosting, the controller C1 controls the on-off valve so that a refrigerant may flow through the bypass circuit, thereby avoiding reduction in the amount of flow of the refrigerant during defrosting and preventing the defrosting operation from being prolonged.

Abstract: A method and apparatus is shown for increasing the efficiency of a fuel driven turbine generator, and in particular, a system comprising a turbo compressor and turbo expander device that produces super chilled air that can be mixed with ambient air to produce relatively cool dry inlet air that can be introduced under pressure into the fuel driven generator to increase the efficiency thereof. A separation compartment with a passageway extending normal to the travel direction of the chilled air is preferably used to remove ice particles and particulates from the cool inlet air to avoid damage to the turbine blades. Additional efficiency increasing apparatuses such as heat exchangers and steam driven turbine generators and chillers that use heat from the compressors, as well as thermal energy storage systems that store chilled water produced by releasing compressed air are contemplated.

Abstract: A method of cooling a data center can include: extracting compressed air from a storage vessel or process stream, expanding the air to lower a pressure of the air, with the ratio of the pressure of air after expansion to the pressure of air before expansion being the critical pressure ratio, defining choked flow, providing a constant mass rate of cooling air, thus lowering a temperature of the air; and dispersing the expanded air through a heat sink onto a microprocessor or other heat generating component of a server or a storage device, thus cooling the microprocessor or the other heat generating component of the server or the storage device.

Abstract: The invention described herein represents a significant improvement in the efficiency of heating and cooling applications such as buildings. An air or water sourced fluid extraction process on the front end of an open loop heat pump system is provided. The extracted fluid is compressed in a heat pump compressor to achieve a heating function but no expansion of the compressed fluid is performed. The compressed fluid is instead stored for a subsequent cooling process or transported to a different location. After storage or transport, the compressed fluid is expanded to achieve a cooling function which requires no energy input other than the transport or storage. Once the fluid is expanded, it can be released back to the environment, can be converted to electricity in the case of hydrogen, or can be transported or stored for a heating application at a different place or time.

Abstract: An apparatus and method for automatic operation of a refrigeration system to provide refrigeration power to a catheter for tissue ablation or mapping. The primary refrigeration system can be open loop or closed loop, and a precool loop will typically be closed loop. Equipment and procedures are disclosed for bringing the system to the desired operational state, for controlling the operation by controlling refrigerant flow rate, for performing safety checks, and for achieving safe shutdown. The catheter-based system for performing a cryoablation procedure uses a precooler to lower the temperature of a fluid refrigerant to a sub-cool temperature (?40° C.) at a working pressure (400 psi). The sub-cooled fluid is then introduced into a supply line of the catheter. Upon outflow of the primary fluid from the supply line, and into a tip section of the catheter, the fluid refrigerant boils at an outflow pressure of approximately one atmosphere, at a temperature of about ?88° C.

Abstract: A machine air supply system includes a primary air circuit and a secondary air circuit and a single compressor for supplying compressed air to both circuits. In an embodiment, the compressor is a reciprocating piston compressor having a primary air circuit including a compression chamber of the compressor and a secondary air circuit including a crankcase chamber of the compressor. In an aspect, the compressor may be a multi-cylinder compressor.

Abstract: An inventive air conditioning system includes an air conditioning pack for receiving pressurized air and converting the pressurized air into conditioned air for an aircraft. Pressurized air is provided by a compressed air supply system that is fluidly connected to the air conditioning pack for providing air to the air conditioning pack. The compressed air system includes a compressor driven by an electric motor. The electric motor is commanded by a controller to provide pressurized air when needed. In particular, the controller commands the electric motor based upon a desired conditioned airflow that is to be provided by the air conditioning pack. For high altitude aircraft, applications, a diffuser is used to increase the efficiency of the compressor within the compressed air supply system.

Abstract: A gas pressure reducer comprising at least one gas expansion device for allowing the gas to expand and thereby reduce in pressure, and at least one means for raising the temperature of the gas in the vicinity of the gas expansion device and wherein the means for raising the temperature of the gas comprises a liquid or solid fuel heater or a liquid fuelled engine.

Abstract: A closed loop cooling system and method for an oil-free electric motor of an aircraft cabin air compressor. A closed-loop fan, which may be coupled to a motor rotor opposite a compressor impeller, circulates the required cooling air in a closed loop through a motor stator and bearings, a motor cooler, and a ducting used to complete the flow circuit via a ram air cooled heat exchanger. The cooling air may be pressurized to cabin pressure. The system and method of the present invention eliminates the possibility of contaminating trace amounts of oil in cabin supply air.

Abstract: A heat dissipation system, including an air compressor mechanism disposed in a body shell, which has an inlet and enlarged outlet. An air is directed to the air compressor mechanism, and compressed. Upon exhaling the body shell, a compressed air will rapidly expand and a heat generated from electrical appliances installed thereunder will be reduced to a functional level. The system is applicable for the heat dissipating to computer devices, electronic appliances, or heat producing devices.

Abstract: A cold cryostorage assembly includes a storage chamber in which specimens can be cryo-preserved. Specimen samples are stored in a vacuum so as to minimize the risk of sample contamination. The specimen samples can be cooled and warmed at adjustable controlled rates which best suit the specimen samples in question. The storage chamber can be cooled to temperatures as low as ?269° C. without the use of a cryogen that contacts the specimen sample containers. The specimens can be inserted into and/or removed from the storage chamber at individually programmed variable rates by means of an automated specimen-handling component of the assembly. The specimen handling component of the assembly can be operated by remote control, or even over the internet. The storage chamber is evacuated, and in any case, it does not involve the use of a cryogen in direct contact with sample containers in the storage chamber. The cryogen is contained inside of closed heat exchangers that are disposed in the storage chamber.

Abstract: A thermal management system for an aircraft is provided. The aircraft includes a primary air conditioning system which compresses and cools outside air to create inside air. The inside air pressurizes the internal volume of the aircraft and ventilates a first object in the internal volume. An exhaust exhausts a portion of the inside air to allow more outside air to be drawn into the aircraft. A cooler cools a coolant which in turn controls temperature of at least two objects in the internal volume.

Abstract: An air conditioning system for an aircraft in which cabin air is recirculated and mixed with cold air from an air conditioning machine which includes at least an expansion turbine over which warm pressurised air is expanded and cooled, and wherein the system includes a heat exchanger in which a heat load from hot cabin air and/or a hot avionics system is exchanged with the warm pressurised air prior to the pressurised air being expanded by the expansion turbine.

Abstract: The following invention relates to an air conditioning system, in particular for aircraft, comprising at least one heat exchanger, arranged in a ram air duct, for cooling compressed air by means of a fluid, and comprising at least a first and a second air cycle machine which at the compressed-air end are connected to the heat exchanger. A particularly compact, reliable, redundant and economical arrangement is achieved in that the heat exchanger comprises at least one first heat exchanger unit and a second heat exchanger unit, of which one each is connected at the compressed-air end to one of the air cycle machines, and in that ram air outlet ducts which are fluidically separate from each other are provided, of which one is connected to the first heat exchanger unit and another is connected to the second heat exchanger unit.

Abstract: A method of, and apparatus, for, controlling the temperature of pressurized air such as bleed air from a gas turbine engine, wherein the air is passed through a heat exchanger to exchange heat with coolant air which is caused to flow through the heat exchanger by operation of an ejector device powered by some of the pressurized air, the supply of the pressurized air to the ejector device is controlled to control the flow of coolant air and hence control the temperature of the pressurized air downstream of the heat exchanger.

Abstract: The method of processing air prior to separation of such air into gaseous components, the steps that include: first compressing a stream of air and cooling the compressed air, to enable water separation and removal from the stream, to provide a dry stream of air; then further compressing the dry air stream and cooling the compressed dry air stream to enable removal of contained remanent water; then expanding the cooled air stream in an expansion stage which extracts work from the expanding stream; then passing the expanded air stream to a separator operating to remove water from the stream, thereby producing dry air passed to a component gas separation stage or stages.

Abstract: The present invention is directed to an apparatus for cooling, a liquid in a portable container. The apparatus comprises a housing having a top end and a bottom end. The bottom end is adapted to attach to the portable container. A can of compressed gas can be within the housing. The can of compressed gas can have a release valve to expel the compressed gas. A heat exchanger can be around an exterior surface of the can. The heat exchanger can be adapted to absorb heat from a warm liquid.

Abstract: A closed loop cooling system and method for an oil-free electric motor of an aircraft cabin air compressor. A closed-loop fan, which may be coupled to a motor rotor opposite a compressor impeller, circulates the required cooling air in a closed loop through a motor stator and bearings, a motor cooler, and a ducting used to complete the flow circuit via a ram air cooled heat exchanger. The cooling air may be pressurized to cabin pressure. The system and method of the present invention eliminates the possibility of contaminating trace amounts of oil in cabin supply air.

Abstract: A cycle-side system (20) is formed by duct connecting a compressor (21), a heat exchanger (30), a demoisturizer (22), and an expansion device (23) in that order. The compressor (21) draws in room air and supply air for ventilation and compresses the same. The compressed air exchanges heat with exhaust air for ventilation in the heat exchanger (30), thereby being cooled. Water vapor in the cooled, compressed air is removed in the demoisturizer (22). The demoisturizer (22) is provided with a separation membrane and separates water vapor in the compressed air without the occurrence of condensation. Thereafter, the compressed air is expanded in the expansion device (23) to change into low-temperature air. The low-temperature air is supplied into a room. On the other hand, the heat exchanger (30) is fed exhaust air cooled in a humidifying cooler (41).

Abstract: A method of, and apparatus, for, controlling the temperature of pressurized air such as bleed air from a gas turbine engine, wherein the air is passed through a heat exchanger to exchange heat with coolant air which is caused to flow through the heat exchanger by operation of an ejector device powered by some of the pressurized air, the supply of the pressurized air to the ejector device is controlled to control the flow of coolant air and hence control the temperature of the pressurized air downstream of the heat exchanger.

Abstract: An air conditioning system for an aircraft in which cabin air is recirculated and mixed with cold air from an air conditioning machine which includes at least one expansion turbine over which warm pressurised air is expanded and cooled, and wherein the system includes a heat exchanger in which a heat load from hot cabin air is exchanged with the warm pressurised air prior to the pressurised air being expanded by the expansion turbine, further including a condenser heat exchanger in which recirculating cabin air is used to cool and promote water removal from the warm pressurised air before it is expanded by the expansion turbine.

Abstract: An air cycle air conditioning system for treating air contained within a passenger compartment of a vehicle. The system includes a compressor for receiving air from the passenger compartment and compressing the air, thereby producing charged air. Further, an expander is provided selectively coupled to the compressor for expanding the air and cooling the air communicated to the passenger compartment. The system further includes an air-to-air heat exchanger that cools the air received by the compressor-and supplies cooled charged air to the vehicle's engine.

Abstract: The present invention relates to an electrically driven aircraft cabin and ventilation and environmental control system. The system includes at least one inlet for capturing ram air, an electrically driven compressor for pressurizing the ram air, and a thermal conditioning subsystem for thermally conditioning the pressurized ram air. The system further includes a subsystem for removing undesirable moisture from the thermally conditioned ram air.

Abstract: An aircraft air conditioning air supply system is provided that includes a primary propulsion turbine engine having a bleed valve providing pressurized air. A ram air inlet provides ram air. A super charger includes a spool with at least two turbines mounted thereon driven by the pressurized air from the engine. At least one compressor is connected to the turbines, preferably mounted on the same spool as the turbines, and receives the ram air. The turbines drive the compressor and compresses the ram air for use by an air conditioning pack. The supercharger provides compressed air to an air conditioning pack that conditions the compressed air and distributes the refrigerated air throughout the aircraft. The number of turbines and compressors for the super charger is selected by matching the specific speeds of the compressors and turbines.

Abstract: In an air conditioner, air extracted from engine is fed through a main air flow path into cabin after being cooled by a cooling device. This extracted air is fed into the cabin through an auxiliary air flow path. The air within the cabin flows out through an outflow air flow path. A plurality of adsorption sections are constituted by an adsorption agent that adsorbs molecules contained in the air and releases adsorbed molecules by being raised in temperature to more than the temperature thereof on adsorption. By control of an air flow changeover mechanism by a controller, each of the adsorption sections is changed over between a condition connected with the auxiliary air flow path and a condition connected with the outflow air flow path.

Abstract: An electronic control for an air conditioning system is provided. The system includes first and second air conditioning packs located in the air craft remote from one another. Each pack includes a pack controller in the same location as the pack. The pack controllers produce operating instruction signals to the packs for instructing the packs to produce conditioned air in response to a reference signal. A supervisory controller is centrally located in aircraft, preferably in the electronics equipment bay, and is connected to each of the pack controllers. The supervisory controller produces the reference signal to the pack controllers. In addition to controlling the operation of the packs, the pack controllers preferably include prognostics for monitoring the packs and diagnosing problems. The distributed electronic controllers of the present invention utilized for the packs may similarly be applied to the zone trim system and the engine air bleed valves.

Abstract: This invention is directed to an external loop nonfreezing heat exchanger for cooling a heat transfer fluid with cryogenic fluid. The cryogenic fluid is first pre-vaporized with the spent cryogenic fluid. The heat transfer fluid is then cooled by the vaporized cryogenic fluid instead of the cryogenic fluid feed directly.

Abstract: The present invention relates to a self-cooling liquid container for rapidly cooling the liquid in a container by evaporation of coolant gas. A self-cooling liquid container having a liquid cooling device for cooling a liquid in a container by evaporation of a coolant gas comprises a coolant gas bottle inside the liquid container containing a coolant gas stored under pressure, a nozzle tube communicating with the coolant gas bottle and rounding outside the coolant gas bottle, a mounting support for mounting and supporting the coolant gas bottle inserted into the liquid container, and having a switching portion for selectively releasing the coolant gas, and a cap coupled with the mounting support outside of the container and selectively opening and closing the switching portion.

Abstract: This invention relates to an air-conditioning system for passenger aircraft for conditioning humidity-containing air under excess pressure for air-conditioning a passenger aircraft cabin, comprising at least one compressor and two expansion turbines, where in accordance with the invention a droplet coalescing device with succeeding water separator is disposed between the expansion turbines.

Abstract: A cabin air temperature control system includes cooling recirculated air. A first air circuit includes an intake that receives air from outside the cabin and then conditions the air to bring it closer to a desired cabin temperature before the air is introduced into the cabin. A second air circuit recirculates air from the cabin and then reintroduces it back into the cabin. The second circuit includes an air cooling assembly, comprising a heat exchanger, that is selectively used to cool the recirculated air before it is reintroduced into the cabin. A bypass flow arrangement is provided to selectively direct the recirculated air through the air cooling assembly or to simply recirculate it back into the cabin depending on the current temperature adjustment needs.