Abstract: An aircraft environmental control system comprising a bleed air or compressed ambient air input and a RAM air input, heat exchanger means for receiving bleed air from the bleed air input and RAM air from the RAM air input and using RAM air to cool the bleed air, and means for providing the cooled bleed air to an interior of the aircraft; the system further comprising means for feeding back exhaust air emitted from the interior of the aircraft to combine with the RAM air to further cool the bleed air or compressed ambient air.

Abstract: Cryogenic refrigeration device comprising a working circuit intended to cool a working fluid circulating in the said circuit, the working circuit comprising, arranged in series in a loop: a compression portion, a cooling portion, a portion with valve(s), an expansion portion and a reheating portion, in order to subject the working fluid to a recuperative working cycle comprising compression, then cooling, then expansion and then reheating to prepare for a new cycle, wherein the compression portion comprises at least one compressor having a linear piston driven by a linear motor, the expansion proportion comprises at least one expander with a linear piston, the portion with valve(s) comprises at least one regulating valve linearly actuated by a linear motor and controlled in order to supply or extract the working fluid from the at least one expansion piston.

Abstract: An environmental control system includes an airflow source, and an air cycle machine in flow communication with the airflow source, and through which an airflow from the airflow source is directed. The air cycle machine includes a compressor and a turbine. A liquid load heat exchanger is located in flow communication with the turbine such that airflow downstream of the turbine exchanges thermal energy with a liquid flow at the liquid load heat exchanger to cool the liquid flow. A liquid load reheater is located upstream of the turbine and upstream of the liquid load heat exchanger. The liquid load reheater is configured such that a thermal energy exchange between the airflow prior to the airflow entering the turbine and the liquid flow prior to the liquid flow entering the liquid load heat exchanger occurs at the liquid load reheater.

Abstract: The present disclosure discloses a compressor, an air conditioning system and a vehicle. The compressor comprises a compression cavity, and further comprises a flash cavity capable of flashing a liquid refrigerant, and a communicating passage that communicates a flash cavity gas outlet of the flash cavity and an enthalpy increasing gas supply port of the compression cavity; the flash cavity is provided with an inlet and a liquid outlet, the inlet of the flash cavity is configured to be communicated with an outlet of a condenser, and the liquid outlet of the flash cavity is configured to be communicated with an inlet of an evaporator. The air conditioning system comprises the compressor, the evaporator, the condenser, a flasher, and various pipelines for connecting the entire system.

Abstract: A two-wheel air cycle machine includes a tie rod defining an axis, a turbine mounted on the tie rod, and a compressor mounted on the tie rod and having a rotor portion and a disk portion with at least one aperture. The air cycle machine further includes a compressor inlet fluidly connecting the compressor and an inlet air source, at least one thrust bearing disposed between the turbine and the compressor, and a compressor end shaft coaxial with the tie rod and abutting the compressor disk portion. The compressor end shaft includes a radially-extending seal disk portion and an axially-extending shaft portion having at least one shaft aperture. The at least one disk aperture and the at least one shaft aperture are fluidly connected by a compressor disk cavity defined by a gap between the tie rod and the compressor disk portion. The at least one disk aperture, the compressor disk cavity, and the at least one shaft aperture at least partially define a compressor inlet flow path.

Abstract: The present invention relates in general to the field of fluid reaction surfaces, and more specifically, to a fluid-foil impeller and method of use. One aspect of the fluid-foil impeller utilizes a plurality of fluid-foil discs that may be of uniform and/or variable thickness and configured to rotate rapidly in series to produce propulsion. Each fluid-foil disc comprises a leading edge, a trailing edge, a chord and a fixed pitch. The fluid-foil impeller may further include a standard or Venturi shroud that is designed to encompass the plurality of fluid-foil discs. The plurality of fluid-foil discs are configured to act in cooperation with the shroud to reduce losses incurred from turbulence and the conversion of mechanical work to fluid movement. Fluid may be acted upon by the plurality of fluid-foil discs and/or shroud, singly or in an array.

Abstract: An environmental control system of an aircraft includes a compressing device having a compressor configured to receive a flow of a first medium and a turbine configured to receive the flow of the first medium from the compressor and a flow of a second medium. The turbine is arranged downstream from the compressor along a flow path of the first medium. A dehumidification system is arranged in fluid communication with the turbine and a bypass valve is operable configured to divert the flow of the first medium around the turbine and at least a portion of the dehumidification system.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a heat exchanger positioned therein and a dehumidification system arranged in fluid communication with the ram air circuit. A plurality of expansion devices is arranged in fluid communication with the ram air circuit and the dehumidification system. At least one of the expansion devices is a simple cycle expansion device.

Abstract: The present disclosure relates to a turbomachine assembly, which includes a shaft, a radial gas expander supported on the shaft between a first bearing and a second bearing, and a compressor supported on the shaft in overhung position adjacent to one or the other of the first and second bearings. The compressor includes a plurality of movable inlet nozzles and the radial gas expander includes a plurality of movable guide vanes.

Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a cooling air tap at a location upstream of the downstream most location. A main turbine section, each of the main turbine section and the main compressor section are mounted within a housing, and each have rotatable components. A first heat exchanger is connected to the cooling air tap. The first heat exchanger is also connected to receive fuel to be supplied to a combustor in the gas turbine engine, and such that the fuel may cool the cooling air in the first heat exchanger. A boost compressor is connected to receive air downstream of the first heat exchanger and connected to deliver the cooling air to at least one of the rotatable components in at least one of the compressor and turbine sections.

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, a dehumidification system arranged in fluid communication with the ram air circuit, and a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a first turbine coupled to one another via a shaft. During operation of the first turbine, work is extracted from a first medium within the first turbine to power the compressor. At an outlet of the first turbine, a temperature of the first medium is above freezing and at least a portion of the moisture within the first medium is condensed.

Abstract: A blower includes an impeller housing, an impeller rotatably secured to the housing and an electric motor. The motor has a motor housing with a central portion and a radially extending portion extending from the central portion, a venturi chamber adjacent the motor housing and opposed to the impeller housing, a stator secured to the central portion of the motor housing, a rotor rotatably secured to the central portion of the housing, and at least one heat generating electrical component secured to the radially extending portion of the motor housing. The impeller housing has a first air pressure therein and the motor housing has a second air pressure therein different that the first air pressure. The venturi housing and the motor housing define a passageway therebetween whereby the difference in air pressure generates air flow within the motor housing to cool the at least one heat generating electrical component.

Abstract: Disclosed is a cooling circuit for cooling a heat load in an aircraft system, having: a compressor; a turbine connected to the compressor by a shaft, the turbine configured to drive the compressor via the shaft when RAM air pressure into a turbine inlet is above a first threshold; and a motor connected to the shaft configured to drive the compressor when RAM air pressure at the turbine inlet is below the first threshold to cause the compressor to draw air into the turbine inlet, through the turbine, a heat exchanger in fluid communication with the heat load, the compressor, and out of a compressor outlet.

Abstract: An aircraft is provided. The aircraft includes a pressurized volume and an air conditioning system. The air conditioning system operates in a first mode or a second mode. The first mode includes when a first medium and a second medium and are mixed and provided to the pressurized volume. The second mode includes when only the first medium is provided to the pressurized volume.

Abstract: Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a VGT cooling system turbine (240) downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) for bypassing the turbine can also be included.

Abstract: Methods and devices for cooling systems (100, 700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a cooling system turbine (240) with variable guide vanes—VGT—and downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) can also be included that bypasses the cooling system turbine (240).

Abstract: A ram air system for an aircraft having an engine and a fuselage with an outer mold line. The ram air system includes an engine air pathway having an opening in the outer mold line defining an engine inlet. The engine air pathway is configured to supply operating air for combustion in the engine. An auxiliary air pathway includes a first intake disposed inside the outer mold line in the engine inlet and a second intake disposed externally to the engine air pathway. The auxiliary air pathway is configured to draw in cooling air to cool ancillary aircraft components from at least one of the first intake and the second intake based on the airspeed of the aircraft.

Abstract: An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component.

Abstract: A compressor module for compressing gas composed of a compressor element with a housing with integrated compressor element cooler; a motor and a gas cooler for cooling the compressed gas originating from the compressor element. The gas cooler includes a primary section through which the gas to be cooled can be guided and a secondary section that is in heat-exchanging contact with the primary section. A first cooling circuit can guide a coolant through the secondary section of the gas cooler or through a section thereof and a second cooling circuit can guide a coolant through the compressor element cooler. The first cooling circuit and the second cooling circuit are joined together in series or in parallel and are guided to a common output.

Abstract: A flow conditioning device for conditioning a wet gas stream having a plurality of liquid droplets and a gas flow is presented. The flow conditioning device includes a first segment including a first convergent section configured to break the plurality of liquid droplets from a first size to a second size. Further, the flow conditioning device includes a second segment coupled to the first segment and including a second convergent section configured to break the plurality of liquid droplets from the second size to a third size.

Abstract: A fan and compressor housing for an air cycle machine includes a fan inlet disposed around a center axis of the housing and having a fan inlet mounting flange, a compressor outlet having a compressor outlet mounting flange, and a compressor inlet having a compressor inlet mounting flange. The fan inlet mounting flange has a pinhole disposed thereon configured to receive a pin from a fan inlet diffuser housing and a fan inlet counterbore configured to receive a mating component from the fan inlet diffuser housing. The compressor outlet mounting flange has a compressor outlet counterbore configured to receive a first mating component from a condenser/reheater. The compressor inlet mounting flange has a compressor inlet counterbore configured to receive a second mating component from the condenser/reheater.

Abstract: A gas turbine engine includes a main compressor section. A booster compressor includes an inlet and an outlet. The inlet receives airflow from the main compressor section and the outlet provides airflow to a pneumatic system. A recirculation passage is between the inlet and the outlet. A flow splitter valve controls airflow between the outlet and the inlet through the recirculation passage for controlling airflow to the pneumatic system based on airflow output from the booster compressor. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

Abstract: Provided is a solvent separation method and a solvent separation apparatus that make it possible to efficiently retrieve the thermal energy possessed by an exhaust atmosphere released in a solvent-removal step to suppress reductions in a temperature of the exhaust atmosphere. In the solvent separation method and the solvent separation apparatus, a vaporized solvent is removed from a gas while heat exchange between the gas within a condensation part and the gas within a dust-collection part is conducted by using a heat exchange part that is placed between the condensation part that introduces the gas into a first direction and the dust-collection part that introduce the gas into a second direction opposite to the first direction the gas discharged from a downstream side of the condensation part.

Abstract: A fan and compressor housing for an air cycle machine includes a fan inlet disposed around a center axis of the housing and having a fan inlet mounting flange, a compressor outlet having a compressor outlet mounting flange, and a compressor inlet having a compressor inlet mounting flange. The fan inlet mounting flange has a pinhole disposed thereon configured to receive a pin from a fan inlet diffuser housing and a fan inlet counterbore configured to receive a mating component from the fan inlet diffuser housing. The compressor outlet mounting flange has a compressor outlet counterbore configured to receive a first mating component from a condenser/reheater. The compressor inlet mounting flange has a compressor inlet counterbore configured to receive a second mating component from the condenser/reheater.

Abstract: The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit (6) of the aircraft by supplying compressed air to the auxiliary power unit (6) from a supercharger (7), and transferring non-propulsive energy from the auxiliary power unit (6) to the aircraft. The invention also concerns a system (5) for generating auxiliary power in an aircraft and an aircraft implementing such a method.

Abstract: An aircraft duct structure includes a first duct through which exhaust air from a front-side equipment compartment flows, and a second duct through which exhaust air from a rear-side equipment compartment flows. The first duct has a terminal end part where the exhaust air inside the second duct flows into the exhaust air inside the first duct at a substantially right angle, and a flow straightening plate located inside the terminal end part. The terminal end part has a jet opening which faces, across a clearance, an air pressure regulating port where an air pressure regulating valve is disposed. The inside of the terminal end part is divided by the flow straightening plate into an upper region and a lower region. The exhaust air inside the first duct and the exhaust air inside the second duct merge together in the upper region.

Abstract: A generator arrangement includes a generator and a pneumatic turbine. The pneumatic turbine is operably connected to the generator. A gas turbine engine compressor section is in fluid communication with the pneumatic turbine through a bleed air conduit to provide pressurized air to the pneumatic turbine for applying mechanical rotation to the generator.

Abstract: A fan housing for an air cycle machine includes a fan exit flow passage and a ring disposed around a center axis of the fan housing and disposed around the fan exit flow passage. The ring includes a first end disposed axially opposite a second end and a guide surface facing radially inward relative the center axis and formed between the first end and the second end. The ring also includes a shelf disposed radially inward from the guide surface. The shelf includes a stop surface extending radially and disposed axially between the second end and the guide surface. The shelf also includes a shelf surface facing radially outward relative the center axis and extending axially between the first end and the stop surface.

Abstract: A heat exchange system includes a core of cross flow passages having a reheater, and a condenser that is downstream of and directly interfaces the reheater. A first water extractor is downstream of the condenser, wherein the first water extractor turns a first fluid from the first pass of the condenser back towards the condenser and produces a second fluid that flows into the second pass of the condenser. A second water extractor is downstream the condenser, wherein the second water extractor turns a third fluid from the second pass of the condenser towards the reheater; and produces a fourth fluid that flows into the reheater.

Abstract: A system and method captures and processes flare gas so that the gas is usable as compressed natural gas (“CNG”). The flare gas is pressurized by a combination of a booster compressor and a CNG compressor. While interstage and between the booster compressor and the CNG compressor, the gas is treated to remove moisture and to separate out higher molecular weight hydrocarbons. The moisture is removed by contacting the interstage gas with a hygroscopic agent within a dehydration unit. The moisture free hydrocarbon fluid is expanded, and/or externally cooled and directed to a knock out drum. Higher molecular weight hydrocarbons are separated from the fluid in the knock out drum. Gas from the knock out drum is compressed in the CNG compressor.

Abstract: A fan shroud for an air cycle machine includes a tubular body extending axially between a first end and a second end of the shroud along a center axis of the fan shroud. A flange extends radially outward from the tubular body of the shroud at the first end of the shroud. At least one mounting hole extends through the flange. A sight hole extends through the flange and is positioned radially inward from the at least one mounting hole relative the center axis.

Abstract: A system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The compressing device is bypassed based on the preparing in parallel the medium for the chamber, which in turn enables the compressing device to windmill. Therefore, the system employs at least one mechanism to prevent components of the compressing device from windmilling.

Abstract: A power plant system including a fossil fuel fired power plant (6) for the generation of electricity, a carbon dioxide capture and compression system (5, 13), and an external heat cycle system has at least one heat exchanger (1,2,3) for the heating of the flow medium of the external heat cycle system. The heat exchanger (1,2,3) is connected to a heat flow from the CO2 capture plant (5) or a CO2 compression unit (13). A return flow from the heat exchanger (1,2,3) is led to the CO2 capture and compression system (5,13) or to the power plant (6). The power plant system allows an increase in overall efficiency of the system.

Abstract: A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.

Abstract: A distributed bleed system temperature management scheme utilizes a distributed, closed loop temperature protection function. By allowing consumer systems to limit the consumer flow to meet a specified bleed system outlet temperature (which may be different for each consumer or group of consumers), each system can be penalized according to their level of importance. The closed loop approach allows optimization of the performance reduction instead of relying on conservative assumptions as is done with conventional systems. In some embodiments, each consumer system may have a different temperature limit at which the consumed flow is limited to maintain a given bleed system exit temperature. The temperature setpoints may be separated by a minimum temperature, based on sensor and controls tolerances, to ensure that the flow limiting functions do not interact with each other.

Abstract: An on board inert gas generation system receives cabin air, or air from another relatively low pressure source, passing a portion thereof through an energy recovery turbine to ambient to extract power which is used to provide all, or part of, the energy required to drive a positive displacement compressor to compress another portion of cabin air to increase the pressure thereof to be suitable for supply to an air separation module.

Abstract: A control system for a refrigeration appliance is provided. The control system uses a linear model that is designed to minimize or remove excess enthalpy from one or more compartments and/or features of the appliance. At least one variable speed compressor is operated at a speed that will remove excess enthalpy within a desired time period while also operating at an optimized speed for energy efficiency.

Abstract: A valve control system includes a valve connected to regulate flow of a medium provided to an output and a sensor connected to monitor a feedback value associated with the medium. A controller modulates the valve based on a comparison of a reference value to the feedback value provided by the sensor. The controller detects saturation of the valve if the error between the monitored feedback value and reference value exceeds a threshold. In response to detected saturation, the controller reduces the reference value to a value less than the monitored feedback value.

Abstract: An air cycle machine has a housing which holds a compressor section, and a turbine section having an expansion area, and a fan section disposed outside of the housing. A shaft, which attaches to and is coaxial with the compressor section, the turbine section and the fan section, is supported by an air journal bearing and an air thrust bearing. The shaft has a hollow core for porting cooling air from the air journal bearing and the air thrust bearing, and a tube that extends into said expansion area and communicates cooling air from the turbine expansion area to the thrust bearing.

Abstract: A first stage turbocharger configured to receive an ambient intake air stream. A compressor of the first stage turbocharger coupled to a first intercooler. The first intercooler coupled to a turboexpander stage. The turbine of the turboexpander discharging an expanded air stream to an intake manifold of an engine. The expanded airstream having a temperature of less than the ambient intake air stream, thereby reducing enabling operation of the engine under high load conditions while maintaining reduced emissions.

Abstract: Provided is a machine unit layout system that simplifies the layout of a compressor unit and an expander unit and is extremely effective in terms of not only the reliability of the entire machine but also maintainability. Two separate compressors, a low-pressure-side compressor and a high-pressure-side compressor (11A, 11b), are disposed on either side of a steam turbine (10). Two separate expanders, a low-pressure-side expander and a high-pressure-side expander (12A, 12B), are disposed outside the low-pressure-side and high-pressure-side compressors (11A, 11b). The steam turbine (10), the low-pressure-side and high-pressure-side compressors (11A, 11b), and the low-pressure-side and high-pressure-side expanders (12A, 12B) are coupled by rotor shafts comprising a single shaft. The torque distribution between rotator shafts is optimized.

Abstract: An energy storage system that includes a compressor for compressing a gas, a thermal energy storage for cooling the gas coming from the compressor to a given temperature by heating a thermal storage medium to store thermal energy and a reservoir for storing the compressed gas. The energy system also includes a heat recuperator for further cooling the gas coming from the compressor and thermal energy storage below the given temperature by heating the gas supplied to the compressor.

Abstract: A component of an air cycle machine includes a fan housing portion, a compressor housing portion, a main bore housing radius, a static seal radius, a shroud pilot housing radius, and an insulator seal plate housing radius. The fan housing portion includes a shroud for a fan section. The compressor housing portion includes a shroud for a compressor air inlet, a shroud portion for a compressor blade section, and a shroud portion for a compressor air outlet. The main bore housing radius is arranged about a central axis and is configured to circumscribe a shaft arranged along the central axis, the main bore housing radius being between 1.9400 and 1.9440 inches. The static seal portion is arranged about the central axis and positioned longitudinally adjacent to the main bore housing portion. The static seal portion is configured to circumscribe a static seal defined by the shaft, and has a radius between 2.0420 and 2.0440 inches. The shroud pilot housing radius is arranged about the central axis.

Abstract: A turbomachine having gas cooled bearings may include an axially-oriented, cooling-gas passageway interconnecting first and second bearing chambers. The passageway may include grooves formed at an interface between an aerodynamic component of the turbomachine (e.g., a wheel or impeller) and a portion of a shaft assembly of the turbomachine.

Abstract: A compressor for compressing refrigerant in a refrigerant circuit includes a housing defining a compression chamber. A screw rotor is mounted within the housing and configured to form a pocket of high pressure refrigerant and a pocket of low pressure refrigerant within the compression chamber. The screw rotor has a rotor shaft rotating about an axis. A bearing cavity includes at least one bearing rotatably supporting the rotor shaft. A partition through which the rotor shaft extends separates the bearing cavity from the compression chamber. A contacting seal is sealingly engaged with the rotor shaft and disposed in the bearing cavity proximate the partition. A passage has an opening adjacent the rotor shaft between the contacting seal and the compression chamber and in fluid communication with the pocket of low pressure refrigerant.

Abstract: An air refrigerant type freezing and heating apparatus has a compressing mechanism that compresses an air refrigerant. As the air refrigerant is heated by a first heat exchanger and further heated by a heater, the temperature of the air refrigerant is increased to more than 200° C. and the air refrigerant is supplied to an oven. Heat of the air refrigerant outputted from the oven is recovered by a second heat exchanger, and supplied to a high-temperature side of the first heat exchanger. The air outputted from the second heat exchanger is cooled by a cooler and a third heat exchanger, is adiabatically expanded by an expansion turbine to be cooled to ?85° C., and is supplied to a freezer. The air of the freezer is recovered to be supplied to the low-temperature side of the third heat exchanger, and then is supplied to the compressor.

Abstract: A variable capacity type rotary compressor and a cooling apparatus having the same, and an operation method thereof are provided. In the variable capacity type rotary compressor and the cooling apparatus having the same, a discharge pressure is supplied to a rear side of a second vane disposed in the compressor after the discharge pressure is higher than a reference pressure, so that the compressor is switched from a saving mode into a power mode. The second vane is press-contacted with a second rolling piston with fast and accurately moving without vibration, resulting in preventing beforehand noise occurrence or efficiency degradation due to the vibration of the second vane when the compressor or the cooling apparatus having the compressor is operated in the power mode.

Abstract: The invention described herein enables a variety of heating, cooling, energy transformation, and energy storage options with a small number or components. Described are Pressure Swing Adsorption and Pressure Swing Desorption cycles, processes, and apparatuses including multiple sorption beds and active energy input by a pump and energy storage as pressure differentials. A preferred embodiment includes two zeolite 13X sorption beds, CO2 adsorbate, solenoid valves, and a compressor pump. In operation these components provide a range of heating, cooling, and energy storage options. Operational cycles are described.

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: A method of constructing self-powered air-conditioner comprises a convergent divergent nozzle where powered fan pushes air into said nozzle. While the pushed air accelerates toward the nozzle throat it becomes colder as air internal energy transformed into kinetic energy. An axial turbine installed within the nozzle throat extracts energy from the air in the nozzle and drives an electrical generator that provides electricity to the fan electric motor. Alternatively the turbine and fan are installed on common shaft, which could be the electric generator shaft. The cold air within the nozzle throat cools the nozzle throat skin, which serves as air-conditioner core. The cold nozzle skin is wrapped with coiled pipes in which liquid flows, becomes colder and this cold liquid flows away to heat exchanger where air is flowing through it and becomes colder. This cold air is then flows into spaces needed to be air-conditioned.