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: A cooling air supply system for an aircraft is configured to supply cooling air from the surroundings of the aircraft to at least two devices requiring cooling air (38, 44, 56) within the aircraft. The cooling air supply system includes an air inlet, an air channel communicating with the air inlet, and an air distribution device for the distribution of air from the air channel to the at least two devices requiring cooling air. The air inlet is sized to provide sufficient air flow to accommodate a maximum cooling air requirement of the at least two devices requiring cooling air.

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: Apparatus and method for removing particles from an air source. The air source is passed through multiple rows (R65) of cyclone separators (65), removing particles from the air to create cleaned air and passing the particles through openings (112) in the separators 65 so that the particles fall to a surface (42) below the openings. The cleaned air is directed into a first chamber region (73) above the cyclone separators (65) and moved along a second chamber region (76) positioned between two of the rows (R65) toward a duct (85) for passage out to a compressor (22).

Abstract: A solar powered air conditioner comprising of at least one solar panel, an inverter that converts the DC voltage created by the solar panels to AC voltage connected to the solar panel, a battery charger that receives the AC voltage from the inverter and converts the AC voltage to DC voltage, a charge controller connected to the battery charger, a rechargeable battery connected to the charge controller, a contactor connected to the rechargeable battery and to a thermostat, a DC powered motor connected to the contactor, and an air conditioning system, the air conditioning system having an air compressor and an air conditioning motor, the air compressor connects to the DC powered motor via a belt, and the air conditioner motor connects to the contactor.

Abstract: An ejector (200; 400; 600; 700; 800) has a housing (202) and an insert. The housing has an upstream end (206) and a downstream end (208) and a branch (220). A primary flowpath extends from the upstream end and a secondary flowpath passes through the branch to join the primary flowpath. The insert (204; 402) is within the housing and extends from an upstream end (250) to a downstream end (252). The insert has a motive nozzle (240) having an inlet and an outlet. A mixer (242) is at least partially downstream of the motive nozzle. One or more passages (304) are positioned such that the secondary flowpath extends through the branch and through the one or more passages to join the primary flowpath, at least one portion of the insert being of less robust material than a material of the housing.

Abstract: An air-conditioning system for an aircraft includes a compressed air branch for conveying externally supplied and pressurized air, preferably bleed air. Furthermore, a cooling circuit for conveying preferably liquid refrigerant is provided and extends through a ram air duct. The system also includes a first heat exchanger for the heat transfer between the compressed air branch and the cooling circuit, a compressed air turbine arranged in the compressed air branch and a cooling circuit compressor arranged in the cooling circuit and mechanically coupled to the compressed air turbine. The system can have a modular design and be positioned at optimal locations in the aircraft due to the separation of the compressed air branch and the cooling circuit. In this way, the length of hot compressed air ducts can be shortened.

Abstract: A heating and cooling system for inlet air of a turbine compressor. The heating and cooling system may include a fluid coil positioned about the turbine compressor and a thermal energy storage tank. The fluid coil and the thermal energy storage tank are in fluid communication such that fluid is both provided to the fluid coil from the thermal energy storage tank for exchanging heat with the inlet air and returned to the thermal energy storage tank without further heat exchange.

Abstract: An aircraft air-conditioning unit (10) includes a compressor (18) and a motor (20) driving the compressor (18). A fuel cell system (24) is connected directly to a control unit (22) for controlling the motor (20) driving the compressor (18), wherein the control unit (22) is adapted to convert electrical energy directly generated by the fuel cell system (24) into corresponding electrical control signals for controlling the motor (20) driving the compressor (18). In a method for operating an aircraft air-conditioning unit (10), which includes a compressor (18) and a motor (20) driving the compressor (18), a control unit (22) for controlling the motor (20) driving the compressor (18), which is directly connected to a fuel cell system (24), converts electrical energy directly generated by the fuel cell system (24) into corresponding electrical control signals for controlling the motor (20) driving the compressor (18).

Abstract: A ram air fan assembly includes a ram air fan disposed at a fan inlet and a ram air fan motor operably connected to the ram air fan. A blower is operably connected to the ram air fan and is configured to redirect a cooling flow across the ram air fan motor from a substantially axially directed flow to a substantially radially directed flow thereby increasing the cooling flow across the ram air fan motor. A method of cooling a ram air fan assembly includes urging a cooling flow toward the ram air fan motor and is directed across the ram air fan motor thus removing thermal energy from the ram air fan motor. The cooling flow proceeds across a blower operably connected to the ram air fan motor, thus directing the cooling flow substantially radially outwardly toward the fan inlet.

Abstract: A refrigeration system for minimizing the cool down time of a mass to cryogenic temperatures including a compressor, an expander, a gas storage tank, interconnecting gas lines, and a control system. The compressor output is maintained near its maximum capability by maintaining near constant high and low pressures during cool down, gas being added or removed from the storage tank to maintain a near constant high pressure, and the speed of said expander being adjusted to maintain a near constant low pressure, no gas by-passing between high and low pressures.

Abstract: A method for operating an air-conditioning system for an aircraft including receiving an available power level from a control system of the aircraft, forwarding air from a first compressed air source to an aircraft cabin and forwarding air from a second compressed air source to the aircraft cabin if the available power level exceeds a threshold value.

Abstract: An air cycle machine includes two turbines and a compressor mounted on an integral shaft. The integral shaft includes a plurality of shaft sections that are welded together and machined in a single set-up process into a desired shaft shape to provide highly aligned bearing surfaces. The shaft includes three stops that cooperate with three fasteners to secure the two turbines and the compressor on the shaft.

Abstract: Embodiments of a heat transfer apparatus, and related methods, involve a first flow path through at least one neck portion defined by at least one boundary wall, a first heat source external to and in thermal communication with the at least one boundary wall, an inflow portion in fluid communication with the first flow path, an outflow portion in fluid communication with the first flow path, and a drive system for driving a first fluid through the first flow path, whereby heat is transferred from the first heat source to the first fluid as it flows through the first flow path.

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: An ECS system provides an ACM which locates the compressor upon a common shaft between a first turbine and a second turbine. Each RAF is located remote from the ACM such that the turbines are located outboard on each end of the ACM to provide the highest efficiency possible with each turbine using a straight axial outlet diffuser. As the compressor is located between the turbines the bypass circuits from the turbines are less circuitous and more efficient. Integral valve ports formed into the ACM housing portions results in a weight reduced design due to increase bypass efficiencies and simplified installations.

Abstract: The air cycle refrigerating/cooling system compresses air that has flown in with a compressor (6) in a turbine unit (5) and adiabatically expands the air with an expansion turbine (7) in a turbine unit (5). In the turbine unit (5), a compressor rotor (6a) of the compressor (6) and a turbine rotor (7a) of the expansion turbine (7) are attached to the same main shaft (13), the main shaft (13) is supported by bearings (15) and (16) so as to be freely rotatable, and part or the entirety of the thrust force applied to this main shaft (13) is supported by an electromagnet (17).

Abstract: A refrigeration cycle apparatus achieves efficient operation by constantly recovering power in a wide operating range. The refrigeration cycle apparatus regulates a pressure of a high pressure side by changing either one or both of an opening degree of the intermediate-pressure bypass valve and an opening degree of the pre-expansion valve on the basis of a density ratio that is obtained from an inflow refrigerant density of the expander and an inflow refrigerant density of the sub-compressor in an actual operating state and a design volume ratio that has been expected at the time of design and that is obtained from a stroke volume of the sub-compressor, a stroke volume of the expander, and a ratio of a flow rate of the refrigerant flowing to the sub-compressor.

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: A method for cool drying gas by a cooling element with an evaporator, using a device for determining the evaporator temperature and measuring the lowest gas temperature, by applying the steps: determining the load of the cooling circuit on the basis of the evaporator temperature and the lowest gas temperature; calculating a desired value for the evaporator temperature that is required to cool the gas supplied to a set lowest gas temperature, taking account of the aforementioned load; controlling the speed of the compressor to make the evaporator temperature equal to the desired value.

Abstract: A vehicular air conditioner in which a plurality of parts comprising a refrigerant circuit are integrally provided to reduce an occupying space and reduce the number of the parts and the number of assembling steps. A refrigerant circuit is provided with a cold storage internal heat exchanger having a high-pressure refrigerant storage unit through which the high-pressure refrigerant on the downstream side of a condenser flows, a low-pressure refrigerant storage unit through which the low-pressure refrigerant on the downstream side of an evaporator flows, and a cold storage material housing unit which houses a cold storage material therein.

Abstract: An aircraft compound cooling system includes a power thermal management system for cooling one or more aircraft components, an air cycle system, a vapor cycle system, and a turbine cooling circuit for cooling bleed air and cooling turbine components in a high pressure turbine in the engine. An air to air FLADE duct heat exchanger is disposed in a FLADE duct of the engine and a valving apparatus is operable for selectively switching the FLADE duct heat exchanger between the turbine cooling circuit and the air cycle system. A vapor cycle system includes a vapor cycle system condenser that may be in heat transfer cooling relationship with the air cycle system. An air cycle system heat exchanger and an engine burn fuel to air heat exchanger in the vapor cycle system condenser may be used for cooling a working fluid in a refrigeration loop of the vapor cycle system.

Abstract: An environmental control system (ECS) for providing conditioned air to a cabin of an aircraft at a desired rate may include a bleed-air driven primary air treatment unit configured to produce pack supply air and to recirculate a portion of the pack supply air into a compressor of the primary air treatment unit. The ECS may also include a bleed-air driven secondary air treatment unit configured to compress ram air at a rate that corresponds to the rate of recirculation. The ECS may be configured to selectively deliver conditioned air from both the primary and the secondary air treatment units to the cabin.

Abstract: The present invention provides a technique for rapidly removing frost accumulated in air-refrigerant cooling apparatuses. An air-refrigerant cooling apparatus in accordance with the present invention includes a bypass line for directly supplying a defroster with refrigerant air having an increased temperature from a compressor, avoiding temperature drop by a heat exchanger and an expansion turbine. Moisture of the frost melted in the defroster is externally exhausted by a fan.

Abstract: By the invention a heat storage system for storing solar heat is provided, the system including a subterranean heat storage (2) for storing heat at temperatures above 800° C., a collector structure (8) being placed on or above the ground, the collector structure having at least one reflecting surface (10) or converging lens for deflecting solar radiation (12), an absorber body (6) positioned so as to receive solar radiation (12) deflected by the collector structure (8) and be heated by said solar radiation (12), and a solid material heat conductor (4) for transferring heat from the absorber body (6) to the subterranean heat storage (2). A method of storing solar heat is also provided.

Abstract: A bleed air conditioning system within an aircraft including a low-pressure bleed air line and a high-pressure bleed air line. The system includes an air-to-air heat exchanger and an un-cooled bleed air line to connect the air-to-air heat exchanger to the low-pressure bleed air line and the high-pressure bleed air line. The un-cooled bleed air line carries a flow of un-cooled bleed air from at least one of the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger. The system also includes a cooled bleed air line connected to the air-to-air heat exchanger for carrying cooled bleed air from the air-to-air heat exchanger and a low-pressure bypass line connecting the low-pressure bleed air line to the cooled bleed air line, bypassing un-cooled bleed air from the low-pressure line around the air-to-air heat exchanger to the cooled bleed air line.

Abstract: An integrated gasification combined cycle system is provided. The integrated gasification combined cycle system includes an air compressor coupled in flow communication to an air separation unit, a condensate heater coupled in flow communication with the air compressor, and a condenser coupled in flow communication with the condensate heater. The condensate heater and the air compressor are coupled such that a portion of compressed air generated by the air compressor is channeled to the condensate heater. A method of assembling an integrated gasification combined cycle system is also provided.

Abstract: This invention provides heat engines based on various structures of internal combustion engines, such as a four-stroke piston-type combustion engine, two-stroke piston-type combustion engine, rotary combustion engine, or a free-piston type combustion engine. Said heat engine is provided with at least a heating chamber per piston or rotor, a heat exchanger unit disposed within said heating chamber through which thermal energy is extracted from a heat source and at least a port leading to a working chamber space from said heating chamber, and has a significantly increased heat transfer duration from the heat source to the working fluid within said heating chamber without increasing the number of strokes per power stroke in a cycle. Additionally, said heat engine is provided with an over expansion mechanism in conjunction with a compression means for intake charge. Thereby many of the operational characteristics of an Otto power cycle may be attained in said heat engine, and a heat source with a.

Abstract: Systems and methods provide for cooling air in a power generation system. The system includes: an air handling unit configured to receive air, to cool the air and to remove moisture from the air; a first compressor fluidly connected to the air handling unit and configured to receive the air from the air handling unit and to exhaust a first compressed, heated air flow; a vapor absorption chiller connected to the first compressor and configured to transfer heat energy between a plurality of mediums and to cool the first compressed, heated air flow; and a second compressor connected to the vapor absorption chiller and configured to receive the cooled first compressed, heated air flow and to exhaust a second compressed, heated air flow.

Abstract: An air-conditioner capable of suppressing increase in the suction temperature of a compressor is provided. The air-conditioner according to the present invention has a refrigerant circuit in which a compressor, an oil separator, a heat source side heat exchanger, a throttle device, and a use side heat exchanger are connected in series, an oil returning circuit that connects the oil separator with the suction side of the compressor, and a decompression mechanism provided in the oil return circuit. The oil return circuit is installed by piping so as to exchange heat with a part of the heat source side heat exchanger at the upstream side of the decompression mechanism.

Abstract: A refrigeration system for minimizing the cool down time of a mass to cryogenic temperatures including a compressor, an expander, a gas storage tank, interconnecting gas lines, and a control system. The compressor output is maintained near its maximum capability by maintaining near constant high and low pressures during cool down, gas being added or removed from the storage tank to maintain a near constant high pressure, and the speed of said expander being adjusted to maintain a near constant low pressure, no gas by-passing between high and low pressures.

Abstract: A refrigeration air conditioner includes a first equalizer pipe connecting a bottom portion of a first hermetic vessel, which contains a main compression mechanism and lubricating oil, to a bottom portion of a second hermetic vessel, which contains an expansion mechanism, a sub-compression mechanism, and lubricating oil. A second equalizer pipe connects a side of the second hermetic vessel at a position higher than a minimum oil level to a suction side of the main compression mechanism. The space within the second hermetic vessel is isolated from the expansion mechanism and the sub-compression mechanism, and the pressure within the second hermetic vessel is not dependent upon the pressure within the expansion mechanism and the pressure within the sub-compression mechanism.

Abstract: An environmental control system for conditioning air in a vehicle compartment, such as an aircraft cabin. Cool expanded higher-pressure air from a turbine is mixed with recirculated warmer, lower pressure air from the compartment. The air is mixed and recirculated by a jet pump which includes an inlet section, an outlet section, a diffuser section and a mixing section. The mixing section includes a plurality of separate mixing chambers. The diffuser section includes diffusers for receiving mixed gases from each of the mixing chambers. The outlet section receives the mixed gases which are then conveyed to the compartment. The inlet section includes for each of the mixing chambers, a primary nozzle for introducing the higher-pressure air into a respective mixing chamber, and a secondary nozzle for introducing the lower pressure air to a respective mixing chamber.

Abstract: A cabin air compressor assembly includes a cabin air compressor disposed at a compressor inlet and a cabin air compressor motor operably connected to the cabin air compressor. At least one cooling flow inlet is located at a first end of the cabin air compressor motor substantially opposite a second end whereat the cabin air compressor is located. The cooling flow inlet is configured to direct a cooling flow across the cabin air compressor motor. A blower is operably connected to the cabin air compressor and is configured to urge a cooling flow from across the cabin air compressor motor toward a cooling flow outlet, thereby increasing the cooling flow across the cabin air compressor motor.

Abstract: Air-conditioning system (10) for aircraft, in particular for commercial aircraft, with a bleed air source (12), a bleed air line (22-30) comprising a main valve (16), and an air-conditioning unit (32), wherein a mass air flow conveyed from the bleed air source (12) through the bleed air line (22-30) to the air-conditioning unit (32) can be controlled by means of the main valve (16). According to the invention it is envisaged that a by-pass line (36-50, 58, 60) comprising a by-pass valve (34) and by-passing at least a part (22-26, 16) of the bleed air line, is present between the bleed air source (12) and the air-conditioning unit (32).

Abstract: A fluid machine (201) includes: a compression mechanism (2) for compressing a working fluid; an expansion mechanism (4) for expanding the working fluid and for recovering mechanical power from the expanding working fluid; a shaft (5) for coupling the compression mechanism (2) and the expansion mechanism (4) and for transferring the mechanical power recovered by the expansion mechanism (4) to the compression mechanism (2); and a closed casing (1) for accommodating the compression mechanism (2), the shaft (5) and the expansion mechanism (4), and having an internal space into which the working fluid that has been compressed by the compression mechanism (2) is discharged. A refrigerant passage space (7) through which a refrigerant to be drawn into the expansion mechanism (4) passes is formed between an expansion chamber of the expansion mechanism (4) and the internal space of the closed casing (1).

Abstract: Disclosed are the use of fluorine substituted olefins, including tetra- and penta-fluoropropenes, in a variety of applications, including connection with blowing agents, foams, foamable compositions, foaming methods, heat transfer compositions and methods, propellants, and solvating methods.

Abstract: An avionics cooling system including an avionics cooling circuit operating with a liquid coolant; a fuel circuit; and a vapor cooling cycle operating with a refrigerant. The avionics cooling circuit transfers heat withdrawn from avionics to the fuel circuit, whereby the heat is dumped into fuel, and the vapor cooling cycle transfers heat that cannot be dumped into the fuel from the fuel circuit to ram air.

Abstract: The present invention provides a system and method for cooling the bleed air supply in an on-board inert gas generation system. The gas generation system cools the bleed air using a turbocompressor in conjunction with heat exchangers. Exhaust from a regenerative heat exchanger providing air to the turbocompressor is ported to a ram air outlet using a flow-restriction/ejector unit.

Abstract: An arrangement has a turbomachine, a cooler, and a carrying frame that accommodates the turbomachine and the cooler, with frame segments. The cooler has at least one essentially pipe-shaped cooling element disposed horizontally, and the frame segments are disposed at a distance from one another in the longitudinal direction of the cooling element, and have contact points on the underside to support the arrangement on a floor surface or a base frame. The at least one cooling element is attached to the frame segments by way of flexible sections for accommodating thermal deformations of the cooling element.

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.

Abstract: A system for the provision of process air comprises a first cooling system (2) with a first heat exchanger, which is arranged in a channel (3) that serves as a cooling sink, and a cooling system (8), integrated in the first cooling system (2), wherein said cooling system (8) comprises a heat exchanger (9) which is integrated in the channel (3) either upstream or downstream of the first heat exchanger.

Abstract: Heat pumps move heat from a source to a higher temperature heat sink. This invention enables spontaneous source-to-sink heat transfer. Spontaneous heat transfer is accomplished by conducting heat from the source through rotating disks to a portion of the generally warmer sink flow that is cooled to a temperature below that of the source by the Bernoulli effect. The nozzled flow required for Bernoulli cooling is provided by the corotating disk pairs. The distance between the opposing surfaces of the disk pair decreases with distance from the rotation axis, forming a nozzle. The heat-sink flow through the nozzle is maintained by centrifugal force caused by the circular motion of the gas near the disk surfaces. Embodiments of the invention differ in the paths followed by the source and sink fluid flows, by the number of disk pairs and by the state (gas or liquid.) of the heat source.

Abstract: The present disclosure generally relates to an apparatus for the condensation of a liquid suspended in a gas, and more specifically, to an apparatus for the condensation of water from air with a geometry designed to emphasize adiabatic condensation of water using either the Joule-Thompson effect or the Ranque-Hilsch vortex tube effect or a combination of the two. Several embodiments are disclosed and include the use of a Livshits-Teichner generator to extract water and unburned hydrocarbons from exhaust of combustion engines, to collect potable water from exhaust of combustion engines, to use the vortex generation as an improved heat process mechanism, to mix gases and liquid fuel efficiently, and an improved Livshits-Teichner generator with baffles and external condensation.

Abstract: A mobile cooling apparatus and method for harvested produce includes working platform and a cooling zone. Produce harvested along the working platform and transferred thereto is placed into the cooling zone which, in one embodiment, is located on an opposite side of the working platform from where harvesting is occurring. The cooling zone may be open at an outward facing end thereof, to permit offloading of harvested produce to a second mobile apparatus. The cooling zone may be dimensioned to contain at least one pallet and, in one embodiment, two pallets positioned side-by-side.

Abstract: The invention relates to a universal system for producing cost effective energy particularly for cooling purposes. In one embodiment, wind turbines are used to generate electricity and compressed air energy, wherein the compressed air energy is used to co-generate electricity and chilled air. The chilled air is then used to chill water in either a mixing chamber, or a desalination system, wherein the chilled water is stored in a separation tank, wherein it can later be used to provide cooling for an air conditioning system for a facility. When desalination is used, the system produces chilled fresh drinking water which can be used for air conditioning, and then used as fresh drinking water. Any exhaust chilled air can be used directly for air conditioning.

Abstract: A system for cooling computer equipment in a data center. The system includes a raised floor defining a pressurized under-floor plenum; a computer room air conditioning unit disposed on the raised floor and having a hot air inlet and a cold air outlet, wherein the cold air outlet is in fluid communication with pressurized under-floor plenum; and a server cabinet housing server equipment and including a pressurized vertical plenum in fluid communication with under-floor plenum via an inlet duct. The server cabinet is configured to receive a cold air stream from the under-floor plenum via the inlet duct into the vertical plenum and draw the cold air across the server equipment to provide cooling without the use of external fans. The system may also include an inflatable airfoil damper assembly disposed within the inlet duct and configured to provide failsafe variable airflow to the vertical plenum within the server cabinet.

Abstract: A multi cylinder compressor/expansion engine having a centrally mounted drive shaft. A cylinder barrel is mounted on the drive shaft and both the cylinder barrel and the drive shaft rotate about a common axis. There is a plurality of cylinders in the cylinder barrel with pistons disposed in each of the cylinders. Some of the cylinders are compression cylinders and some of the cylinders are expansion cylinders. The compression cylinders discharge a fluid at a first high pressure from the engine. The expansion cylinders receive fluid at a second pressure which provides energy to the engine thereby reducing the energy required for the engine to rotate the drive shaft.

Abstract: It is an object of the present invention to reduce the constraint that the density ratio is constant as small as possible, and to obtain high power recovering effect in a wide operation range. A refrigeration cycle apparatus uses carbon dioxide as refrigerant and has a compressor, an outdoor heat exchanger evaporator, an expander and an indoor heat exchanger a radiator. An injection circuit for introducing high pressure refrigerant is provided in a halfway of an expansion process of said expander.