Abstract: Systems and methods are disclosed for providing a work vehicle with an auxiliary air conditioner and/or an auxiliary heater. The systems include power conversion circuitry configured to convert AC power from an AC power source to power conditioned to drive the auxiliary air conditioner and/or auxiliary heater. The AC power source may be configured to drive various loads, and accordingly may include control circuitry to manage the power provided to the various loads, including the auxiliary air conditioner and/or auxiliary heater.

Abstract: The invention relates to an air conditioning system for a cabin (10) of an aircraft (80) comprising: a bleed air source (12); a ram-air circulation channel (13); a network of pipes and control valves; an air cycle turbine engine comprising at least one compressor (3) and a power turbine (4) which are mechanically connected to one another; and at least one primary cooling exchanger (PHX) which is accommodated in said channel (13), characterized in that said pipe network comprises a thermal power pipe (53) which is suitable for being able to fluidically connect, upon control of at least one control valve (25, 21), said air outlet (4b) of said power turbine (4) and said ram-air circulation channel (13) upstream of said primary exchanger (PHX) so that said bleed air expanded by said power turbine (4) can form a thermal energy source for said ram air being supplied to said primary circuit of said primary exchanger (PHX).

Abstract: Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.

Abstract: An air cycle machine includes a housing having an exterior wall and an interior wall, a scavenging turbine supported for rotation within the housing, and an ambient air fan. The ambient air fan is supported for rotation within the housing and is operably associated with the scavenging turbine. The interior wall defines therethrough a turbine-fan port that fluidly couples the ambient air fan to the scavenging turbine for communication of an overboard air flow to an ambient air flow without external ducting. Environmental control systems and methods of flowing fluid through air cycle machines are also described.

Abstract: An air cycle machine includes a housing, a scavenging turbine, and an ambient air fan. The housing has an exterior wall defining an overboard air inlet, an ambient air inlet, and an ambient air outlet. The scavenging turbine is arranged within the housing, is supported for rotation about a rotation axis, and is in fluid communication with the overboard air inlet. The ambient air fan is arranged within the housing, is supported for rotation about the rotation axis within the housing, and has a radially inner spoked portion and radially outer bladed portion. The bladed portion of the ambient air fan fluidly couples the ambient air inlet to the ambient air outlet and the spoked portion of the ambient air fan fluidly couples the scavenging turbine to the ambient air fan within the housing. Environmental control systems and fluid communication methods are also described.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a plurality of heat exchangers positioned therein, the plurality of heat exchangers including a first heat exchanger, a second heat exchanger, and a third heat exchanger. The ram air circuit is configured and arranged so that a first medium received at the first heat exchanger passes through the first heat exchanger and then through the third heat exchanger and so that a second medium received at the second heat exchanger passes through the second heat exchanger. A compressing device is arranged in fluid communication with the ram air circuit.

Abstract: The invention relates to a rotary sliding vane machine (1) for fluid processing, comprising a housing (2) with a cavity (4) with a rotor (9). Vanes (12) are arranged in outwardly directed slots (13) in the rotor (9), and relative sliding between the vanes and the rotor provides spaces with variable volumes in the rotational direction. Each vane is supported by a vane bearing apparatus (102) comprising a slide bearing body (105) with a slot (13) forming a slide bearing for the vane (12), and a cylindrical convex face (116) facing away from the slot (13), and, on each side of the slot (13), a pivot bearing pad (106) with a cylindrical concave face (117) facing the slide bearing convex face (116), forming a pivot bearing for the vane.

Abstract: The system can include an on-board thermal management subsystem. The system 100 can optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The system 100 can additionally or alternatively include any other suitable components.

Abstract: A thermal management system includes an open circuit refrigeration circuit that has a refrigerant fluid flow path, with the refrigerant fluid flow path including a receiver configured to store a refrigerant fluid, a first control device configured to receive refrigerant from the receiver, a liquid separator, and an evaporator configured to extract heat from a heat load that contacts the evaporator, with the evaporator coupled to the first control device and the liquid separator. The system includes a pump having an inlet and an outlet, with the outlet of the pump coupled to the liquid side outlet of the liquid separator and a second control device that is coupled to an exhaust line, that is coupled to the vapor side outlet of the liquid separator through the second control device. In operation, the evaporator in the open circuit refrigeration circuit would be coupled to a heat load.

Abstract: A method for large-scale, air-cooled floating liquefaction, storage and offloading of natural gas gathered from onshore gas pipeline networks. Gas gathered from on-shore pipeline quality gas sources and pre-treated to remove unwanted compounds is compressed and cooled onshore before being piped to an offshore vessel for liquefaction to produce LNG.

Abstract: An environmental control system according to an example of the present disclosure includes a heat exchanger, a ram air duct operable to provide cooling ram air to the heat exchanger, and a water extractor operable to extract water from a bleed air stream. The heat exchanger includes at least one nozzle operable to spray water from the water extractor into the ram air duct. An example heat exchanger and a method of making a heat exchanger are also disclosed.

Abstract: An environmental control system for providing conditioned air to a volume of an aircraft includes a ram air circuit including a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. A plurality of mediums is receivable within the environmental control system. A first medium of the plurality of mediums is provided from the volume of the aircraft via at least one valve.

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 is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. The at least one compressing device includes a turbine and a compressor operably coupled via a shaft. A fan is operably coupled to the ram air circuit. At least one compressing device is arranged non-linearly with the ram air circuit such that an axis of rotation of the fan is offset from the axis of the shaft.

Abstract: A CO2 power generation system includes a furnace to burn fuel, a turbine operated by a working fluid supplied thereto, the working fluid being heated by heat generated in the furnace, a recuperator exchanging heat with the working fluid passing through the turbine, a cooler to cool the working fluid passing through the recuperator, and a compressor to compress the working fluid passing through the cooler, wherein the working fluid passing through the compressor is circulated to the furnace, and the working fluid is supercritical CO2.

Abstract: An air-cycle machine (ACM) air conditioning system and method, uses a turbocharger to cool cabin air through expansion. The ACM utilizes an unused, excess, compressed air output from another compressor. A compressor provides compressed air to the intake of an internal combustion engine. The unused, excess, compressed air output from another compressor is diverted to and compressed in an ACM compressor. The output of the ACM compressor is cooled in a heat exchanger and then input to an ACM turbine. The ACM turbine expands the output of the heat exchanger to produce expanded, cooled, cabin air. At least a portion of the expanded, cooled, cabin air can be used to cool an intake charge for the internal combustion engine and/or to cool a passenger cabin and/or other enclosed, refrigerated space.

Abstract: A water separator and system includes a compressed air aftercooler and water/moisture separator with a demister core comprising a plurality of offset fins. In one embodiment, the compressed air aftercooler comprises a compressed air core having an aftercooler inlet, an aftercooler outlet at the bottom of the compressed air core, and one or more heat transfer passages. In one aspect, the system comprises a moisture separator substantially integral to the aftercooler. In another aspect, the system includes a first generally horizontal region beneath and adjacent to the aftercooler outlet; and an expansion zone adjacent to and in fluid communication with the first region, the expansion zone being configured to reduce the horizontal velocity of compressed air passing therethrough. In another aspect, the demister core is in fluid communication with the expansion zone.

Abstract: Gas Pressure Reduction Generator (GPRG) systems and methods for implementing a GPRG system are provided, where the GPRG systems comprise a gas inlet configured to receive a pressurized gas flow, at least one expander in gas flow receiving communication with the gas inlet wherein the expander is operable to convert the pressurized gas flow into mechanical energy and a depressurized gas flow, and a generator configured to convert the mechanical energy into electrical energy.

Abstract: An energy recovery apparatus for use in a refrigeration system, comprises an intake port, a nozzle, a turbine and a discharge port. The intake port is adapted to be in fluid communication with a condenser of a refrigeration system. The nozzle is configured to expand refrigerant discharged from the condenser and increase velocity of the refrigerant as it passes through the nozzle. The turbine is positioned relative to the nozzle and configured to be driven by refrigerant discharged from the nozzle. The discharge port is downstream of the turbine and is configured to be in fluid communication with an evaporator of the refrigeration system.

Abstract: An aircraft light comprises a housing (24), at least one light source (32) to be cooled, the at least one light source (32) being arranged in the housing (24), a heat sink element (26) thermally coupled to the at least one light source (32) and defining a cooling surface (36) exposable to a cooling airstream (52) for the cooling airstream (52) to flow along the cooling surface (36) in a flow direction. The cooling surface (36) extends between upstream and downstream end portions (40,42) spaced apart in the flow direction and means for generating a pressure difference between the upstream and downstream end portions (40,42) of the cooling surface. Due to the pressure difference, a cooling airstream (52) flowing along the cooling surface (36) is created.

Abstract: An environmental control system including a turbomachine assembly having a shaft, motor, turbine and compressor, the compressor outputting a compressed air stream, a first valve that splits the compressed air stream into first and second compressed air streams, a heat exchanger to cool the first compressed air stream and output a cooled air stream, a second valve positioned to receive the cooled air stream and split the cooled air stream into first and second cooled air streams, wherein the first cooled stream is expanded in the turbine to produce an expanded air stream that is combined with the second compressed air stream and the second cooled air stream to provide a combined air stream having a temperature and a flow rate, and a controller that communicates control signals to the compressor, motor and first and second valves to control the temperature and flow rate of the combined air stream.

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

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

Abstract: 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.

Abstract: A cooling system includes a heat exchanger through which a refrigerant flows, and which rejects heat to a fluid, an evaporator, a first circuit having an expansion device, a second circuit having an expansion machine coupled to a compressor, and a set of valves arranged to direct the refrigerant through the first circuit, the second circuit, or both the first and second circuits based on ambient conditions.

Abstract: An aircraft air conditioning system comprising a compressor adapted to generate compressed process air, an air conditioning unit adapted to cool and expand compressed process air supplied to the air conditioning unit from the compressor, and an energy converter adapted to convert hydraulic energy into electric energy. The compressor is supplied with electric energy generated by the energy converter by converting hydraulic energy supplied to the energy converter.

Abstract: The present invention provides a refrigeration cycle apparatus using a first compressor and a second compressor driven by an expander and including a high and low pressure heat exchanger, in which a low-pressure-side outlet of the high and low pressure heat exchanger is bypassed to a low pressure portion or an intermediate pressure portion to adjust an inlet density at the expander and thereby provide high efficiency. The high and low pressure heat exchanger of the refrigeration cycle apparatus of the present invention changes an amount of heat exchange between a high-pressure refrigerant and a reduced-pressure refrigerant branched from the high-pressure refrigerant at an inlet portion of the high and low pressure heat exchanger and reduced in pressure to adjust the density of the refrigerant flowing in the expander so that power recovered by the expander and power required by the second compressor match.

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: A refrigerant system utilizes an expander to expand refrigerant and to drive or assist in driving an associated compressor. By varying the compressor load, the speed of the expander can be adjusted to achieve the desired thermodynamic characteristics of the expanding refrigerant and enhance expander operation.

Abstract: A refrigerant vapor compression system includes a compression device, a heat rejecting heat exchanger, an economizer heat exchanger, an expander and an evaporator disposed in a refrigerant circuit. An evaporator bypass line is provided for passing a portion of the refrigerant flow from the main refrigerant circuit after having traversed a first pass of the economizer heat exchanger through the expander to partially expand it to an intermediate pressure and thence through a second pass of the economizer heat exchanger and into an intermediate pressure stage of the compression device. An economizer bypass line is also provided for passing a portion of the refrigerant from the main refrigerant circuit after having traversed the heat rejecting heat exchanger through a restrictor type expansion device and thence into the evaporator bypass line as liquid refrigerant or a mix of liquid and vapor refrigerant for injection into an intermediate pressure stage of the compression device.

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: A system for managing heat fluxes of an aircraft is provided, including a fuel tank supplying a turbomachine with fuel via a fuel supply circuit; a cell cooling circuit connected to a thermal effluents source, which integrates a first heat exchanger ensuring heat transfer between a coolant circulating in the cell cooling circuit and air flow channeled into a cooling air channel extending from an air intake to an exhaust; and a second heat exchanger ensuring a heat transfer between the coolant circulating in the cell cooling circuit and the fuel. The air intake includes a blocker to open/close it. The system includes a fuel transfer circuit, which connects the fuel tank to the second heat exchanger and provides fuel to the second heat exchanger, including a valve selectively changing a fuel supply direction from the second heat exchanger between the directions of the tank and the fuel supply circuit.

Abstract: Refrigerating device formed by a main compressor (190), a condenser (140) downstream of and in fluid communication with the main compressor (190), main expansion means (170) downstream of the condenser (140) and an evaporator (180) downstream of and in fluid communication with the main expansion means (170), which also comprises a turbocompressor unit (160) in fluid communication between the evaporator (180) and the main compressor (190) and a heat exchanger (150, 152) having a hot branch (150c) connected upstream, via an inlet line (145), to the condenser (140) and downstream, via an outlet line (149), to the main expansion means (170) and a cold branch (15Of) connected, upstream, to an expansion means (142, 144) mounted on a branch (146) of the line (145) and, downstream, to a turbine portion (162) of the turbocompressor unit (160). The invention also relates to a method for circulating a refrigerating fluid inside the abovementioned device.

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: An air conditioning system is provided with mainly an evaporator, a compressor, a condenser and an energy recovery device. The compressor is fluidly connected to the evaporator to compress low-pressure refrigerant exiting the evaporator to high-pressure refrigerant. The condenser is fluidly connected to the compressor to receive the high pressure refrigerant and dissipate heat therefrom. The energy recovery device is configured to extract work from refrigerant flowing therethrough. The energy recovery device includes a movable expander and a valve. The movable expander has an inlet fluidly connected to the condenser to receive high pressure refrigerant exiting the condenser, an outlet fluidly connected to the evaporator to deliver low pressure refrigerant thereto and a chamber fluidly connected between the inlet and the outlet. The valve is configured to control a flow rate of high pressure refrigerant flowing from the inlet to the chamber.

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

Abstract: 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: An environmental control system (ECS) includes an air cycle machine with an expansion turbine and a condenser having a cold air inlet connected to receive air from the expansion turbine. The condenser has hollow, internally finned hot bars positioned at the cold air inlet to prevent ice formation at the cold air inlet.

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: The air conditioning system uses an air cycle thermodynamic process. The system comprises a centrifuge. This centrifuge includes at one of its ends, an axial inlet that funnels air into a centrifugal compressor rotating in unison with the centrifuge. The air is compressed, adiabatically heated and directed to a heat exchanger mounted in the rim of, and rotating with the centrifuge. The air is accelerated with respect the centrifuge by varying the centrifuge radius or by using forward leaning impeller blades. The air is cooled by the heat exchanger and directed to an expander also rotating with the centrifuge. The air is expanded and adiabatically further cooled. The cold air exits the centrifuge through an axial outlet located at the second end of the centrifuge.

Abstract: A cooling system includes a compressor for compressing a refrigerant from a subcritical state to a supercritical state, a cooler for transferring heat from the refrigerant, an expander for expanding the refrigerant in the supercritical state, an expansion valve for expanding the refrigerant from the supercritical state to the subcritical state and an evaporator for transferring heat from a cooling fluid to the refrigerant in the subcritical state. Work extracted by the expander provides power to the compressor. A method for cooling a vehicle includes compressing a refrigerant from a subcritical state to a supercritical state, cooling the refrigerant, expanding the refrigerant in the supercritical state where work produced by expanding the refrigerant is used to compress the refrigerant, expanding the refrigerant from the supercritical state to the subcritical state, cooling a cooling fluid with the refrigerant in the subcritical state and cooling vehicle components with the cooling fluid.

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: An energy efficient air conditioning system preferably includes a compressor, a reaction turbine, an electrical generator, an expansion device, an evaporator coil, an evaporator fan and a refrigerant gas. A condenser coil and fan are replaced with the reaction turbine. Hot high pressurized gas is piped into the reaction turbine from the compressor, which causes a drive shaft of the reaction turbine to spin the electrical generator. High pressurized liquid exits the reaction turbine into the expansion device as a high pressure liquid. A low pressure liquid exists at an output of the expansion device and enters the evaporator coil. The low pressure liquid boils, absorbing heat in the evaporator. The evaporator fan blows warm air from a confined space over the evaporator coil to provide a flow of cold air to the confined space. The low pressure gas then enters the compressor to start a new cycle.

Abstract: Embodiments of a heat transfer apparatus, and related methods, involve a curved flow path, a heat source external to and in thermal communication with at least a portion of an inner radial boundary of the curved flow path, and a working fluid, including a heavier component and a lighter component, flowing through the flow path. The flow path causes the working fluid to experience centrifugal force so as to preferentially force the heavier component toward the exterior wall portion and thereby cause the lighter component to preferentially absorb heat from the interior wall portion.

Abstract: A method for managing heat in an airplane includes extracting hot bleed air from a gas turbine engine, and cooling the hot bleed air in a first heat exchanger thereby forming warm bleed air. The method further includes expanding the warm bleed air with a turbine thereby forming cool bleed air, and using the cool bleed air as a heat sink in a second heat exchanger associated with an environmental control system and thereby forming used bleed air.

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 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 apparatus for cooling, comprising: a liquid pump for transport of fluid through a heating cycle, an external heat source for heating the fluid in the heating cycle, for example a solar heater directly connected to the heating cycle or connected through a heat exchanger, an expander with an expander inlet and an expander outlet, the expander inlet having a fluid connection to the external heat source for receiving fluid in the gas phase to drive the expander by expanding the fluid, a compressor with a compressor inlet and a compressor outlet, the compressor being driven by the expander for compressing working fluid from a low pressure compressor inlet gas to a high pressure compressor outlet gas, a first heat exchanger with a fluid connection to the compressor outlet and connected to the expander inlet for transfer of heat from the high pressure compressor outlet gas to the fluid in the heating cycle, a second heat exchanger with a condenser for condensing the working fluid from the expander by energy trans

Abstract: An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system and at least one bleed air connection for routing bleed air to the air conditioning system. The electric line network is connected to the air conditioning system and at least one electrical energy source for routing electrical energy to the air conditioning system. The air conditioning system has an electrically operable cooling device. By means of the energy supply system according to the invention the energy withdrawn from the power units is better adapted to the energy necessary for operating the air conditioning system and other systems—such as, for example, wing de-icing—and therefore reduces the excess fuel consumption of the aircraft.

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.