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

Abstract: 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 method and a device for compressing a gas-phase medium, particularly hydrogen or natural gas, in a single-stage or multistage process using at least one piston compressor, wherein the medium may have a water content up to total saturation with water. The medium to be compressed is heated before the compression at least to such point that the water is unable to condense out during the compression process, and the compressed medium undergoes a water separation process.

Abstract: A motor driven compressor system includes a motor with an internal cooling loop. The internal cooling loop draws cooling air from outside the motor driven compressor system. At least one compressor is driven by the motor. A heat exchanger is in fluid communication with the at least one compressor and the cooling loop and is arranged in a ram air duct. An on board inert gas generating system (OBIGGS) for a gas turbine engine and a method of cooling the system utilizing such a compressor system are also disclosed.

Abstract: A method for providing a flow control system for an aircraft. A compressor is removed from an existing air cycle machine, along with compressor ducting that is connected to a primary stage outlet of the heat exchanger and a secondary stage inlet of the heat exchanger in the existing air cycle machine. A first connector duct is provided and connected to the primary stage outlet of the heat exchanger and the secondary stage inlet of the heat exchanger. The turbine is removed from the existing air cycle machine, and a second connector duct is provided and connected to the upstream turbine duct directly and the downstream turbine duct.

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: A cooling system for an aircraft includes an air inlet through which air from the environment of the aircraft enters a ram air channel, and an air outlet through which air emerges from the ram air channel. A heat exchanger is arranged in the ram air channel. A ventilation device is in fluid communication with the ram air channel. Also connected to the ram air channel is a distribution line to cool at least one heat-loaded component of the aircraft, in particular a cabin air conditioning system, and/or to ventilate an installation space of the at least one heat-loaded component.

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 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: A hybrid vehicle which runs on power from at least one of an electric motor and an engine. When a required output exceeds a sum of an output of the electric motor which is driven by electric power supplied from a battery and an output of the engine while the hybrid vehicle is running on a drive mode in which at least the engine works as a drive source with a clutch engaged, a transmission ratio changing unit increases a ratio of electrical transmission to mechanical transmission of the output of the engine, and an engaging/disengaging control unit releases the clutch at a time point when the mechanically-transmitted output of the engine becomes 0, with the clutch engaged.

Abstract: An apparatus for use with an aircraft air conditioning machine to provide conditioned air to an aircraft cabin includes a recirculation air mixer to mix recirculation air and cold air from a turbine in the air conditioning machine as mixed air, the recirculation air mixer including a cold inlet, a plenum, a recirculation air inlet connected to an annulus and a plurality of injectors for injecting the recirculation air from the annulus into the plenum; and a condenser connected to the recirculation air mixer, the condenser including an inlet to receive air from a heat exchanger, a chamber where air from the recirculation air mixer enters to condense the air received through the inlet from the heat exchanger, an outlet for transferring the condensed air to the turbine, and an outlet for transferring conditioned air to the aircraft cabin.