Abstract: An aircraft cooling system includes a refrigerant cycle including a first heat exchanger. A liquid cycle passes a liquid through the first heat exchanger, at which it is cooled by a refrigerant in the refrigerant cycle. An air cycle compresses air and delivers the compressed air into a second heat exchanger. The liquid passes through the second heat exchanger at a location downstream of the first heat exchanger. The liquid cools the air in the second heat exchanger. Air downstream of the second heat exchanger passes to be utilized by a use on an aircraft.

Abstract: An environmental conditioning system has a compressor for compressor air in an air flow path. A turbine drives the compressor and is coupled to the compressor. An evaporator is in communication with the compressor. The evaporator is configured to cool air from the compressor.

Abstract: An aircraft cooling system includes a refrigerant cycle including a first heat exchanger. A liquid cycle passes a liquid through the first heat exchanger, at which it is cooled by a refrigerant in the refrigerant cycle. An air cycle compresses air and delivers the compressed air into a second heat exchanger. The liquid passes through the second heat exchanger at a location downstream of the first heat exchanger. The liquid cools the air in the second heat exchanger. Air downstream of the second heat exchanger passes to be utilized by a use on an aircraft.

Abstract: A galley chiller system for an aircraft includes at least one condenser having a refrigerant fluid. The fluid within the condenser rejects heat to a first surrounding environment. To more efficiently use the condenser of the galley chiller system and reduce the requirement on other cooling systems within an aircraft, the condenser may reject its heat to a desired location using a heat exchanger. The galley chiller system includes at least one evaporator that receives fluid from the condenser. A first evaporator absorbs heat from a galley, which may include a bank of carts. The first evaporator is arranged in ducting that carries cooled air to the carts. A second evaporator may absorb heat from a cabin recirculation air duct of the aircraft cooling system. In this manner, the evaporators of the inventive galley chilling system cools not only the galley carts but also provides supplemental cooling to the aircraft cooling system thereby reducing its cooling requirements.

Abstract: An air conditioning system is provided that includes first and second turbines and a compressor. The second turbine is in fluid communication with a pack outlet. A passage fluidly connects the first turbine and the pack outlet. A valve is associated with the passages and is movable between open and closed positions. In the open position, the valve permits flow through the passageway from the first turbine directly to the pack outlet thereby bypassing the second turbine and reducing the resistance to the flow through the system. The valve is opened at higher altitudes to change the typical series fluid connection between the turbines to a parallel fluid connection. In this configuration, the air conditioning system operates more efficiently using reduced air pressure provided to the system. Another valve is also opened to permit additional reduction in the air pressure required.

Abstract: The present invention provides an air generation unit (AGU) including a pressurized air source, such as an engine providing pressurized air. First and second air cycle machine (ACM) are fluidly connected to the pressurized air source for receiving the air. A heat exchanger interconnects the first and second ACMs. The heat exchanger mechanically supports the first and second ACMs by flexible isolators, which accommodates the thermo expansion of the heat exchanger through out the operation of the AGU. The heat exchanger includes a primary heat exchanger that cools the air from the air source. The ACMs each include a compressor receiving the air from the primary heat exchanger to provide compressed air. The compressed air is sent to a secondary heat exchanger to be cooled. The compressed air is passed through a condenser and a water collector to remove moisture from the air for being sent to a first turbine.

Abstract: A galley chiller system for an aircraft includes at least one condenser having a refrigerant fluid. The fluid within the condenser rejects heat to a first surrounding environment. To more efficiently use the condenser of the galley chiller system and reduce the requirement on other cooling systems within an aircraft, the condenser may reject its heat to a desired location using a heat exchanger. The galley chiller system includes at least one evaporator that receives fluid from the condenser. A first evaporator absorbs heat from a galley, which may include a bank of carts. The first evaporator is arranged in ducting that carries cooled air to the carts. A second evaporator may absorb heat from a cabin recirculation air duct of the aircraft cooling system. In this manner, the evaporators of the inventive galley chilling system cools not only the galley carts but also provides supplemental cooling to the aircraft cooling system thereby reducing its cooling requirements.

Abstract: An air generation unit includes first and second air cycle machines (ACMs), each having first and second turbines. A manifold is arranged between the first and second ACMs and is in fluid communciation with each of the first and second turbines of the first and second ACMs. A condenser is arranged between the ACMs and is in fluid communication with the manifold. First and second valves are disposed within the manifold and control flow of air between the turbines and the condenser. An actuator is assembly is connected to the valves for moving the valves between a plurality of positions. The valves selectively close off or prevent the flow of air from the turbines of one of the ACMs in the event that the ACM is not needed or malfunctions.

Abstract: An air generation unit includes first and second air cycle machines (ACMs), each having first and second turbines. A manifold is arranged between the first and second ACMs and is in fluid communication with each of the first and second turbines of the first and second ACMs. A condenser is arranged between the ACMs and is in fluid communication with the manifold. First and second valves are disposed within the manifold and control flow of air between the turbines and the condenser. An actuator is assembly is connected to the valves for moving the valves between a plurality of positions. The valves selectively close off or prevent the flow of air from the turbines of one of the ACMs in the event that the ACM is not needed or malfunctions.

Abstract: The present invention provides an air generation unit (AGU) including a pressurized air source, such as an engine providing pressurized air. First and second air cycle machine (ACM) are fluidly connected to the pressurized air source for receiving the air. A heat exchanger interconnects the first and second ACMs. The heat exchanger mechanically supports the first and second ACMs by flexible isolators, which accommodates the thermo expansion of the heat exchanger through out the operation of the AGU. The heat exchanger includes a primary heat exchanger that cools the air from the air source. The ACMs each include a compressor receiving the air from the primary heat exchanger to provide compressed air. The compressed air is sent to a secondary heat exchanger to be cooled. The compressed air is passed through a condenser and a water collector to remove moisture from the air for being sent to a first turbine.

Abstract: An integrated environmental control system is disclosed for providing conditioned supply air to loads such as a passenger cabin of an aircraft. The system comprises at least two shafts, each shaft having a fan, compressor, and turbine mechanically secured to the shaft; common heat transfer components including primary and secondary heat exchangers, a reheater, and a condenser with a water collector; lines that deliver the supply air separately through the compressors and turbines of each shaft and deliver the supply air in common through the common heat transfer components to the load; and shutoff valves secured in fluid communication with each turbine.

Abstract: A dual-pack, aircraft environmental control system has each pack dedicated to providing a temperature-controlled air supply to a corresponding compartment, either the crew or passenger, of the aircraft. Each refrigeration pack is fed hot, compressed bleed air from an associated turbine engine on the aircraft. During normal operation, the pack associated with a particular compartment on the aircraft provides the air supply with independent temperature control to that compartment. However, during failure of one of the refrigeration packs and the resulting operation of the other pack, the environmental control system is able to provide independent temperature control of the air supplied to each compartment.

Abstract: An air supply and conditioning system 10 is provided having a constant speed air blower 26 whose output is controlled by a thermostatic throttle and check valve 28. The throttle and check valve provides a minimum air flow below a minimum ambient temperature, provides a maximum air flow above a maximum temperature, and provides a roughly linearly increasing flow from the minimum to the maximum ambient temperature. The air blower draws air through a pair of nuclear and biological contamination filters 22 from the ambient and impels the air through an air conditioning portion 14 and a pressurization door 42.