Hamilton Sundstrand Corporation

Sundstrand Corporation

Steven E Squier

Charles E Lents

Mark Hamilton Severson

Wayne A Thresher

Michael K Sahm

Jules Ricardo Munoz

Luca Bertuccioli

Eric Alan Henderson

Richard C Welch

Robert Grennan

John N Rice

Jay Fletcher

Arthur Curtis Becker

An environmental control system for an aircraft is provided. The environmental control system comprises a bleed air system. Also included is a ram air system. Further included is an air pressure and temperature conditioning system, wherein bleed air and ram air are mixed to satisfy a cabin fresh air requirement. The air pressure and temperature conditioning system includes a compressor that pressurizes ram air. The air pressure and temperature conditioning system also includes a power turbine that expands bleed air, the pressurized ram air and expanded bleed air at identical pressures prior to mixing downstream of the compressor and the power turbine.

Blended flow air cycle system for environmental control

An environmental control system for an aircraft includes a bleed air system. Also included is a ram air system. Further included is an air pressure and temperature conditioning system, wherein bleed air and ram air are mixed to satisfy a cabin fresh air requirement.

An aircraft air provision system includes a power turbine that receives bleed air at a first pressure and provides rotational energy to a shaft and outputs output air at an intermediate pressure. The system also includes a compressor coupled to the shaft that receives input air at a second pressure that is lower than the first pressure and outputs compressed air having a pressure equal to the intermediate pressure and a mix chamber coupled to outputs of both the power turbine and the compressor where the output air and the compressed air are mixed. The system also includes a cooling turbine coupled to the shaft and that is in fluid communication with an output of the mix chamber.

The present invention relates to an electrically driven aircraft cabin and ventilation and environmental control system. The system includes at least one inlet for capturing ram air, an electrically driven compressor for pressurizing the ram air, and a thermal conditioning subsystem for thermally conditioning the pressurized ram air. The system further includes a subsystem for removing undesirable moisture from the thermally conditioned ram air.

Electrically driven aircraft cabin ventilation and environmental control system

The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.

Integrated system for providing aircraft environmental control

A method for assessing the reliability of an electrical power distribution system begins with identifying each element of the electrical power distribution system, and establishing characteristic data for each of these elements. The characteristic data at least identifies one operating characteristic of the element and further identifies interconnections of that element to other elements in the system. Next, at least one &ldquo;minimum cut&rdquo; is determined separating a first system element from a second system element, e.g., a power source from a load. The minimum cut is at least based upon the interconnection data. At least one third element is then identified, located on the minimum cut, and the reliability may then be assessed by evaluating the characteristic data of the at least one third element.

System reliability assessment tool

The bleed air requirements for a pressurization and environmental control system for the cabin (10) of an aircraft may be reduced by a system that includes a turbomachine (20) having a rotary compressor (22) driven by a turbine wheel (26). A ram air inlet (16) is connected to the compressor inlet (28) and the aircraft is provided with a cabin air exhaust port (18) which is connected to the outlet (34) of the turbine wheel (26). A heat exchanger (40) has a cabin inlet air flow path (42) and a cabin outlet air flow path (44) in heat exchange with one another. The cabin inlet air flow path (42) is connected to the outlet (30) of the compressor (22) and to the cabin (10) of the aircraft. The cabin outlet air flow path (44) is connected to the cabin (10) as well as to the inlet (32) of the turbine (26). A bleed air inlet port (36), (70) is adapted to be connected to the bleed air tap (14) of a turbine engine (12) and is connected to one of the flow paths (42, 44, 52, 60) between the compressor outlet (30) and the turbine wheel inlet (32).

Environmental control system with energy recovery and bleed air assist

Improved cooling of electronic heat loads aboard aircraft is achieved in a system including a sealable aircraft cabin (10), first and second electronic heat loads (38), (40) and a means (42) for maintaining a desired pressure within the cabin (10). A rotatable turbine wheel (16) is associated with an overboard dump port (32) such that air being dumped overboard from the cabin is expanded to rotate the turbine wheel (16). A mechanical load (20) is connected to the turbine wheel (16) for harnessing the rotation thereof and means (24), (60) are employed for using the air expanded by the turbine wheel (16) for cooling at least one of the loads (38), (40).

Cooling of aircraft electronic heat loads

Redundant components, and their volume and weight, used in on board gas generating systems are avoided in a fully integrated system for generating oxygen enriched air (OEA) and nitrogen enriched air (NEA) for a variety of purposes. A first separator (16) may provide OEA to a second separator (24) directly to provide oxygen for crew consumption or alternatively may provide OEA to a compressor (42) which in turn provides high pressure OEA to storage vessels (70), (72). The separator (16) also provides NEA alternatively to aircraft fuel tanks (60) for inerting them by direct flow or, after being compressed by the compressor (42) to an NEA storage system (50). NEA from the storage system (50) may additionally be used for fuel expulsion in a fuel system (96) associated with an auxiliary power unit/emergency power unit including a hot gas generator (74), the latter also receiving oxidant for the fuel in the form of OEA from one of the OEA storage tanks (72).

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Rockford, IL, United States of America

Steven E Squier