Integrated power and pressurization system
AssigneeHoneywell International Inc.
InventorsJean-Luc Derouineau, Bjoern Schenk, Clarence Lui
Life of this patent
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Abstract
An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can supply compressed air for cabin pressurization and environmental cooling functions, and can generate electrical power for various electrical loads. The system further includes one or more electrically driven compressors.
Claims14
An integrated power and cabin pressurization system for selectively generating electrical power and supplying cabin pressurization air to an aircraft cabin, the system comprising:
- a combustor having a combustor air inlet and a combustor air outlet, the combustor air inlet adapted to receive a flow of compressed air;
- a power turbine having an air inlet coupled to selectively receive a flow of air from the combustor and to selectively receive a flow of air from the aircraft cabin not via the combustor, the power turbine operable, upon receipt of the flow of air, to supply a rotational drive force;
- a motor-generator coupled to the power turbine and configured to operate in either a motor mode, in which the motor-generator supplies a rotational drive force, or a generate mode, in which the motor-generator receives the rotational drive force supplied by the power turbine;
- a compressor having a ram air inlet and a compressed air outlet, the compressor coupled to only receive the rotational drive force supplied from the power turbine or the motor-generator and no other electrically powered prime movers, the compressor operable, upon receipt of the rotational drive force, to supply compressed air to the combustor air inlet via the compressor compressed air outlet;
- a cabin air exhaust conduit coupled between the power turbine air inlet and the aircraft cabin;
- a turbine air supply valve mounted on the cabin air exhaust conduit and moveable between an open position, in which the power turbine air inlet is in fluid communication with the aircraft cabin, and a closed position, in which the power turbine air inlet is not in fluid communication with the aircraft cabin;
- a first cabin air supply conduit coupled between the compressed air outlet and the aircraft cabin;
- a first cabin air supply valve mounted on the cabin air supply conduit and moveable between an open position, in which the compressed air outlet is in fluid communication with the aircraft cabin, and a closed position, in which the compressed air outlet is not in fluid communication with the aircraft cabin;
- an electric motor operable to supply a rotational drive force;
- a second compressor having a second compressor ram air inlet and a second compressor compressed air outlet, the second compressor coupled to only receive the rotational drive force supplied from the electric motor and operable, upon receipt thereof, to supply compressed air to the second compressor compressed air outlet;
- a second cabin air supply conduit coupled between the second compressor compressed air outlet and the aircraft cabin;
- and
- a second cabin air supply valve mounted on the second cabin air supply conduit and moveable between an open position, in which the second compressor compressed air outlet is in fluid communication with the aircraft cabin, and a closed position, in which the second compressor compressed air outlet is not in fluid communication with the aircraft cabin.
Dependencies are inferred from the claim text.