초록 ▼

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 ex

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.

대표청구항 ▼

1. An integrated environmental control system for an aircraft comprising:means for using engine bleed air to provide power to at least one aircraft component and to provide cooling to at least one of a flight deck and a cabin;said bleed air using means comprising an aircraft mounted accessory drive,

1. An integrated environmental control system for an aircraft comprising:means for using engine bleed air to provide power to at least one aircraft component and to provide cooling to at least one of a flight deck and a cabin;said bleed air using means comprising an aircraft mounted accessory drive, a turbine connected to said aircraft mounted accessory drive for providing power to said aircraft mounted accessory drive, and means for delivering said engine bleed air to an inlet of said turbine;means for delivering bleed air exiting said turbine to means for cooling said bleed air and delivering said cooled bleed air to said at least one of a flight deck and a cabin; andsaid delivering and cooling means comprising a first means for cooling said bleed air exiting said turbine, a compressor for increasing the pressure and temperature of said cooled bleed air exiting said first cooling means, a second cooling means for lowering the temperature of the pressurized bleed air exiting said compressor and an expansion turbine for generating shaft power for driving said compressor, said expansion turbine receiving said cooled pressurized bleed air from said second cooling means. 2. An integrated environmental control system according to claim 1, wherein said engine bleed air delivering means comprises means for delivering bleed air from a high pressure compressor stage. 3. An integrated environmental control system according to claim 1, wherein said first and second cooling means utilize ram air as a heat sink and wherein ram air from said first and second cooling means is delivered to cool aircraft components. 4. An integrated environmental control system according to claim 1, further comprising means for removing moisture from the cooled pressurized bleed air exiting said expansion turbine. 5. An integrated environmental control system according to claim 1, further comprising means for delivering a portion of said cooled bleed air to an avionics deck. 6. A method for providing environmental control for an aircraft comprising the steps of:bleeding air from an engine;delivering said bleed air to an inlet of a turbine;using said turbine to deliver power to an aircraft mounted accessory drive;cooling bleed air exiting said turbine and delivering said cooled bleed air to at least one of a flight deck and a cabin; andsaid bleed air cooling step comprises supplying said bleed air to an inlet of a compressor to increase the pressure and temperature of said bleed air and delivering said bleed air at said increased pressure and temperature to an inlet of an expansion turbine for driving a shaft to which said compressor is connected and to drop the temperature of said bleed air. 7. A method according to claim 6, wherein said air bleeding step comprises bleeding air from a high pressure compressor stage of said engine. 8. A method according to claim 6, wherein said bleed air cooling step further comprises passing said bleed air through a first cooling means using ram air as a heat sink prior to delivering said bleed air to said compressor inlet. 9. A method according to claim 8, wherein said bleed air cooling step further comprises passing said bleed air exiting said compressor through a second cooling means using ram air as a heat sink prior to delivering said bleed air to said expansion turbine. 10. A method according to claim 9, further comprising using said ram air exiting said first and second cooling means to cool at least one aircraft component. 11. A method according to claim 9, further comprising removing moisture from said cooled bleed air exiting said expansion turbine. 12. A method according to claim 6, further comprising delivering a portion of said cooled bleed air to an avionics deck for cooling avionics onboard said aircraft.