[특허]Thermoelectric generator on an aircraft bleed system

The Boeing Company

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Thermoelectric generator on an aircraft bleed system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-006/06
미국특허분류(USC)	060/785; 060/266
출원번호	US-0632250 (2009-12-07)
등록번호	US-8484983 (2013-07-16)
발명자 / 주소	Gao, Lijun Liu, Shengyi Chien, Chin-Hsi
출원인 / 주소	The Boeing Company
대리인 / 주소	Weiss & Moy, P.C.
인용정보	피인용 횟수 : 4 인용 특허 : 2

초록

A device for producing electrical power has a thermoelectric device coupled to an aircraft bleed system for generating electrical power using temperature differentials between ram air and bleed air. A system control is coupled to the ram air and the bleed air to control a temperature of the bleed air and to control a temperature gradient of the thermoelectric device.

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1. A device for producing electrical power in an aircraft comprising: a bleed air system bleeding air from one of an engine or compressor;a thermoelectric device coupled to said bleed air system for generating said electrical power using temperature differentials between ram air and bleed air;the thermoelectric device including an air-to-air heat exchanger receiving said ram air and said bleed air;a bypass line for routing bleed air around the thermoelectric device; anda system control coupled to the ram air and the bleed air to control a temperature of the bleed air and to control a temperature gradient of the thermoelectric device by selectively bypassing bleed air around the thermoelectric device. 2. The device of claim 1, wherein said bleed air system comprises: an ozone converter for reducing ozone levels within said bleed air;the air-to-air heat exchanger receiving said ram air and said bleed air from said ozone converter, wherein said ram air cools said bleed air; andan air separator receiving said cooled bleed air, wherein said air separator separates said cooled bleed air into nitrogen and oxygen enriched fractions. 3. The device of claim 2, further comprising a fuel tank for said nitrogen enriched fraction. 4. The device of claim 1, wherein said bleed air provides a heat source and said ram air provides a cold source to create said temperature differentials. 5. The device of claim 1, wherein said electrical power is generated from said thermoelectric device when said temperature differential is above a threshold value. 6. The device of claim 2, further comprising a bypass flow valve coupled to the air separator to allow the bleed air to be passed through the air-to-air heat exchanger or bypass the air-to-air heat exchanger based on a temperature of the bleed air. 7. The device of claim 1, wherein said system control displays a system status. 8. A method for generating power on an aircraft bleed system comprising: receiving ram air;receiving bleed air from one of an engine or compressor;directing said ram air and said bleed air through a thermoelectric cell coupled to said aircraft bleed system for generating electrical energy, the thermoelectric cell including an air-to-air heat exchanger receiving said ram air and said bleed air;a bypass line for routing bleed air around the thermoelectric cell; andcontrolling a temperature of the bleed air and a temperature gradient of the thermoelectric device by selectively bypassing bleed air around the thermoelectric cell. 9. The method of claim 8, further comprising cooling said bleed air by said thermoelectric cell reducing an amount of ram air used by said aircraft bleed system. 10. The method of claim 9, wherein reducing an amount of ram air decreases air drag. 11. The method of claim 9, wherein cooling said bleed air further comprises cooling said bleed air to about 230° C. 12. The method of claim 8, further comprising coupling the thermoelectric cell to a nitrogen generation system. 13. A system for producing electrical power in an aircraft comprising: a thermoelectric device with an air-to-air heat exchanger receiving bleed air from one of an engine or compressor, wherein said thermoelectric device produces electrical energy from a temperature difference between said bleed air and ram air while cooling said bleed air;a bypass line for routing bleed air around the thermoelectric device; anda system control coupled to the ram air and the bleed air to control a temperature of the bleed air and to control a temperature gradient of the thermoelectric device by selectively bypassing bleed air around the thermoelectric device. 14. The system of claim 13, wherein said air-to-air heat exchanger cools said bleed air using said ram air. 15. The system of claim 13, further comprising the system control controlling ram air flow and bleed air flow. 16. The system of claim 13, further comprising a nitrogen generation system coupled to said thermoelectric device. 17. The system device of claim 16, wherein said nitrogen generation system comprises: an ozone converter for reducing ozone levels within said bleed air;the air-to-air heat exchanger receiving said ram air and said bleed air from said ozone converter, wherein said ram air cools said bleed air; andan air separator receiving said cooled bleed air, wherein said air separator separates said cooled bleed air into nitrogen and oxygen enriched fractions.

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Thermoelectric generator on an aircraft bleed system

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Thermoelectric generator on an aircraft bleed system

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