Environmental control system supply precooler bypass
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-099/00
F02C-006/08
F02C-006/04
출원번호
US-0036534
(2011-02-28)
등록번호
US-8397487
(2013-03-19)
발명자
/ 주소
Sennoun, Mohammed El Hacin
Dinsmore, Nicholas Rowe
Miller, Brandon Wayne
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
8인용 특허 :
15
초록▼
A precooler for cooling compressor bleed air for an environmental control system includes a heat exchanger in fluid communication with a source of cooling air and operable for cooling the bleed air. A variable bypass valve between a bleed air source and environmental control system is operable for b
A precooler for cooling compressor bleed air for an environmental control system includes a heat exchanger in fluid communication with a source of cooling air and operable for cooling the bleed air. A variable bypass valve between a bleed air source and environmental control system is operable for bypassing at least a portion of the compressor bleed air around the heat exchanger. The cooling air may be a portion of fan air modulated by a variable fan air valve. The bleed air source may be selectable between the low pressure bleed air source and a high pressure bleed air source. One method includes flowing the compressor bleed air from a single low pressure source only and increasing thrust sufficiently to meet a minimum level of pressure of the bleed air during one engine out aircraft operating condition during approach or loitering.
대표청구항▼
1. A gas turbine engine compressor bleed air supply system comprising: a compressor air supply precooler for cooling compressor bleed air from a bleed air source and operably connected in supply flow communication with an environmental control system operable for conditioning cabin air and/or provid
1. A gas turbine engine compressor bleed air supply system comprising: a compressor air supply precooler for cooling compressor bleed air from a bleed air source and operably connected in supply flow communication with an environmental control system operable for conditioning cabin air and/or providing cooling for avionics and/or other equipment,a bleed air outlet line connecting the compressor air supply precooler to the environmental control system,the precooler including an air-to-air heat exchanger in fluid communication with a source of cooling air and operable for cooling the compressor bleed air,the source of cooling air being a fan of the gas turbine engine,a variable bypass valve disposed between the bleed air source and environmental control system, andthe variable bypass valve operable for bypassing at least a portion of the compressor bleed air around the heat exchanger. 2. A gas turbine engine compressor bleed air supply system as claimed in claim 1 further comprising: the bleed air source being a low pressure bleed air source disposed between first and last stages of a compressor,the cooling air being a portion of fan air from the fan, anda variable fan air valve disposed between the source of cooling air and the heat exchanger. 3. A gas turbine engine compressor bleed air supply system as claimed in claim 2 further comprising the bleed air source being selectable between the low pressure bleed air source and a high pressure bleed air source. 4. A gas turbine engine compressor bleed air supply system as claimed in claim 3 further comprising the high pressure bleed air source being the last stage of the high pressure compressor. 5. A gas turbine engine compressor bleed air supply system comprising: a compressor air supply precooler for cooling compressor bleed air from a bleed air source and operably connected in supply flow communication with an environmental control system operable for conditioning cabin air and/or providing cooling for avionics and/or other equipment,a bleed air outlet line connecting the compressor air supply precooler to the environmental control system,the bleed air source being selectable between low and high pressure bleed air sources of a gas turbine engine high pressure compressor,the precooler including an air-to-air heat exchanger in fluid communication with a source of cooling air and operable for cooling the compressor bleed air,the source of cooling air being a fan of the gas turbine engine,a variable bypass valve disposed between the bleed air source and environmental control system, andthe variable bypass valve operable for bypassing at least a portion of the compressor bleed air around the heat exchanger. 6. A gas turbine engine compressor bleed air supply system as claimed in claim 5 further comprising: the high pressure compressor including first and last stages and an intermediate stage therebetween,the low and high pressure bleed air sources being the intermediate and last stages,the cooling air being a portion of fan air from the fan, anda variable fan air valve disposed between the source of cooling air and the heat exchanger. 7. A gas turbine engine compressor bleed air supply system as claimed in claim 6 further comprising: a bleed air inlet line connected to and in selective flow communication with the low and high pressure bleed air sources,the bleed air inlet line connected to and in flow communication with a heat exchanger cooling circuit in the air-to-air heat exchanger for cooling the compressor bleed air,the bleed air outlet line connecting the heat exchanger cooling circuit to the environmental control system, andthe variable bypass valve being a bypass throttle valve disposed in a bleed air bypass line between the bleed air inlet line and the bleed air outlet line. 8. A gas turbine engine compressor bleed air supply system as claimed in claim 7 further comprising: a high pressure bleed shutoff valve disposed in a high pressure bleed line between the high pressure bleed air source and the bleed air inlet line, andan electronic control controllingly connected to the bypass throttle valve and the variable fan air valve. 9. A gas turbine engine compressor bleed air supply system as claimed in claim 8 further comprising the electronic control controllingly connected to the high pressure bleed shutoff valve. 10. A gas turbine engine compressor bleed air supply system as claimed in claim 6 further comprising: the precooler being an integrated precooler including an integrated variable precooler bypass for bypassing the compressor bleed air around the heat exchanger,a bleed air inlet line connected to and in selective flow communication with the low and high pressure bleed air sources,the bleed air inlet line connected to and in flow communication with a diffuser,the diffuser in selective flow communication with the air-to-air heat exchanger for cooling at least a portion of the compressor bleed air and in selective flow communication with a bypass duct in the integrated precooler,the heat exchanger and the bypass duct being in parallel flow relationship and in flow communication with an exhaust outlet of the integrated precooler,the bleed air outlet line connecting the exhaust outlet to the environmental control system, andthe variable bypass valve including a bypass door disposed between the heat exchanger and the bleed air inlet line. 11. A gas turbine engine compressor bleed air supply system as claimed in claim 10 further comprising a high pressure bleed shutoff valve disposed in a high pressure bleed line between the high pressure bleed air source and the bleed air inlet line and an electronic control controllingly connected to the variable bypass valve and the variable fan air valve. 12. A gas turbine engine compressor bleed air supply system as claimed in claim 11 further comprising the electronic control controllingly connected to the high pressure bleed shutoff valve. 13. An aircraft comprising: two or more aircraft gas turbine engines and an environmental control system within the aircraft,each aircraft gas turbine engine including in serial flow communication a fan, a high pressure compressor, an annular combustor, a high pressure turbine for powering the high pressure compressor, and a low pressure turbine for powering the fan,an annular nacelle surrounding the fan,a core cowl surrounding the high pressure compressor, the combustor, and the high pressure turbine,an annular bypass duct located radially between the annular nacelle and the core cowl,a compressor air supply precooler for cooling compressor bleed air from a bleed air source in the high pressure compressor,the compressor air supply precooler operably connected in supply flow communication with the environmental control system operable for conditioning cabin air and/or providing cooling for avionics and/or other equipment,a bleed air outlet line connecting the compressor air supply precooler to the environmental control system,the precooler including an air-to-air heat exchanger in fluid communication with a source of cooling air from the bypass duct,the source of cooling air being a fan of the gas turbine engine,the precooler operable for cooling the compressor bleed air,a variable bypass valve disposed between the bleed air source and environmental control system, andthe variable bypass valve operable for bypassing at least a portion of the compressor bleed air around the heat exchanger. 14. An aircraft as claimed in claim 13 further comprising: the source of cooling air being the fan located upstream of the bypass duct,the bleed air source being a low pressure bleed air source disposed between first and last stages of a compressor,the cooling air being a portion of fan air from the bypass duct, anda variable fan air valve disposed between the bypass duct and the heat exchanger. 15. An aircraft as claimed in claim 14 further comprising the bleed air source being selectable between the low pressure bleed air source and a high pressure bleed air source disposed between the low pressure bleed air source and the combustor. 16. An aircraft as claimed in claim 15 further comprising the high pressure bleed air source being the last stage of a compressor. 17. An aircraft as claimed in claim 15 further comprising: a bleed air inlet line connected to and in selective flow communication with the low and high pressure bleed air sources,the bleed air inlet line connected to and in flow communication with a heat exchanger cooling circuit in the air-to-air heat exchanger for cooling the compressor bleed air,the bleed air outlet line connecting the heat exchanger cooling circuit to the environmental control system,the variable bypass valve being a bypass throttle valve disposed in a bleed air bypass line between the bleed air inlet line and the bleed air outlet line,a high pressure bleed shutoff valve disposed in a high pressure bleed line between the high pressure bleed air source and the bleed air inlet line, andan electronic control controllingly connected to the bypass throttle valve and the variable fan air valve. 18. An aircraft as claimed in claim 17 further comprising further comprising the electronic control controllingly connected to the high pressure bleed shutoff valve. 19. An aircraft as claimed in claim 15 further comprising: the precooler being an integrated precooler including an integrated variable precooler bypass for bypassing the compressor bleed air around the heat exchanger,a bleed air inlet line connected to and in selective flow communication with the low and high pressure bleed air sources,the bleed air inlet line connected to and in flow communication with a diffuser,the diffuser in selective flow communication with the air-to-air heat exchanger for cooling at least a portion of the compressor bleed air and in selective flow communication with a bypass duct in the integrated precooler,the heat exchanger and the bypass duct being in parallel flow relationship and in flow communication with an exhaust outlet of the integrated precooler,the bleed air outlet line connecting the exhaust outlet to the environmental control system,the variable bypass valve including a bypass door disposed between the heat exchanger and the bleed air inlet line,a high pressure bleed shutoff valve disposed in a high pressure bleed line between the high pressure bleed air source and the bleed air inlet line, andan electronic control controllingly connected to the variable bypass valve and the variable fan air valve. 20. An aircraft as claimed in claim 19 further comprising the high pressure bleed air source being the last stage of a compressor. 21. An aircraft as claimed in claim 20 further comprising the electronic control controllingly connected to the high pressure bleed shutoff valve. 22. A method for supplying compressor bleed air to an environmental control system of an aircraft: flowing low pressure bleed air bled from a single low pressure source to a compressor air supply precooler for cooling the low pressure bleed air,flowing the low pressure bleed air to an environmental control system operable for conditioning cabin air and/or providing cooling for avionics and/or other equipment,flowing the low pressure bleed air through a bleed air outlet line connecting the compressor air supply precooler to the environmental control system,the precooler being an air-to-air heat exchanger in fluid communication with a source of cooling air and operable for cooling the compressor bleed air,the source of cooling air being a fan of the gas turbine engine,a variable bypass valve disposed between the bleed air source and environmental control system,the variable bypass valve operable for bypassing at least a portion of the compressor bleed air around the heat exchanger,the single low pressure source being an intermediate or lower pressure stage of a high pressure HP compressor wherein the intermediate or lower pressure stage is located between a first stage and a last stage of the of the high pressure HP compressor,detecting one engine out aircraft operating condition during approach or loitering of the aircraft, andincreasing a thrust level of the engine sufficiently to meet a predetermined or calculated minimum level of pressure of the compressor bleed air from the single low pressure source.
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이 특허에 인용된 특허 (15)
Coffinberry George A. (West Chester OH), Aircraft gas turbine engine bleed air energy recovery apparatus.
Suciu, Gabriel L.; Glahn, Jorn A.; Merry, Brian D.; Dye, Christopher M., Bypass air-pump system within the core engine to provide air for an environmental control system in a gas turbine engine.
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