IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0877493
(2010-09-08)
|
등록번호 |
US-8297038
(2012-10-30)
|
우선권정보 |
GB-0916491.4 (2009-09-21) |
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
2 |
초록
▼
An aircraft propulsion arrangement including a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted to an external surface of an aircraft component so as to define part of an aerodynamic surface to a flow of ambient air, and a
An aircraft propulsion arrangement including a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted to an external surface of an aircraft component so as to define part of an aerodynamic surface to a flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger. A method of operating the gas turbine aircraft engine, the method involving the steps of: (a) flowing engine oil through the heat exchanger and thus into heat-exchange relationship with the ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along the duct arrangement and into heat-exchange relationship with the engine oil in the heat exchanger, wherein the directing step (b) is performed selectively.
대표청구항
▼
1. A method of operating a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted to an external surface of an aircraft component so as to define part of an aerodynamic surface to a flow of ambient air, and a duct arrangement fl
1. A method of operating a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted to an external surface of an aircraft component so as to define part of an aerodynamic surface to a flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger, the method involving the steps of (a) flowing the engine oil through the heat exchanger and thus into heat-exchange relationship with the ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along the duct arrangement and into heat-exchange relationship with the engine oil in the heat exchanger, wherein the directing step (b) is performed selectively. 2. A method according to claim 1, wherein the directing step (b) is performed selectively in dependence on a temperature of the engine oil measured within the gas turbine aircraft engine. 3. A method according to claim 2, wherein the compressor gas is directed into heat exchange relationship with the engine oil in the heat exchanger when the measured temperature of the engine oil is above a predetermined threshold value. 4. A method according to claim 3, wherein the bleed flow of compressor gas is stopped or reduced when the measured temperature of the engine oil is below the predetermined threshold value. 5. A method according to claim 1, wherein the directing step (b) is performed selectively in dependence on aircraft flight cycle conditions. 6. A method according to claim 5, wherein the compressor gas is directed into heat exchange relationship with the engine oil in the heat exchanger during at least one of the following flight cycle conditions: stationary; taxi; take-off; landing-approach; and reverse-thrust. 7. A method according to claim 6, wherein the bleed flow of compressor gas is stopped or reduced during at least one of the following flight conditions: climb; cruise; and descent. 8. A method according to claim 1, wherein the directing step (b) is performed selectively in dependence on an airspeed of the aircraft. 9. A method according to claim 8, wherein the compressor gas is directed into heat exchange relationship with the engine oil in the heat exchanger when the airspeed of the aircraft is below a determined or predetermined threshold value. 10. A method according to claim 9, wherein the bleed flow of compressor gas is stopped or reduced when the airspeed of the aircraft is above the threshold value. 11. A method according to claim 9, wherein the threshold value is determined in dependence on aircraft flight cycle conditions. 12. A method according to claim 1, wherein the gas turbine aircraft engine is supported by a pylon to which the heat exchanger is mounted, the method further comprising the step of exhausting the bleed flow of compressor gas into wake produced by the pylon. 13. A method according to claim 1, wherein the bleed flow of compressor gas is directed across the aerodynamic surface of the heat exchanger. 14. A method according to claim 1, wherein the bleed flow of compressor gas is directed across a surface of the heat exchanger opposed to the aerodynamic surface of the heat exchanger. 15. A propulsion arrangement for an aircraft, the arrangement comprising: a heat exchanger mounted to an external surface of an aircraft component so as to define part of an aerodynamic surface to a flow of ambient air; a gas turbine engine having a compressor with a bleed offtake configured to bleed gas from the compressor; an oil system configured to route engine oil through the heat exchanger, and a duct arrangement fluidly connecting the bleed offtake to the heat exchanger and configured to direct a flow of the compressor gas across the heat exchanger in heat-exchange relationship with the engine oil, the arrangement further including a flow controller actuable to regulate the flow of the compressor gas across the heat exchanger. 16. An arrangement according to claim 15, wherein the flow controller is programmed to regulate the flow of the compressor gas across the heat exchanger in dependence on at least one of the following: (i) a temperature of the engine oil within the gas turbine engine; (ii) an airspeed of the aircraft; and (iii) aircraft flight cycle conditions. 17. An arrangement according to claim 15, wherein the gas turbine engine is supported by a pylon to which the heat exchanger is mounted, the pylon having an exhaust aperture, and the duct arrangement being configured to direct the flow of the compressor gas into the pylon, through the exhaust aperture and into wake produced by the pylon during movement through the ambient air. 18. An arrangement according to claim 17, wherein the exhaust aperture is located upstream of the heat exchanger, relative to the flow of the compressor gas. 19. An arrangement according to claim 18, wherein the heat exchanger is located in a region of a trailing edge of the pylon. 20. An arrangement according to claim 17, wherein the exhaust aperture is located downstream of the heat exchanger, relative to the flow of the compressor gas. 21. An arrangement according to claim 20, wherein the exhaust aperture is located in the region of the trailing edge of the pylon. 22. An arrangement according to claim 17, wherein the flow controller comprises a mechanism operable to vary a size of the exhaust aperture. 23. An arrangement according to claim 15, wherein the flow controller comprises a control valve within the gas turbine engine. 24. An arrangement according to claim 15, wherein the oil system includes a bypass valve selectively operable to prevent the flow of engine oil through the heat exchanger. 25. An arrangement according to claim 15, wherein the heat exchanger is remote from the gas turbine engine, and the engine oil system includes self-sealing couplings arranged to permit disconnection and reconnection of the oil system to the heat exchanger, the oil system further comprising a bypass valve connected across the self-sealing couplings. 26. A method of operating a gas turbine aircraft engine supported by a pylon, the pylon defining an aerodynamic surface and incorporating a heat exchanger, the gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through the heat exchanger, and a duct arrangement fluidly connecting the compressor to the heat exchanger, the method involving: flowing engine oil through the heat exchanger, directing a bleed flow of compressor gas drawn from the compressor along the duct arrangement and into heat-exchange relationship with the engine oil in the heat exchanger, and exhausting the bleed flow of compressor gas into wake produced by the pylon. 27. An aircraft propulsion arrangement, the arrangement including: a gas turbine engine supported by a pylon and having a compressor with a bleed offtake configured to bleed gas from the compressor, the pylon defining an aerodynamic surface and incorporating a heat exchanger; an oil system configured to route engine oil through the heat exchanger; and a duct arrangement fluidly connecting the bleed offtake to the heat exchanger and configured to direct a flow of the compressor gas across the heat exchanger in heat-exchange relationship with the engine oil and to exhaust the flow of the compressor gas into wake produced by the pylon.
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