[특허]Aircraft ground support air conditioning unit with cooling air flow control doors

Honeywell International, Inc.

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Aircraft ground support air conditioning unit with cooling air flow control doors

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-023/00 B60H-001/00
미국특허분류(USC)	165/299; 165/203; 454/267; 062/172; 062/401
출원번호	US-0354773 (2003-01-30)
발명자 / 주소	Leathers,Thomas M.
출원인 / 주소	Honeywell International, Inc.
대리인 / 주소	Ingrassia Fisher &
인용정보	피인용 횟수 : 2 인용 특허 : 11

초록

A system and method of supplying conditioned air to an aircraft environmental control system during ground support operations that uses at least one flow control door to control the flow of cooling air through a heat exchanger. The heat exchanger removes heat from a flow of compressed air supplied to the system. The temperature of the conditioned compressed air is controlled by selectively positioning the flow control door, which regulates cooling air flow through the heat exchanger.

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I claim: 1. A temperature-controlled air supply system for use with an aircraft on the ground and for connection to a compressed air source, the air supply system comprising: a primary air flow passage having at least an inlet port and an outlet port, the inlet port coupled to receive a flow of primary air; a first heat exchanger having at least a first fluid flow path and a second fluid flow path, the first fluid flow path fluidly coupled in series with the primary air flow passage, the second flow path coupled to receive a flow of compressed air from the compressed air source, the first heat exchanger adapted to transfer heat between the primary air and the compressed air and supply at least conditioned compressed air; a plurality of flow control doors mounted on the primary air flow passage, each flow control door independently moveable between an open position and a closed position to control primary air flow through the primary air flow passage, whereby primary air flow through the first heat exchanger is controlled to thereby control conditioned compressed air temperature; a temperature sensor mounted downstream of the first heat exchanger second fluid flow path and operable to supply a temperature signal representative of the conditioned compressed air; a controller coupled to receive the temperature signal from the temperature sensor and operable, in response thereto, to supply door control signals; and a plurality of door actuators coupled to receive the control signals and operable, in response thereto, to independently move the flow control doors to control primary air flow through the primary air flow passage. 2. The system of claim 1, further comprising: a bypass flow passage fluidly coupled in parallel with the primary air flow passage; and a bypass valve mounted on the bypass flow passage and selectively moveable between a closed and an open position to control primary air flow rate through the bypass flow passage, whereby primary air flow through the first heat exchanger is further controlled to thereby further control conditioned compressed air temperature. 3. The system of claim 2, wherein the controller is further responsive to the temperature signal to supply at least one valve control signal, and wherein the system further comprises: at least one valve actuator coupled to receive the valve control signal and operable, in response thereto, to selectively move the bypass valve to control primary air flow through the bypass flow passage. 4. The system of claim 1, further comprising: at least one cooling turbine having an air intake port and an air exhaust port; and a second heat exchanger coupled to receive the conditioned compressed air from the first heat exchanger and turbine exhaust air from cooling turbine air exhaust port, and adapted to transfer heat from the conditioned compressed air to the cooled air exhausted from the cooling turbine and supply warmed turbine exhaust air and further conditioned compressed air. 5. The system of claim 4, wherein the cooling turbine air intake is coupled to receive the further conditioned compressed air from the second heat exchanger. 6. The system of claim 5, further comprising: a moisture separator coupled between the second heat exchanger and the cooling turbine air intake. 7. The system of claim 1, further comprising: a fan operable to draw the primary air from a primary air source into the primary air flow passage. 8. The system of claim 7, wherein the fan is configured to pull the primary air through the first heat exchanger. 9. The system of claim 7, wherein the fan is configured to push the primary air through the first heat exchanger. 10. The system of claim 1, wherein the primary air is ambient air. 11. A method of conditioning compressed air from an aircraft ground support equipment, the method comprising: supplying a flow of compressed air through a first flow path in a heat exchanger; supplying a flow of primary air through a plurality of independently actuated flow control doors and through a second flow path in the heat exchanger to thereby condition the compressed air to a desired temperature; sensing a temperature that is representative of the conditioned compressed air; and based on the sensed temperature, controlling primary air flow through the second flow path by independently actuating one or more of the flow control doors that are mounted in the second flow path, whereby the temperature of the conditioned compressed air is controlled. 12. The method of claim 11, further comprising: selectively diverting a portion of the primary air away from the heat exchanger second flow path to further control primary air flow therethrough. 13. The method of claim 11, further comprising: flowing the conditioned compressed air through a second heat exchanger; and flowing cooling turbine exhaust air through the second heat exchanger to thereby further cool the conditioned compressed air and warm the turbine exhaust air. 14. The method of claim 13, further comprising: supplying the warmed turbine exhaust air to the aircraft. 15. The method of claim 13, further comprising: flowing the further cooled conditioned compressed air into an air intake of the cooling turbine. 16. The method of claim 11, further comprising: supplying the primary air from ambient surroundings. 17. The method of claim 11, further comprising: supplying the compressed air from an auxiliary power unit (APU). 18. A temperature-controlled air supply system for use with an aircraft on the ground and for connection to a compressed air source, the air supply system comprising: primary air flow means for receiving and supplying a flow of primary air, first heat exchanger means for (i) receiving the flow of primary air from the primary air flow means and a flow of compressed air from the compressed air source, (ii) transferring heat between the primary air and the compressed air and, (iii) supplying at least conditioned compressed air; flow control means for controlling primary air flow through the primary air flow means, whereby primary air flow through the first heat exchanger means is controlled to thereby control conditioned compressed air temperature; sensor means, mounted downstream of the first heat exchanger means, for supplying a temperature signal representative of the conditioned compressed air temperature; controller means for (i) receiving the temperature signal and (ii) supplying door control signals; and actuator means for (i) receiving the control signals and (ii) independently moving the flow control means to control primary air flow through the primary air flow means. 19. The system of claim 18 further comprising: bypass flow means fluidly coupled in parallel with the primary air flow means for bypassing a portion of the primary air flow around the first heat exchanger means; and bypass valve means, mounted on the bypass flow means, for controlling primary air flow rate through the bypass flow means, whereby primary air flow through the first heat exchanger means is further controlled to thereby further control conditioned compressed air temperature. 20. The system of claim 19, wherein said controller means further supplies, upon receipt of the temperature signal, at least one valve control signal, and wherein the system further comprises: valve actuator means for (i) receiving the valve control signal and (ii) selectively moving the bypass valve means to control primary air flow through the bypass flow means. 21. The system of claim 18, further comprising: turbine means for supply turbine exhaust air; and second heat exchanger means for (i) receiving the conditioned compressed air from the first heat exchanger means and the turbine exhaust air from the turbine means, (ii) transferring heat from the conditioned compressed air to the turbine exhaust air, and (iii) supplying warmed turbine exhaust air and further conditioned compressed air. 22. The system of claim 21, wherein the turbine means receives the further conditioned compressed air from the second heat exchanger means. 23. The system of claim 22, further comprising: moisture separation means, coupled between the second heat exchanger means and the turbine means, for removing moisture from the further conditioned compressed air. 24. The system of claim 18, further comprising: fan means for flowing the primary air from a primary air source into the primary air flow means. 25. A temperature-controlled air supply system for use with a compressed air source and for connection to an aircraft on the ground, the air supply system comprising: a primary air flow passage having at least an inlet port and an outlet port, the inlet port coupled to receive a flow of primary air; a first heat exchanger having at least a first fluid flow path and a second fluid flow path, the first fluid flow path fluidly coupled in series with the primary air flow passage, the second flow path coupled to receive a flow of compressed air from the compressed air source, the first heat exchanger adapted to transfer heat between the primary air and the compressed air and supply at least conditioned compressed air; a plurality of flow control doors mounted on the primary air flow passage, each flow control door independently moveable between an open position and a closed position to control primary air flow through the primary air flow passage, whereby primary air flow through the first heat exchanger is controlled to thereby control conditioned compressed air temperature; a bypass flow passage fluidly coupled in parallel with the primary air flow passage; a bypass valve mounted on the bypass flow passage and selectively moveable between a closed and an open position to control primary air flow rate through the bypass flow passage, whereby primary air flow through the first heat is exchanger is further controlled to thereby further control conditioned compressed air temperature; a second heat exchanger coupled to receive the conditioned compressed air from the first heat exchanger and turbine exhaust air from a cooling turbine, and adapated to transfer heat from the conditioned compressed air to the turbine exhaust air and supply warmed turbine exhaust air and further conditioned compressed air; at least one cooling turbine having an air intake in fluid communication with the second heat exchanger to receive therefrom the further conditioned compressed air and an air exhaust in fluid communication with the second heat exchanger to supply thereto the turbine exhaust air; a moisture separator coupled between the second heat exchanger and the cooling turbine air intake; and a fan operable to draw the primary air from the primary air source into the primary air flow passage.

이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 2

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특허 상세정보

Aircraft ground support air conditioning unit with cooling air flow control doors

초록

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이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 2

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특허 상세정보

Aircraft ground support air conditioning unit with cooling air flow control doors

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이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 2

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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