Auxiliary power unit inlet door having openings formed therein
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-033/02
B64D-041/00
B64C-001/00
출원번호
US-0063324
(2013-10-25)
등록번호
US-9145214
(2015-09-29)
발명자
/ 주소
Payangapadan, Murali Krishnan
Kiran, Vunnam
Gundeti, Lavan Kumar
Sheoran, Yogendra Yogi
Bouldin, Bruce Dan
출원인 / 주소
HONEYWELL INTERNATIONAL INC.
대리인 / 주소
Ingrassia Fisher & Lorenz, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
An inlet door system includes a duct, an inlet door, and a plurality of openings. The duct is configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of an aircraft. The duct includes an inlet port, an outlet port, and a duct sidewall extending betwee
An inlet door system includes a duct, an inlet door, and a plurality of openings. The duct is configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of an aircraft. The duct includes an inlet port, an outlet port, and a duct sidewall extending between the inlet port and the outlet port. The inlet door includes an inner surface, an outer surface, and an outer peripheral edge between the inner and outer surfaces. The door is rotationally coupled to the duct, and is configured to selectively rotate between a closed position and a plurality of open positions. The openings extend through the inlet door between the inner surface and outer surface, and each opening is disposed adjacent to the outer peripheral edge.
대표청구항▼
1. An inlet door system for providing air to at least an auxiliary power unit (APU) contained within an aircraft, the inlet door system comprising: a duct configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of the aircraft, the duct including an i
1. An inlet door system for providing air to at least an auxiliary power unit (APU) contained within an aircraft, the inlet door system comprising: a duct configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of the aircraft, the duct including an inlet port, an outlet port, and a duct sidewall extending between the inlet port and the outlet port, the duct sidewall defining an air flow passage between the inlet port and the outlet port;an inlet door including an inner surface, an outer surface, and an outer peripheral edge between the inner and outer surfaces, the outer peripheral edge of the inlet door is defined by a front edge, a back edge, a first side edge, and a second side edge, the inlet door rotationally coupled to the duct, the inlet door configured to selectively rotate between (i) a closed position, in which the inlet door seals the air inlet port and prevents air flow into the inlet port, and (ii) a plurality of open positions, in which the inlet door does not seal the air inlet and allows air flow into the inlet port; anda plurality of openings extending through the inlet door between the inner surface and the outer surface, each opening disposed adjacent to only the first side edge and the second side edge. 2. The system of claim 1, wherein: the openings disposed adjacent to the first side edge are spaced evenly, and the openings disposed adjacent to the second side edge are spaced evenly. 3. The system of claim 1, wherein the inlet door comprises: an insert portion that extends through the inlet port and is disposed within the air flow passage when the inlet door is in the closed position; anda seal portion disposed outward of the insert portion and inward of the outer peripheral edge, the seal portion engaging the inlet duct when the inlet door is in the closed position. 4. The system of claim 3, wherein the openings extend through the seal portion. 5. The system of claim 1, further comprising: an actuator coupled to the inlet door and configured to selectively move the inlet door between the closed position and one or more of the open positions. 6. An inlet door system for providing air to at least an auxiliary power unit (APU) contained within an aircraft, the inlet door system comprising: a duct configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of the aircraft, the duct including an inlet port, an outlet port, and a duct sidewall extending between the inlet port and the outlet port, the duct sidewall defining an air flow passage between the inlet port and the outlet port;an inlet door including an inner surface, an outer surface, and an outer peripheral edge between the inner and outer surfaces, the outer peripheral edge defined by a front edge, a back edge, a first side edge, and a second side edge, the inlet door rotationally coupled to the duct, the inlet door configured to selectively rotate between (i) a closed position, in which the inlet door seals the air inlet port and prevents air flow into the inlet port, and (ii) a plurality of open positions, in which the inlet door does not seal the air inlet and allows air flow into the inlet port;an actuator coupled to the inlet door and configured to selectively move the inlet door between the closed position and one or more of the open positions; anda plurality of openings extending through the inlet door between the inner surface and the outer surface, each of the openings disposed adjacent to only the front edge, the first side edge, and the second side edge. 7. The system of claim 6, wherein: the openings disposed adjacent to the front edge are spaced evenly, the openings disposed adjacent to the first side edge are spaced evenly, and the openings disposed adjacent to the second side edge are spaced evenly. 8. The system of claim 6, wherein the inlet door comprises: an insert portion that extends through the inlet port and is disposed within the air flow passage when the inlet door is in the closed position; anda seal portion disposed outward of the insert portion and inward of the outer peripheral edge, the seal portion engaging the inlet duct when the inlet door is in the closed position. 9. The system of claim 8, wherein the openings extend through the seal portion. 10. The system of claim 6, further comprising: an actuator coupled to the inlet door and configured to selectively move the inlet door between the closed position and one or more of the open positions.
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이 특허에 인용된 특허 (3)
Wainfan Barnaby Sam ; Liu Yu Ping ; Rihn Daniel R. ; Leggett Douglas William ; Georges Martin James ; Philhower Jeffry Scott ; Shultz Douglas Ellwood ; Boccados Charles, Aircraft engine air intake system.
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