Tandem air inlet apparatus and method for an airborne mobile platform
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-033/02
B64D-033/00
출원번호
UP-0553181
(2006-10-26)
등록번호
US-7624944
(2009-12-16)
발명자
/ 주소
Parikh, Pradip G
Atkey, Warren A
출원인 / 주소
The Boeing Company
대리인 / 주소
Harness, Dickey & Pierce, P.L.C.
인용정보
피인용 횟수 :
7인용 특허 :
9
초록▼
A tandem inlet apparatus for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet for feeding air to a cabin air compressor (CAC) of an air conditioning pack carried on the mobile platform. A flush heat exchanger inle
A tandem inlet apparatus for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet for feeding air to a cabin air compressor (CAC) of an air conditioning pack carried on the mobile platform. A flush heat exchanger inlet is disposed forwardly of the Pitot inlet and longitudinally aligned with the Pitot inlet, for supplying cooling air to a heat exchanger of the air conditioning pack. By locating the heat exchanger inlet forwardly and longitudinally in line with the Pitot inlet, the heat exchanger inlet is able to effectively swallow a large portion of the boundary layer, which results in a thinner boundary layer at the inlet face of the Pitot inlet. This enables a smaller throat area Pitot inlet to be used, as well as a shorter diverter height to be employed with the Pitot inlet, while still realizing an improved recovery factor (RF) performance with the Pitot inlet. The reduced height Pitot inlet also enables drag to be reduced.
대표청구항▼
What is claimed is: 1. A tandem ram air inlet apparatus for a high speed airborne mobile platform, comprising: a protruding Pitot inlet disposed adjacent to an exterior surface of said mobile platform, for channeling airflow to a first subsystem of said mobile platform; said protruding Pitot inlet
What is claimed is: 1. A tandem ram air inlet apparatus for a high speed airborne mobile platform, comprising: a protruding Pitot inlet disposed adjacent to an exterior surface of said mobile platform, for channeling airflow to a first subsystem of said mobile platform; said protruding Pitot inlet including a face having spaced apart upper and lower lip portions and oriented in a plane that is non-parallel to said exterior surface of said mobile platform; a diverter for spacing said face a predetermined distance above said exterior surface by at least about 0.25 inch; and a secondary inlet formed forwardly of said Pitot inlet and longitudinally aligned with said protruding Pitot inlet on said exterior surface, and mounted generally flush with said exterior surface for channeling ram air to a second subsystem of said mobile platform, and also modifying a boundary layer adjacent to said exterior surface. 2. The apparatus of claim 1, wherein said first subsystem comprises a cabin air compressor associated with an air conditioning pack on said mobile platform. 3. The apparatus of claim 1, wherein said second subsystem comprises a heat exchanger associated with an air conditioning pack on said mobile platform. 4. The apparatus of claim 1, wherein said apparatus provides a recovery factor of at least about 0.8 at a cabin air compressor inlet face in communication with said protruding Pitot inlet. 5. The apparatus of claim 1, wherein said secondary inlet includes at least one modulated door to vary airflow into said flush secondary inlet. 6. The apparatus of claim 1, further comprising a deployable shield disposed forwardly of said protruding Pitot inlet and aft of the flush inlet for the secondary subsystem, relative to a direction of airflow over said protruding Pitot inlet, and longitudinally aligned with said protruding Pitot inlet, for controllably blocking foreign object debris (FOD) ingestion into said protruding Pitot inlet, while still allowing airflow into the protruding Pitot inlet during ground runs prior to takeoff and after landing. 7. The apparatus of claim 1, wherein said protruding Pitot inlet includes a throat aspect ratio of between about 5:1 and about 6:1. 8. The apparatus of claim 1, wherein said protruding Pitot inlet includes a diverter for supporting an inlet opening approximately about 0.25 inch-3.0 inch (6 mm-76.20 mm) outside said exterior surface. 9. An aircraft comprising: a fuselage; a protruding Pitot inlet disposed adjacent to an exterior surface of said fuselage, for channeling airflow to a cabin air compressor of an air conditioning pack on said aircraft; said Pitot inlet including a face that is formed in a plane extending non-parallel to said exterior surface of said fuselage; a diverter forming a surface generally non-parallel to the exterior surface of the fuselage, the diverter spacing the face approximately 0.25 inch to about 3.0 inch from the exterior surface; and a flush mounted heat exchanger inlet formed forwardly of said Pitot inlet and longitudinally aligned with said Pitot inlet on said exterior surface, relative to a direction of airflow over an exterior surface of said fuselage when said aircraft is in flight, and mounted generally flush said exterior surface of said fuselage, that channels ram airflow to a heat exchanger of said air conditioning pack, and that also modifies a boundary layer adjacent to said exterior surface. 10. The aircraft of claim 9, wherein said protruding Pitot inlet provides a recovery factor of at least about 0.8 at a cabin air compressor face of a cabin air compressor in communication with said protruding Pitot inlet. 11. The aircraft of claim 9, wherein said flush mounted heat exchanger inlet includes at least one modulated door to vary airflow entering said heat exchanger inlet. 12. The aircraft of claim 9, further comprising a deployable shield disposed forwardly of said protruding Pitot inlet and aft of the flush heat exchanger inlet relative to a direction of airflow over said protruding Pitot inlet, and longitudinally aligned with said protruding Pitot inlet, for controllably blocking airflow into said protruding Pitot inlet. 13. The aircraft of claim 9, wherein said protruding Pitot inlet includes a diverter for supporting an inlet opening of said protruding Pitot inlet outside said exterior surface of said fuselage. 14. The aircraft of claim 9, wherein said protruding Pitot inlet includes a throat aspect ratio of between about 5:1 and about 6:1. 15. A method for directing airflow into inlets of first and second subsystems on an aircraft, comprising: using a protruding Pitot inlet supported on a fuselage of said aircraft to direct a first airflow stream into said first subsystem; using a diverter to space a face of the protruding Pitot inlet at least about 0.25 inch from an exterior surface of the fuselage; positioning an additional airflow inlet, generally flush with said fuselage, in said fuselage forwardly of said face of said protruding Pitot inlet and longitudinally aligned with said protruding Pitot inlet, relative to a free stream airflow over said fuselage when said aircraft is in flight, that directs a second airflow stream into said second subsystem and that modifies a boundary layer forwardly of said face of said protruding Pitot inlet. 16. The method of claim 15, further comprising using a deployable shield positioned forwardly of said face of said protruding Pitot inlet to controllably block foreign obiect debris (FOD) into said protruding Pitot inlet during ground runs prior to takeoff and after landing. 17. The method of claim 15, further comprising using a modulatable door with said additional airflow inlet to control airflow admitted into said additional airflow inlet. 18. The method of claim 15, wherein using said protruding Pitot inlet and said additional airflow inlet to direct first and second airflow streams into said first and second subsystems comprises: using said protruding Pitot inlet to direct said first airflow stream into a cabin air compressor; and using said additional airflow inlet to direct said second airflow stream into a heat exchanger.
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