[특허]Aircraft with thrust vectoring for switchably providing upper surface blowing

The Boeing Company

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특허 상세정보

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Aircraft with thrust vectoring for switchably providing upper surface blowing

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B04C-023/00
미국특허분류(USC)	244/012.5; 244/023.D
출원번호	US-0730357 (2003-12-08)
§371/§102 date	20030910 (20030910)
발명자 / 주소	Cummings, Darold B. Kutzmann, Aaron J. Droney, Christopher K.
출원인 / 주소	The Boeing Company
대리인 / 주소	Harness Dickey &
인용정보	피인용 횟수 : 8 인용 특허 : 11

초록
▼

Aircraft having thrust vectoring for switchably providing upper surface blowing. The aircraft generally includes a wing and an engine. The engine can be rotatably supported to supporting structure to allow the engine to be controllably rotated relative to the wing, and/or the engine can include a thrust vectoring nozzle. The engine's thrust vectoring capabilities allow the exhaust flow to be controllably vectored to switch on or off upper surface blowing depending on the aircraft's phase of operation. During a first phase, the exhaust flow can be vectored to flow across the upper wing surface to provide upper surface blowing to augment lift. During a second phase, the exhaust flow can be discharged generally downstream or rearwardly. The engine is positioned relative to the wing such that the exhaust flow does not provide upper surface blowing during the second phase.

대표
청구항
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1. A method of operating a jet engine on a mobile platform having at least one lift-producing surface, the method comprising:using the engine to generate an exhaust flow;controllably moving at least a nozzle of the engine into a corresponding one of a plurality of configurations including at least:a first configuration in which the exhaust flow is directed to flow across an upper surface of the lift-producing surface to provide upper surface blowing;a second configuration in which the exhaust flow is discharged to flow generally downstream; andthe engine being disposed sufficiently above and ahead of the lift-producing surface such that the exhaust flow does not provide upper surface blowing and, thereby, aerodynamic performance of the lift-producing surface is unaffected by upper surface blowing when the second configuration is used.2. The method of claim 1, wherein:the nozzle comprises a thrust vectoring nozzle; andcontrollably moving at least the nozzle of the engine comprises controllably moving the thrust vectoring nozzle.3. The method of claim 2, wherein the thrust vectoring nozzle is faired when the second configuration is used.4. The method of claim 1, wherein controllably moving at least the nozzle of the engine comprises controllably rotating the engine relative to the lift-producing surface.5. The method of claim 1, wherein:the mobile platform comprises an aircraft; andthe lift-producing surface comprises a wing.6. The method of claim 5, further comprising:using the first configuration during a high-lift phase of operation of the aircraft; andusing the second configuration during a cruising phase of operation of the aircraft.7. The method of claim 5, wherein the engine is sufficiently above and ahead of the wing such that the exhaust flow does not contact an upper surface of the wing when the second configuration is used.8. The method of claim 5, wherein the engine is disposed sufficiently above and ahead of the wing so that performance of the aircraft is unaffected by surface scrubbing of the exhaust flow across an upper surface of the wing when the second configuration is used.9. The method of claim 1, further comprising causing the exhaust flow to laterally diffuse.10. An aircraft, comprising:a wing having an upper surface;a jet engine including a thrust vectoring nozzle;the nozzle being controllably movable into a corresponding one of a plurality of configurations including at least:a first configuration in which the nozzle is positioned to direct an exhaust flow across the upper wing surface to provide upper surface blowing to augment lift;a second configuration in which the nozzle is positioned to discharge the exhaust flow generally downstream; andthe engine being disposed sufficiently above and ahead of the wing such that the exhaust flow does not provide upper surface blowing and, thereby, aerodynamic performance of the wing is unaffected by upper surface blowing when the nozzle is in the second configuration.11. The aircraft of claim 10, wherein the nozzle is faired in the second configuration.12. The aircraft of claim 10, wherein the nozzle is adapted to cause lateral diffusion of the exhaust flow.13. The aircraft of claim 12, wherein the nozzle includes a generally oval shaped cross-section.14. The aircraft of claim 10, wherein the engine is disposed sufficiently above and ahead of the wing such that the exhaust flow does not contact the upper wing surface when the nozzle is in the second configuration.15. The aircraft of claim 10, wherein the engine is disposed sufficiently above and ahead of the wing so that aircraft performance is unaffected by surface scrubbing of the exhaust flow across the upper wing surface when the nozzle is in the second configuration.16. An aircraft, comprising:a wing having an upper surface;a jet engine rotatably supported to supporting structure of the aircraft;the engine being controllably rotatable relative to the wing into a corresponding one of a plurality of configurations including at least:a first configuration in which the engine is rotated to discharge the exhaust flow across the upper wing surface to provide upper surface blowing to augment lift;a second configuration in which the engine is rotated to discharge the exhaust flow generally downstream; andthe engine being disposed sufficiently above and ahead of the wing such that the exhaust flow does not provide upper surface blowing and, thereby, aerodynamic performance of the wing is unaffected by upper surface blowing when the engine is in the second configuration.17. The aircraft of claim 16, wherein the engine is faired in the second configuration.18. The aircraft of claim 16, wherein the engine includes a nozzle adapted to cause lateral diffusion of the exhaust flow.19. The aircraft of claim 18, wherein the nozzle includes a generally oval shaped cross-section.20. The aircraft of claim 16, wherein the engine is disposed sufficiently above and ahead of the wing such that the exhaust flow does not contact the upper wing surface when the engine is in the second configuration.21. The aircraft of claim 16, wherein the engine is disposed sufficiently above and ahead of the wing so that performance of the aircraft is unaffected by surface scrubbing of the exhaust flow across the upper wing surface when the engine is in the second configuration.22. A method of operating a jet engine on a mobile platform having at least one airfoil, the method comprising:using the engine to generate an exhaust flow;controllably vectoring the exhaust flow depending on a phase of operation of the mobile platform, the controllably vectoring including:vectoring the exhaust flow to flow across a surface of the airfoil to provide surface blowing to augment aerodynamic force generated by the airfoil during a first phase of operation of the mobile platform;vectoring the exhaust flow to flow generally downstream during a second phase of operation of the mobile platform; andthe engine being positioned sufficiently above and ahead of the airfoil such that the exhaust flow does not provide surface blowing and, thereby, aerodynamic performance of the airfoil is unaffected by surface blowing when the exhaust flow is vectored to flow generally downstream.23. The method of claim 22, wherein the controllably vectoring comprises controllably moving a thrust vectoring nozzle of the engine.24. The method of claim 22, wherein the controllably vectoring comprises controllably rotating the engine relative to the airfoil.25. The method of claim 22, further comprising causing the exhaust flow to laterally diffuse.26. The method of claim 22, wherein the mobile platform comprises an aircraft, and the aerodynamic force comprises lift.

이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 8

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The Boeing Company (1)

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Aircraft with thrust vectoring for switchably providing upper surface blowing

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이 특허에 인용된 특허 (11)

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Aircraft with thrust vectoring for switchably providing upper surface blowing

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이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 8

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