[특허]Nacelle flow assembly

United Technologies Corporation

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Nacelle flow assembly

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-029/00 B64D-033/02
미국특허분류(USC)	244/053B; 244/207; 244/208
출원번호	US-0938975 (2007-11-13)
등록번호	US-9004399 (2015-04-14)
발명자 / 주소	Jain, Ashok K.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 84

초록

A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume.

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1. A nacelle assembly for a turbine engine, comprising: a cowl for the turbine engine, said cowl extending along an axis wherein at least a portion of said cowl is axially forward of a fan of the turbine engine, said cowl having a first surface spaced from a second surface, said second surface configured to define a bypass flow passage radially inward of said second surface;a flow volume spaced between said first surface and said second surface;a plurality of holes disposed on said first surface and said second surface of the cowl and arranged to communicate air outside the nacelle assembly into said flow volume, each of said plurality of holes configured to alter local air pressure about one of said first surface and said second surface of said cowl, said plurality of holes in communication with said flow volume, and said plurality of holes extending between said flow volume and an exterior of the nacelle assembly; and a device in communication with said flow volume for altering local pressure at one of said first surface and said second surface, wherein said device is configured to increase local pressure. 2. The nacelle assembly of claim 1 wherein said flow volume has a wall dividing said flow volume into a first chamber and a second chamber. 3. The nacelle assembly of claim 2 wherein said first chamber is configured to direct a first air flow in a first direction and said second chamber is configured to direct a second air flow in a second direction, said first direction different from said second direction. 4. The nacelle assembly of claim 3 wherein said first air flow is towards one of said first surface and said second surface and said second air flow is away from one of said first surface and said second surface. 5. The nacelle assembly of claim 2, wherein said first chamber is sealed from said second chamber. 6. The nacelle assembly of claim 1 wherein said device is configured to decrease local pressure. 7. The nacelle assembly of claim 1 wherein said cowl extends at least partially around an axis and along said axis. 8. The nacelle assembly of claim 7 wherein said plurality of holes extends circumferentially on said cowl about said axis. 9. The nacelle assembly of claim 7 wherein said plurality of holes extends on said cowl along said axis. 10. The nacelle assembly of claim 1, wherein the device is a suction device. 11. The turbine engine assembly of claim 1, wherein at least one of said plurality of holes is located at an inner radial side of the exterior and at least another of aid plurality of holes is located at an outer radial side of the exterior. 12. A turbine engine assembly comprising: a turbine engine extending along an axis;a fan cowl having a first surface and a second surface, said second surface defining a bypass flow passage, said fan cowl extending at least partially around said axis and along said axis;a flow volume spaced between said first surface and said second surface, wherein said flow volume has a wall dividing said flow volume into a first chamber and a second chamber, wherein said first chamber is configured to direct a first air flow in a first direction and said second chamber is configured to direct a second air flow in a second direction, said first direction different from said second direction;a core cowl extending at least partially about said turbine engine, said fan cowl spaced from said core cowl to further define said bypass flow passage; anda plurality of holes disposed on said first surface and said second surface of said fan cowl, said plurality of holes extending between said flow volume and an exterior of the nacelle assembly, each of said plurality of holes configured to alter local air pressure about one of said first surface and said second surface of said cowl, said plurality of holes in communication with said flow volume, wherein said first air flow increases local air pressure at one of said first surface and said second surface and said second air flow decreases local air pressure at one of said first surface and said second surface. 13. The turbine engine assembly of claim 12, wherein said plurality of holes are equiaxially spaced apart. 14. The turbine engine assembly of claim 12, wherein said plurality of holes are arranged in a plurality of axial rows, each row equally spaced apart. 15. A nacelle assembly comprising: a cowl for a turbine engine, said cowl extending along an axis wherein at least a portion of said cowl is axially forward of a fan of the turbine engine, said cowl having a first surface spaced from a second surface, said second surface configured to define a bypass flow passage radially inward of said second surface;a flow volume spaced between said first surface and said second surface;a plurality of holes disposed on said first surface and said second surface of the cowl and arranged to communicate air outside the nacelle assembly into said flow volume, each of said plurality of holes configured to alter local air pressure about one of said first surface and said second surface of said cowl, said plurality of holes in communication with said flow volume, and said plurality of holes extending between said flow volume and an exterior of the nacelle assembly; anda device in communication with said flow volume for altering local pressure at one of said first surface and said second surface, wherein the device is a blowing device. 16. A nacelle assembly comprising: a cowl for a turbine engine, said cowl extending along an axis wherein at least a portion of said cowl is axially forward of a fan of the turbine engine, said cowl having a first surface spaced from a second surface, said second surface configured to define a bypass flow passage radially inward of said second surface;a flow volume spaced between said first surface and said second surface, wherein said flow volume has a wall dividing said flow volume into a first chamber and a second chamber, wherein a control unit independently and separately controls air flow through the first chamber and the second chamber; anda plurality of holes disposed on said first surface and said second surface of the cowl and arranged to communicate air outside the nacelle assembly into said flow volume, each of said plurality of holes configured to alter local air pressure about one of said first surface and said second surface of said cowl, said plurality of holes in communication with said flow volume, and said plurality of holes extending between said flow volume and an exterior of the nacelle assembly. 17. The nacelle assembly of claim 16, wherein said first chamber is in communication with a first blowing device and a first suction device and said second chamber is in communication with a second blowing device and a second suction device. 18. The nacelle assembly of claim 17, wherein said control unit directs the first blowing device blows air flow in a first direction in said first chamber and the second suction device sucks air flow in a second direction in said second chamber. 19. The nacelle assembly of claim 17, wherein said control unit directs the first suction device blows air flow in a first direction in said first chamber and the second blowing device blows air flow in a second direction in said second chamber. 20. The nacelle assembly of claim 17, wherein said control unit directs one of the first blowing device and the second blowing device, and the first suction device and the second suction device, operate simultaneously to move air flow in each chamber in a first direction.

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