[특허]Nacelle with porous surfaces

Nacelle with porous surfaces 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/24 F02K-003/06 B64D-033/02 F02C-007/04
출원번호	US-0891991 (2010-09-28)
등록번호	US-8974177 (2015-03-10)
발명자 / 주소	Atassi, Oliver V.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 51

초록

A fan nacelle for a gas turbine engine includes a leading edge region with a flow path between an intake region in a nacelle outer surface and an exhaust region in a nacelle inner surface to locally modify a flow around the leading edge region during a predefined off-design condition.

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1. A fan nacelle for a gas turbine engine comprising: an annular leading edge region that extends around an axis and defines a flow path between an intake region at a nacelle radially outermost surface and an exhaust region at a nacelle radially innermost surface, wherein said exhaust region includes a porous structure; anda tertiary region within the innermost surface forward of the exhaust region, the tertiary region including a blind opening, the blind opening comprising a concave region formed in the nacelle radially innermost surface, straddling a shock line. 2. The fan nacelle as recited in claim 1, wherein said intake region includes another porous structure. 3. The nacelle assembly as recited in claim 2, wherein said porous structures include micro-pores. 4. The nacelle assembly as recited in claim 2, wherein said porous structures include slot-like structures. 5. The fan nacelle as recited in claim 2, wherein open areas of said porous structures are optimized to minimize losses at conditions other than a predefined off-design condition. 6. The fan nacelle as recited in claim 5, wherein said conditions other than said predefined off-design condition includes a cruise condition. 7. The fan nacelle as recited in claim 2, including an open flow path extending radially between the porous structures. 8. The fan nacelle as recited in claim 1, wherein said intake region and said exhaust region extend for a circumferential distance around a nacelle keel of said leading edge region axially forward of a throat region. 9. The fan nacelle as recited in claim 1, wherein said blind opening includes another porous structure. 10. The fan nacelle as recited in claim 1, wherein an axially forward-most point of said intake region is axially forward of an axially forward-most point of said exhaust region. 11. The fan nacelle as recited in claim 10, wherein an axially aft-most point of said intake region is axially forward of an axially aft-most point of said exhaust region. 12. The fan nacelle as recited in claim 1, wherein said intake region is located at a position on a nacelle keel within a captured streamline at a predefined angle of attack such that a portion of said captured stream line enters said intake region. 13. A nacelle assembly for a gas turbine engine comprising: a core nacelle defined about an engine centerline axis;a fan nacelle defined about said engine centerline axis and mounted at least partially around said core nacelle to define a fan bypass flow path, said fan nacelle defines a leading edge region that defines a flow path between an intake region at a nacelle radially outermost surface and an exhaust region at a nacelle radially innermost surface; anda tertiary region within the innermost surface forward of the exhaust region, the tertiary region including a blind opening, the blind opening comprising a concave region formed in the nacelle radially innermost surface, straddling a shock line. 14. The nacelle assembly as recited in claim 13, wherein said intake region and said exhaust region extend for a circumferential distance around a nacelle keel of said leading edge region axially forward of a throat region. 15. The nacelle assembly as recited in claim 13, wherein said intake region and said exhaust region each includes a porous structure. 16. The nacelle assembly as recited in claim 15, including an open flow path extending radially between the porous structures. 17. The nacelle assembly as recited in claim 13, wherein said porous structure includes micro-pores. 18. The nacelle assembly as recited in claim 13, wherein said tertiary region includes a porous structure. 19. The nacelle assembly as recited in claim 18, wherein said porous structure includes micro-pores. 20. A method to locally modify a flow around a leading edge region of a nacelle to move a captured streamline stagnation region forward and weaken a shock strength comprising: communicating a portion of a captured streamline through a flow path defined between an intake region in a nacelle outermost surface and an exhaust region in a nacelle innermost surface during a predefined off-design condition, wherein said exhaust region includes a porous structure; andlocating a tertiary region within the innermost surface forward of the exhaust region to straddle a shock line. 21. A method as recited in claim 20, further comprising: optimizing an open area of a porous structure within the intake region and the exhaust region to minimize losses at conditions other than the predefined off-design condition. 22. A method as recited in claim 20, further comprising: optimizing the flow path to minimize losses at conditions other than the predefined off-design condition. 23. A method as recited in claim 20, further comprising: defining the predefined off-design condition as a high-angle of attack condition. 24. A method as recited in claim 20, said tertiary region including a blind opening, and said blind opening is configured to axially span a shock such that suction occurs downstream of the shock and blowing occurs upstream of the shock.

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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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