Aircraft nacelle including at least one radial partition between two conducts
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/20
B64D-033/02
출원번호
US-0270604
(2011-10-11)
등록번호
US-8851416
(2014-10-07)
우선권정보
FR-10 58430 (2010-10-15)
발명자
/ 주소
Porte, Alain
Lalane, Jacques
Chelin, Frederic
Surply, Thierry
출원인 / 주소
Airbus Operations (S.A.S.)
대리인 / 주소
Young & Thompson
인용정보
피인용 횟수 :
2인용 특허 :
4
초록▼
An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50′) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52′) that is in contact with the air stream and an ed
An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50′) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52′) that is in contact with the air stream and an edge (54, 54′) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54′)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.
대표청구항▼
1. An aircraft nacelle that channels a stream of air in a longitudinal direction, said nacelle comprising: two panels (50, 50′) placed end to end in the longitudinal direction, the two panels (50, 50′) including a vertical longitudinal plane, each panel comprising an exterior aerodynamic surface (52
1. An aircraft nacelle that channels a stream of air in a longitudinal direction, said nacelle comprising: two panels (50, 50′) placed end to end in the longitudinal direction, the two panels (50, 50′) including a vertical longitudinal plane, each panel comprising an exterior aerodynamic surface (52, 52′) that contacts the air stream and an end edge (54, 54′),a first of the panels (50) including an outside pipe (18) at an exterior aerodynamic surface (52, 52′) and an inside pipe (16), the end edge (54, 54′) of the first panel extending between the outside pipe (18) and the inside pipe (16),the end edge (54) of the first panel (50) contacting the end edge (54′) of a second of the panels (50′) and delimiting an annular release (68) therebetween; andplural spaced-apart partitions (58), each partition (58) being arranged radially in planes that contain the longitudinal direction and having a wall with a length that extend in the longitudinal direction across the release (68) from the end edge of the first panel to the end edge of the second panel, and a height extending between the outside pipe (18) and the inside pipe (16) of the first panel, with a thickness of the wall being less than the height of the wall, the partitions limiting circulation of air within the release (68). 2. The aircraft nacelle according to claim 1, with said nacelle comprising pressure gradients that vary along edges of the panels, wherein said partitions (58) are arranged at the largest gradients. 3. The aircraft nacelle according to claim 1, wherein the first panel defines an air intake. 4. The aircraft nacelle according to claim 3, wherein said partitions (58) are arranged radially in planes that contain the longitudinal direction. 5. The aircraft nacelle according to claim 3, wherein said partitions (58) are arranged in a radially symmetrical manner relative to the vertical longitudinal plane. 6. The aircraft nacelle according to claim 5, comprising four of said partitions (58), said four partitions (58) being arranged at 45°, 135°, 225°, and 315°, with respect to an origin corresponding to a top part of the two panels. 7. The aircraft nacelle according to claim 5, comprising six of said partitions (58), said six partitions (58) arranged at 45°, 90°, 135°, 225°, 270°, and 315°, with respect to an origin corresponding to a top part of the two panels. 8. The aircraft nacelle according claim 2, wherein the first panel defines an air intake. 9. The aircraft nacelle according to claim 8, wherein said partitions (58) are arranged radially in planes that contain the longitudinal direction. 10. The aircraft nacelle according to claim 4, wherein said partitions (58) are arranged in a radially symmetrical manner relative to the vertical longitudinal plane. 11. The aircraft nacelle according to claim 10, comprising four of said partitions (58), said four partitions (58) being arranged at 45°, 135°, 225°, and 315°, with respect to an origin corresponding to a top part of the two panels. 12. The aircraft nacelle according to claim 10, comprising six of said partitions (58), said six partitions (58) arranged at 45°, 90°, 135°, 225°, 270°, and 315°, with respect to an origin corresponding to a top part of the two panels. 13. The aircraft nacelle according to claim 1, wherein said release (68) defines an annular cavity, delimited between the end edge (54) of the first panel (50) and the end edge (54′) of the second panel (50′), free of any annular filling ring (42) between said partitions (58). 14. An aircraft nacelle that channels a stream of air in a longitudinal direction, said nacelle comprising: two panels (50, 50′) placed end to end in the longitudinal direction, the two panels (50, 50′) including a vertical longitudinal plane, each panel comprising an exterior aerodynamic surface (52, 52′) that contacts the air stream and an end edge (54, 54′),a first of the panels (50) defining an air intake and including an outside pipe (18) at an exterior aerodynamic surface (52, 52′) and an inside pipe (16), the end edge (54, 54′) of the first panel extending between the outside pipe (18) and the inside pipe (16),the end edge (54) of the first panel (50) contacting the end edge (54′) of a second of the panels (50′) and delimiting an annular release (68) therebetween;at least one partition (58) with i) a length that extends in the longitudinal direction across the release (68) from the end edge of the first panel to the end edge of the second panel, ii) a height extending between the outside pipe (18) and the inside pipe (16) of the first panel, and iii) a thickness of the wall being less than the height of the wall,the at least one partition (58) being arranged radially in planes that contain the longitudinal direction and limiting circulation of air within the release (68). 15. The aircraft nacelle according to claim 14, wherein plural of said at least one partition (58) are arranged radially in a symmetrical manner relative to the vertical longitudinal plane. 16. The aircraft nacelle according to claim 15, comprising four of said partitions (58), said four partitions (58) being arranged at 45°, 135°, 225°, and 315°, with respect to an origin corresponding to a top part of the two panels. 17. The aircraft nacelle according to claim 15, comprising six of said partitions (58), said six partitions (58) arranged at 45°, 90°, 135°, 225°, 270°, and 315°, with respect to an origin corresponding to a top part of the two panels. 18. The aircraft nacelle according to claim 13, wherein plural of said at least one partition (58) are arranged in a symmetrical manner, andwherein said release (68) defines an annular cavity, delimited between the end edge (54) of the first panel (50) and the end edge (54′) of the second panel (50′), free of any annular filling ring (42) between said partitions (58). 19. The aircraft nacelle according to claim 15, wherein said release (68) defines an annular cavity, delimited between the end edge (54) of the first panel (50) and the end edge (54′) of the second panel (50′), free of any annular filling ring (42) between said partitions (58). 20. The aircraft nacelle according to claim 16, wherein said release (68) defines an annular cavity, delimited between the end edge (54) of the first panel (50) and the end edge (54′) of the second panel (50′), free of any annular filling ring (42) between said partitions (58).
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