IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0745957
(2008-12-01)
|
등록번호 |
US-8602360
(2013-12-10)
|
우선권정보 |
FR-07 59493 (2007-12-03) |
국제출원번호 |
PCT/FR2008/052166
(2008-12-01)
|
§371/§102 date |
20100603
(20100603)
|
국제공개번호 |
WO2009/077690
(2009-06-25)
|
발명자
/ 주소 |
- Porte, Alain
- Chene, Gilles
- Hormiere, Arnaud
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
8 |
초록
▼
An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame de
An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating de-icing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition.
대표청구항
▼
1. An aircraft nacelle comprising: a first pipe (32),a peripheral wall (34),a lip (36) oriented toward a front of the aircraft nacelle that connects to said first pipe (32) at a point B and said peripheral wall (34) at a point A and that delimits an air intake, as well as a frost treatment system th
1. An aircraft nacelle comprising: a first pipe (32),a peripheral wall (34),a lip (36) oriented toward a front of the aircraft nacelle that connects to said first pipe (32) at a point B and said peripheral wall (34) at a point A and that delimits an air intake, as well as a frost treatment system that treats a zone that extends along a longitudinal section of the point A that is provided at the peripheral wall (34) at the point B that is provided at the first pipe (32), anda front frame (38) that delimits with said lip (36) a second pipe (51) in which the hot air for de-icing circulates,wherein said first pipe (32) comprises a coating (44) for the acoustic treatment, comprising, from the inside to the outside, a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure,wherein the front frame (38) comprises a junction zone with at least one of the lip (36) and the first pipe (32) that is offset toward the front of the aircraft nacelle relative to point B,wherein third pipes (50) are provided at the inside surface of the lip (36) and the pipe (32) for conveying the hot air from said second pipe (51) for hot air up to discharges that are arranged at a circle that corresponds to point B,wherein said third pipes (50) extend beyond the junction zone between the front frame (38), and at least one of the lip (36) and the first pipe (32) and are delimited by at least one partition that isolates the hot air from a coating (44) for the acoustic treatment. 2. The aircraft nacelle according to claim 1, wherein said at least one partition is made of a heat-resistant material and is constructed and arranged to isolate the hot air from the coating for the acoustic treatment that is made of composite material. 3. The aircraft nacelle according to claim 2, comprising: a first panel (56) that forms the first pipe (32), anda second panel (54) that forms the lip (36),wherein said first panel (56) and said second panel (54) are superposed at a junction zone,wherein said at least one partition comes in the form of a two-part block (52), a first part (58, 70, 88) that is inserted between the superposed first panel and second panel and that comprises at least one of a projecting and hollow element that is constructed and arranged to provide the third pipes (50) between said first panel and second panel so as to link an inside and an outside of the aircraft nacelle, and a second part (60, 72, 90) disposed adjacently to a single panel, the latter arranged inside at the level of the junction zone so as to provide protection from heat. 4. The aircraft nacelle according to claim 1, further comprising: a first panel (56) that forms the first pipe (32), anda second panel (54) that forms the lip (36),wherein said first panel (56) and said second panel (54) are superposed at a junction zone,wherein said at least one partition comes in the form of a two-part block (52), a first part (58, 70, 88) that is inserted between the superposed first panel and second panel and that comprises at least one of a projecting and hollow element that is constructed and arranged to provide the third pipes (50) between said first panel and second panel so as to link an inside and an outside of the aircraft nacelle, and a second part (60, 72, 90) disposed adjacently to a single panel, the latter arranged inside at the level of the junction zone so as to provide protection from heat. 5. The aircraft nacelle according to claim 4, wherein the block (52) comprises at least one groove (68, 96) on at least one of the surfaces of the block (52) that is constructed and arranged to delimit a third pipe (50) of the third pipes (50). 6. The aircraft nacelle according to claim 5, wherein the at least one groove (68, 96) emerge at a first edge (80, 98) via first ports (82, 100) that communicate with the second pipe (51), and at a second edge (76, 92) via second ports (84, 102) that communicate with the outside of the aircraft nacelle. 7. The aircraft nacelle according to claim 5, wherein the two-part block (52) comprises a shoulder (86) with a height that is approximately equal to a thickness of the second panel (54), which delimits the first part (88) in the form of a thin plate that is inserted between the first panel (56) and said second panel (54), extending at least over a length of a superposition zone of said first panel (56) and said second panel (54), and the second part (90), the second part (90) being beveled-shaped, with an edge (92) whose surface is arranged at an aerodynamic surface of said first panel (56) and said second panel (54) and an inclined face (94) against which the first panel (56) is flattened, and wherein the two-part block (52) comprises the at least one groove (96) only at a surface opposite the second panel (54). 8. The aircraft nacelle according to claim 5, wherein the two-part block (52) comprises a shoulder (86) with a height that is approximately equal to a thickness of the second panel (54), which delimits the first part (88) in the form of a thin plate that is inserted between the first panel (56) and said second panel (54), extending at least over a length of a superposition zone of said first panel (56) and said second panel (54), and the second part (90), the second part (90) being beveled-shaped, with an edge (92) whose surface is arranged at an aerodynamic surface of said first panel (56) and said second panel (54) and an inclined face (94) against which the first panel (56) is flattened, and wherein the two-part block (52) comprises the at least one groove (96) only at a surface opposite the second panel (54).
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