IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0120025
(2009-09-17)
|
등록번호 |
US-8646723
(2014-02-11)
|
우선권정보 |
FR-08 56387 (2008-09-23) |
국제출원번호 |
PCT/FR2009/051750
(2009-09-17)
|
§371/§102 date |
20110321
(20110321)
|
국제공개번호 |
WO2010/034922
(2010-04-01)
|
발명자
/ 주소 |
- Porte, Alain
- Fargues, Matthieu
- Lalane, Jacques
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
11 |
초록
▼
An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acous
An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.
대표청구항
▼
1. An aircraft nacelle, comprising: an air intake (50) that includes an air intake pipe (54) located at a front of the nacelle;a power plant (52) with a fan located within a power plant pipe (56), the power plant (52) being located aft of the air intake (50), the power plant pipe (56) being an aft e
1. An aircraft nacelle, comprising: an air intake (50) that includes an air intake pipe (54) located at a front of the nacelle;a power plant (52) with a fan located within a power plant pipe (56), the power plant (52) being located aft of the air intake (50), the power plant pipe (56) being an aft extension of the air intake pipe (54);wherein the air intake pipe (54) channels air from the front of the nacelle in an aft direction toward the power plant pipe (56) to channel an incoming stream of air into the power plant pipe (56), a first primary portion of the incoming stream of air passing through the power plant, and a second secondary portion of the incoming stream of air being entrained by the fan and flowing into an annular pipe that is delimited by an inside wall of the power plant pipe (56) and an outside wall of the power plant,said air intake pipe (54) including i) a panel (58), the panel (58) integrating an acoustic treatment with an acoustically resistive porous layer (60) that is in contact with an aerodynamic stream that enters into the nacelle, at least one alveolar structure (62), and a reflective layer (64), the reflective layer (64) forming a rear surface of said panel (58), and ii) an edge (72) delimiting the air intake pipe (54), the edge (72) being a distal aft portion of the reflective layer (64) located aft adjacent an aft distal end of the alveolar structure (62); anda flange (66) connecting said air intake (50) and said power plant (52), said flange (66) comprising a first wing (68) connected to a flange of the power plant pipe and a second wing (76), the second wing (76) being connected to the reflective layer (64) forming the rear surface of said air intake (50) by a number of connecting elements, some of said connecting elements connecting the flange (66) to the edge (72) delimiting the air intake pipe (54), said connecting elements connecting the flange (66) to the edge (72) having central longitudinal axes (74) that are secant with the edge;wherein the flange (66) comprises, at said second wing (76) resting against the rear surface (64) of the panel (58), for each connecting element, a projection (78) with an inclined plane (80) that forms an angle with said second wing (76), andwherein each said connecting element connecting the flange (66) to the edge (72) extends through a corresponding one of said projections (78) so that the longitudinal axis of each said connecting element is perpendicular to the inclined plane;further comprising, for each connecting element, a structural reinforcement (82) comprising a top (84) having an inclined plane (92), wherein the connecting element is arranged from the projection to the structural reinforcement. 2. The aircraft nacelle according to claim 1, wherein the flange (66) further comprises, at said second wing (76), blind-type connecting elements. 3. The aircraft nacelle according to claim 2, wherein each projection (78) has a cross-section in a transverse plane in the shape of an inverted U, the inverted U shape of each projection (78) being flattened against the second wing (76), each projection (78) extending from the first wing (68) in a longitudinal direction in a direction toward the front of the nacelle, with a portion of each projection (78) that is oriented toward the front of the nacelle being inclined relative to the transverse plane in such a way as to delimit the inclined plane (80). 4. The aircraft nacelle according to claim 1, wherein each projection (78) has a cross-section in a transverse plane in the shape of an inverted U, the inverted U shape of each projection (78) being flattened against the second wing (76), each projection (78) extending from the first wing (68) in a longitudinal direction in a direction toward the front of the nacelle, with a portion of each projection (78) that is oriented toward the front of the nacelle being inclined relative to the transverse plane in such a way as to delimit the inclined plane (80). 5. The aircraft nacelle according to claim 1, wherein the structural reinforcement (82) is positioned at the edge (72) at the distal aft portion of the reflective layer (64), each said connecting element connecting the flange (66) to the edge (72) further extending through said structural reinforcement (82). 6. The aircraft nacelle according to claim 5, wherein the structural reinforcement (82) is flattened against the reflective layer (64) and located aft an extension of the acoustically resistive porous layer (60) and the alveolar structure (62), andwherein said structural reinforcement (82) has, along a radial plane, a Z-shaped cross-section with a first part (84) that is flattened against the reflective layer (64), a second part (86) that ensures the extension between the air intake and power plant pipes (54, 56), and a third intermediate part (88) that connects said first and second parts (84, 86) delimiting a release (90) housing a portion of the connecting elements between the flange (66) and the air intake (50),wherein each said connecting element connecting the flange (66) extends through said structural reinforcement (82) at said first part (84) that is flattened against the reflective layer (64). 7. The aircraft nacelle according to claim 6, wherein a junction zone between the first part (84) that is in contact with the reflective layer (64) and the intermediate part (88) of the structural reinforcement (82) comprises a raised surface with an inclined plane (92) that is perpendicular to the longitudinal axes (74) of the connecting elements, the connecting elements each extending through said raised surface with the inclined plane (92). 8. The aircraft nacelle according to claim 1, wherein the connecting elements between the flange (66) and the air intake (50) each comprise a rod of longitudinal axis (74) with, at a first end, a stop resting against an inclined plane (80) and, at a second end, a stop resting against an inclined plane (92).
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