IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0571666
(2005-08-01)
|
등록번호 |
US-7624945
(2009-12-16)
|
우선권정보 |
FR-04 51784(2004-08-04) |
국제출원번호 |
PCT/FR05/050637
(2005-08-01)
|
§371/§102 date |
20070105
(20070105)
|
국제공개번호 |
WO06/021721
(2006-03-02)
|
발명자
/ 주소 |
- Diochon, Lionel
- Seguin, Guillaume
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
11 |
초록
▼
The invention relates to an engine assembly for an aircraft comprising a turbojet, a engine mount pylon, and a plurality of engine mounts inserted between the engine mount pylon and the turbojet. According to the invention, the plurality of engine mounts comprises a engine mount (6a) designed so as
The invention relates to an engine assembly for an aircraft comprising a turbojet, a engine mount pylon, and a plurality of engine mounts inserted between the engine mount pylon and the turbojet. According to the invention, the plurality of engine mounts comprises a engine mount (6a) designed so as to uniquely resist forces applied along a direction (Y) transverse to the turbojet, this engine mount (6a) comprising an intermediate fitting (46) assembled onto a first fitting (40) fixed to the pylon through two swivel axes (48) oriented parallel along a vertical direction (Z), and a pin (56) oriented along a longitudinal direction (X) and fixed to the intermediate fitting, the pin being installed on a second fitting (58) fixed to the turbojet, with clearance along the longitudinal direction (X).
대표청구항
▼
The invention claimed is: 1. An engine assembly for an aircraft comprising: a turbojet defining an X direction along a longitudinal axis of the turbojet, a Y direction along a transverse axis of the turbojet, and a Z direction along a vertical axis of the turbojet, the X, Y, and Z directions being
The invention claimed is: 1. An engine assembly for an aircraft comprising: a turbojet defining an X direction along a longitudinal axis of the turbojet, a Y direction along a transverse axis of the turbojet, and a Z direction along a vertical axis of the turbojet, the X, Y, and Z directions being orthogonal to each other; an engine mount pylon; and a plurality of engine mounts inserted between the engine mount pylon and the turbojet, wherein the plurality of engine mounts comprises a first engine mount, said first engine mount comprising: a first fitting fixed to the engine mount pylon, a second fitting fixed to the turbojet, an intermediate fitting between said first and second fittings, said intermediate fitting being V-shaped with two branches extending in an X-Y plane, wherein said intermediary fitting is assembled onto the first fitting through two swivel pins oriented parallel to each other and along the Z direction of the turbojet, each swivel pin passing through said first fitting and through one of said branches of said intermediary fitting, and each swivel pin defining a ball joint received in an opening of a corresponding branch of said intermediary fitting, a pin oriented along the X direction and fixed to the intermediate fitting, the pin being installed on the second fitting with clearance along the X direction so that said pin slides relative to said second fitting over said clearance along the X direction. 2. An assembly for an aircraft according to claim 1, wherein the first engine mount is fixed to a front part of a rigid structure of the engine mount pylon, and to a peripheral annular part of a fan case of the turbojet. 3. An assembly for an aircraft according to claim 1, wherein an X-Z plane including the longitudinal axis of the turbojet forms a plane of symmetry for the first engine mount. 4. An assembly for an aircraft according to claim 1, wherein the plurality of engine mounts further comprise an aft engine mount. 5. An aircraft comprising at least one engine assembly according to claim 1. 6. An assembly for an aircraft according to claim 1, wherein an assembly of said intermediary fitting and said pin forms a Y-shaped assembly extending in said X-Y plane, a lower branch of said Y-shaped assembly being connected to said second fitting. 7. An assembly for an aircraft according to claim 1, wherein the first engine mount forms a first front engine mount, and the plurality of engine mounts further comprise a second front engine mount, the first and second front engine mounts arranged offset from each other in the Z direction of the turbojet. 8. An assembly for an aircraft according to claim 7, wherein the second front engine mount is fixed to a center case of the turbojet. 9. An assembly for an aircraft according to claim 1, wherein the plurality of engine mounts further comprise a second engine mount and a third engine mount. 10. An assembly for an aircraft according to claim 9, wherein the first engine mount is fixed to a first front part of a rigid structure of the engine mount pylon, and to a peripheral annular part of a fan case of the turbojet, wherein the second engine mount is fixed to second front part of the rigid structure of the engine mount pylon, and to a center case of the turbojet, and wherein the third engine mount is fixed to a third part of the rigid structure of the engine mount pylon, and to an aft part of the center case of the turbojet.
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