Aircraft engine assembly
View Patent ↗An engine assembly for aircraft including a turbojet, an attachment strut, and a plurality of engine mounts interposed between the attachment strut and the turbojet. Each of the engine mounts is attached to a fan casing of the turbojet.
1. An engine assembly for aircraft comprising:
a turbojet including a fan casing;
an attachment strut, the attachment strut includes a rigid structure which includes a plurality of cradles arranged in a manner so as to define a portion of a substantially cylindrical surface with a circular cross section; and
a plurality of engine mounts interposed between the attachment strut and the turbojet,
wherein attachment of the turbojet on the strut is made with the plurality of engine mounts,
wherein each of the engine mounts is directly attached to a peripheral annular part of the fan casing of the turbojet,
wherein the plurality of cradles includes at least one annular portion shaped cradle substantially centered on a longitudinal axis of the cylindrical surface, the longitudinal axis being parallel to a longitudinal direction of the turbojet, and
wherein each of the engine mounts is attached to a forward-most annular portion shaped cradle.
2. An assembly for aircraft according to claim 1 , wherein the plurality of engine mounts includes a first engine mount and a second engine mount located in a symmetrical manner in relation to a plane defined by a longitudinal axis of the turbojet and a vertical direction of the turbojet, and a third engine mount traversed by the same plane.
3. An assembly for aircraft according to claim 2 , wherein the first and second engine mounts are traversed by a plane defined by the longitudinal axis of the turbojet and a transversal direction of the turbojet.
4. An assembly for aircraft according to claim 3 , wherein a diameter of the cylindrical surface is substantially identical to a diameter of an external cylindrical surface of the fan casing of the turbojet.
5. An assembly for aircraft according to claim 3 , wherein the plurality of cradles includes a portion of a substantially cylindrical envelope with a semi-circular cross section.
6. An assembly for aircraft according to claim 2 , wherein each of the first and second engine mounts takes loads along a longitudinal direction of the turbojet and along the vertical direction of the turbojet.
7. An assembly for aircraft according to claim 2 , wherein the third engine mount takes loads along a longitudinal direction of the turbojet and along a transversal direction of the turbojet.
8. An assembly for aircraft according to claim 2 , wherein the third engine mount is disposed on the highest part of the peripheral annular part in a vertical direction of the turbojet.
9. An assembly for aircraft according to claim 1 , wherein the rigid structure of the attachment strut comprises a center box extending parallel to the longitudinal axis of the cylindrical surface and integral with each annular portion shaped cradle.
10. An assembly for aircraft according to claim 9 , wherein the plurality of cradles further comprises two lateral cradles which take thrust loads arranged respectively on either side of the center box, each of the two lateral cradles being integral with each annular portion shaped cradle and the center box.
11. An assembly for aircraft according to claim 10 , wherein the plurality of cradles further comprises two secondary lateral cradles which take thrust loads arranged respectively on either side of the center box, each of the two secondary lateral cradles being integral with at least one annular portion shaped cradle and the center box.
12. An assembly for aircraft according to claim 10 , wherein the plurality of cradles further comprises two supporting cradles for the lateral cradles which take thrust loads, the two supporting cradles being arranged respectively on either side of the center box and each integral with one of the two lateral cradles and the center box.
13. An assembly for aircraft according to claim 10 , wherein each of the two lateral cradles which takes thrust loads is integral with one end of each annular portion shaped cradle.
14. An assembly for aircraft according to claim 1 , wherein at least one annular portion shaped cradle is a half ring.
15. An aircraft comprising at least one engine assembly according to claim 1 .
16. An assembly for an aircraft according to claim 1 wherein a forward-most annular portion shaped cradle includes a protrusion, said protrusion cooperates with a groove disposed on a rear portion of a peripheral annular part of the fan casing.