An aircraft engine assembly with an annular load-transfer structure surrounding the central casing (16) and mechanically connected to a plurality of substantially planar reinforcing structures (64a-c) arranged externally with respect to the annular load-transfer structure, and biasing it at a plural
An aircraft engine assembly with an annular load-transfer structure surrounding the central casing (16) and mechanically connected to a plurality of substantially planar reinforcing structures (64a-c) arranged externally with respect to the annular load-transfer structure, and biasing it at a plurality of load application points (68a, 68b, 68c). At least one connecting rod is associated with a load application point, with the connecting rod positioned tangentially with respect to the casing (16), and having an inner end (62a) connected to this casing, as well as an outer end (62a) connected to the annular load-transfer structure (60) so that the outer end of the connecting rod is in an imaginary plane (66a, 66b, 66c) in which the annular load-transfer structure is located and which extends through the load application point.
대표청구항▼
1. An aircraft engine assembly comprising: a turbojet engine comprising a fan casing, an intermediate casing located radially toward the inside with respect to the fan casing and connected to the fan casing by a plurality of structural arms, and a central casing extending along the intermediate casi
1. An aircraft engine assembly comprising: a turbojet engine comprising a fan casing, an intermediate casing located radially toward the inside with respect to the fan casing and connected to the fan casing by a plurality of structural arms, and a central casing extending along the intermediate casing toward the rear;an annular load-transfer structure surrounding the central casing and mechanically connected to the central casing by an intermediary of a mounting means, the mounting means comprising a plurality of connecting rods, the annular structure being also connected to a plurality of substantially planar structures arranged externally with respect to the annular load-transfer structure, and biasing the central casing respectively at a plurality of load application points circumferentially distributed on the annular load-transfer structure;wherein at least one connecting rod of the plurality of connecting rods is associated with a load application point from the plurality of load application points,wherein the at least one connecting rod, when viewed from the front along a longitudinal axis of the turbojet engine, is positioned tangentially with respect to the central casing, and includes an inner end connected to the central casing, and an outer end connected to the annular load-transfer structure so that a plane in which the annular load-transfer structure is located extends through the load application point from the plurality of load application points, and extends through the at least one connecting rod,wherein the connecting rods all extend in a same circumferential direction from an outer end of the connecting rods, andwherein under differential thermal expansion the annular load-transfer structure turns about the central casing while staying coaxial with the central casing. 2. An aircraft assembly according to claim 1, wherein the substantially planar structures are arranged substantially radially and bias substantially radially the annular structure. 3. An aircraft assembly according to claim 1, wherein the connecting rods are arranged substantially in a same transverse plane of the turbojet engine. 4. An aircraft assembly according to claim 1, wherein the connecting rods have inner and outer ends mounted as ball joints. 5. An aircraft assembly according to claim 1, further comprising: an attachment pylon including a rigid structure and means for mounting the turbojet engine on the rigid structure, the mounting means comprising first, second, and third front engine mounts for transferring thrust forces to the fan casing, and arranged so that the third front engine mount extends through a first diametral plane of the turbojet engine, the first and second front engine mounts being arranged on both sides of the first diametral plane, and each of the first, second, and third front engine mounts being associated with a substantially planar reinforcing structure forming a shear plane,wherein the substantially planar reinforcing structure is fixedly connected in an area of the annular structure at a first anchoring point forming the load application point in the annular load-transfer structure; in an area of the fan casing at a second anchoring point; andin an area of a structural arm of the plurality of structural arms of the intermediate casing at a third anchoring point, andat a fourth anchoring point of the front engine mount on the fan casing,wherein the substantially planar reinforcing structure extends along the plane extending through the load application point. 6. An aircraft assembly according to claim 5, wherein the substantially planar reinforcing structure limits flexion of the central casing and limits elongation effects of the fan casing. 7. An aircraft comprising at least one engine assembly according to claim 1, assembled on a wing or an aft section of a fuselage of the aircraft.
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