Engine assembly for aircraft
View Patent ↗An aircraft engine assembly including a turbojet engine, an engine mount, and a plurality of engine attachments. The engine attachments include first and second forward attachments fixed to a fan case and located symmetrically in relation to a plane defined by a longitudinal axis of the turbojet engine and a vertical direction thereof, both forward attachments configured to transfer loads exerted in a longitudinal direction of the turbojet engine and in the vertical direction thereof. Moreover, each of the two forward attachments includes a shear pin mounted on the case and going through two walls of a clevis fixed on the engine mount.
1. An aircraft engine assembly comprising:
a turbojet engine;
an engine mount; and
a plurality of engine attachments inserted between the engine mount and the turbojet engine, the plurality of engine attachments including a first forward engine attachment and a second forward engine attachment fixed to a fan case of the turbojet engine and located symmetrically in relation to a plane defined by a longitudinal axis of the turbojet engine and a vertical direction thereof, the first and second forward engine attachments each configured to transfer loads exerted in a longitudinal direction of the turbojet engine and in the vertical direction thereof during normal operation, and each of the first and second forward engine attachments including
a shear pin oriented in a transverse direction of the turbojet engine and mounted on the fan case, and
a clevis fixed on the engine mount and including two walls,
wherein for each of the first and second forward engine attachments, the shear pin goes through both walls of the clevis.
2. The aircraft assembly according to claim 1 , further comprising a ball joint including a casing fixed on the fan case, and a ball-joint yoke supporting the shear pin.
3. The aircraft assembly according to claim 2 , wherein the shear pin is slidingly mounted in the ball-joint yoke.
4. The aircraft assembly according to claim 1 , wherein the plurality of attachments further comprise an aft engine attachment configured to transfer loads exerted in the vertical direction of the turbojet engine.
5. The aircraft assembly according to claim 4 , wherein the aft engine attachment is configured to transfer only the loads exerted in the vertical direction of the turbojet engine, and wherein the plurality of engine attachments further comprise a third forward engine attachment fixed to the fan case so as to be passed through by the plane defined by the longitudinal axis of the turbojet engine and the vertical direction thereof, the third forward engine attachment configured to transfer only loads exerted in the transverse direction of the turbojet engine.
6. The aircraft assembly according to claim 5 , wherein the first, second, and third forward engine attachments are fixed on a peripheral annular part of the fan case.
7. The aircraft assembly according to claim 1 , wherein the first and second forward engine attachments are passed through by a plane defined by the longitudinal axis of the turbojet engine and a transverse direction thereof.
8. The aircraft assembly according to claim 4 , wherein the aft engine attachment is further configured to transfer loads exerted in a transverse direction of the turbojet engine.
9. The aircraft assembly according to claim 1 , wherein the aft engine attachment is fixed on a central case of the turbojet engine.
10. The aircraft assembly according to claim 1 , wherein the plurality of engine attachments form an isostatic assembly system.