Turbojet engine suspension using a double rear support
View Patent ↗Bypass turbojet engine comprising a fan casing ( 5 ) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct ( 7 ) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point ( 4 ) able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points ( 4 g, 4 d ) is positioned on the circumference of said annular rear end of the cold stream duct ( 7 ), said plurality of attachment points comprising either two points ( 4 g, 4 d ) that are diametrically opposed on said circumference or at least three points that form a polygon through which the axis of symmetry of the cold stream duct ( 7 ) passes, and in that the turbojet engine is equipped with a rear suspension hoop ( 8 ) fixed to said attachment points and able to be fixed to the structure of the aircraft.
1. A bypass turbojet engine having a longitudinal axis and comprising a fan casing at a front and an exhaust casing at a rear along the longitudinal axis, said turbojet engine further comprising a main body, and
a cold-flow channel which extends the fan casing, said cold-flow channel extending between an annular front end and an annular rear end, the cold-flow channel surrounding the main body so that a cold flow circulates between the main body and the cold flow channel and towards a downstream end of the turbojet engine, said annular rear end being connected to the exhaust casing and on which at least one attachment point is positioned which is transmitting the stresses from the exhaust casing to a structure of an aircraft,
wherein a plurality of attachment points is positioned on a circumference of said annular rear end of the cold-flow channel, said plurality of attachment points comprising either two diametrically opposed points on said circumference or at least three points forming a polygon, within which an axis of symmetry of the cold-flow channel passes, and in that the turbojet engine is equipped with a rear-suspension hoop which is attached to said attachment points and is capable of being attached to the structure of the aircraft.
2. The bypass turbojet engine according to claim 1 , wherein said hoop comprises a single attachment region which is capable of transmitting the stresses transmitted by the exhaust casing to the structure of the aircraft.
3. The bypass turbojet engine according to claim 2 , wherein the hoop is semi-circular, said single attachment region being in a middle thereof.
4. The bypass turbojet engine according to claim 1 , wherein said annular rear end of the cold-flow channel comprises a structural ring.
5. The bypass turbojet engine according to claim 4 , wherein said structural ring of the cold-flow channel is connected to the exhaust casing by means of at least two connecting rods, at ends of which reinforcements forming two points of said plurality of attachment points are positioned, the two points being diametrically opposed on a circumference of the structural ring.
6. The bypass Turbojet engine according to claim 1 , comprising an intermediate casing to which the front end of the cold-flow channel is attached.
7. The bypass turbojet engine according to claim 6 , wherein a beam which is capable of ensuring the attachment of a front suspension of the turbojet engine to the structure of the aircraft is arranged on said intermediate casing.
8. The bypass turbojet engine according to claim 2 , which is further equipped with a connection which is capable of attaching said single attachment region to a strut of the aircraft by allowing degrees of freedom in rotation of the turbojet engine along the longitudinal axis thereof.
9. The bypass turbojet engine according to claim 1 , wherein the hoop is made from a carbon-fibre sandwich composite.
10. The bypass turbojet engine according to claim 1 , wherein the annular rear end of the cold flow channel surrounds the exhaust casing.