| abstract |
The present invention relates to an isostatic suspension of a turbojet engine to an aircraft pylon (9), the turbojet comprising a front fan (2), an intermediate casing (3) downstream of the fan with an outer shell (34) and a hub (35) interconnected by radial arms and an exhaust casing (8) with an outer shell (83) on the same axis XX, the suspension comprising a front attachment (10) with a first transverse beam relative to the axis XX connected by at least two links (104, 105) for the front attachment to the outer shell (34) of the intermediate casing (3), a rear attachment (11) with at least two rear attachment links (114) 115) connected to the outer shell (83) of the exhaust casing (8), at least one thrust transmission connecting rod (12) connecting the hub (35) of the intermediate casing (3) to the rear attachment (11). ). The suspension is characterized in that the plane formed by said two links (104, 105) of the front attachment (10) and the push rod (12) converge at a point (C) on the axis of the engine. |