Patent ID: 8919135
Filing Date: 2014-12-30
Classification: F02C,F02K,F05D,Y02T

Abstract:
1. A turbojet engine with a fan and a nacelle element forming a secondary duct downstream of the fan, the turbojet engine comprising: an intermediate casing with an outer shroud to which said nacelle element is fixed by a connecting member, wherein the connecting member comprises a cylindrical element secured to the outer shroud at an upstream end of the cylindrical element while being capable of a rotational movement with respect to an axis of the engine and connected to said nacelle element at a downstream end of the cylindrical element by a bayonet type fitting, wherein the bayonet type fitting includes a transverse groove extending over an arc of a circle and formed in one of the cylindrical element and the nacelle element, and a radial flange portion is formed in the other of the cylindrical element and the nacelle element, wherein, when the cylindrical element is in a first engaged position, the radial flange portion is engaged with the transverse groove so as to lock the connecting member with the nacelle in an axial direction, and, when the cylindrical element is in a second disengaged position, the radial flange portion is disengaged with the transverse groove such that the nacelle element is freely movable in the axial direction, and wherein the cylindrical element is movable between the first engaged position and the second disengaged position by the rotational movement with respect to the axis of the engine at a predetermined angle.