Abstract: An exhaust casing hub includes a hub center, and an upstream flange and a downstream flange arranged on either side of the hub center. Each flange is terminated by a rim. A plurality of cuffs are arranged on the hub center so as to form an angle from the tangent toward the radial direction of 10° to 80° , preferably 15° to 75°. At least one rib is formed at the base of each cuff below a critical stress region in the cuff. The rib is joined to the downstream flange by a downstream end and to the upstream flange by an upstream end.

Abstract: An annular combustion chamber comprising axial walls interconnected by a chamber end wall having a coefficient of thermal expansion that is different from that of the axial walls, the chamber end wall being provided with a plurality of inner and outer fastener tabs secured by fastener systems to the end portions of the axial walls. Each fastener system comprises a bolt, a nut tightened onto one of the ends of the bolt, and a slideway bushing disposed around the bolt between the nut and the end portion of the corresponding axial wall, a determined amount of radial clearance being provided between the nut and the end portion of the axial wall so as to enable the chamber end wall to expand radially freely in operation relative to the axial walls.

Abstract: The component elements of a jet engine combustion chamber are assembled together in a manner that is designed to facilitate maintenance while also improving aerodynamic performance. In an embodiment, the outer cap and the inner cap have tongues and the chamber end wail has corresponding tongues, and the tongues of the caps are assembled to the tongues of the chamber end wall.

Abstract: Injection system of a turbojet engine. It comprises a fixed part and a sliding crossmember. The sliding crossmember comprises a flange capable of sliding on the sliding surface of the fixed part. The fixed part comprises antirotation means and the sliding crossmember of the complementary antirotation means to limit the rotation of the sliding crossmember relative to the fixed part. These means consist of at least one cutout formed in the flange and of at least one lug protruding into said at least one cutout of the flange of the sliding crossmember.

Abstract: An exhaust casing hub comprises a hub center (6), and an upstream flange (8) and a downstream flange (10) arranged on either side of the hub center. Each flange is terminated by a rim (12). A plurality of cuffs (14) are arranged on the hub center (6) so as to form an angle from the tangent toward the radial direction of 10° to 80°, preferably 15° to 75°. At least one rib is formed at the base of each cuff (14) below a critical stress region (26) in the cuff. The rib is joined to the downstream flange by a downstream end and to the upstream flange by an upstream end.

Abstract: A redundant front suspension system for a turboshaft engine mounted on a pylon of an aircraft comprises a primary suspension device forming the normal front suspension of the engine, and an emergency suspension device which operates in the event of failure of the normal suspension. The primary suspension device comprises a base support which is fixed to the pylon and has a suspension shaft which co-operates with the intermediate casing of the engine. Thrust take-up rods connect the intermediate casing to the base support. The emergency suspension device comprises a first support secured to the pylon and a second support secured to the intermediate casing, each of these two supports having a vertical yoke. The vertical yokes are interconnected by a transverse pin which passes through the yokes with a clearance between the pin and one of the yokes.

Abstract: A redundant front suspension system for a turboshaft engine mounted on a on of an aircraft comprises a primary suspension device forming the normal front suspension of the engine, and an emergency suspension device which operates in the event of failure of the normal suspension. The primary suspension device comprises a base support which is fixed to the pylon and has a suspension shaft which co-operates with the intermediate casing of the engine. Thrust take-up rods connect the intermediate casing to the base support. The emergency suspension device comprises a first support secured to the pylon and a second support secured to the intermediate casing, each of these two supports having a vertical yoke associated with it. The vertical yokes are interconnected by a connecting rod in a manner which provides a clearance between the rod and at least one of the yokes.

Abstract: A redundant front suspension system for a turboshaft engine mounted on a pylon of an aircraft comprises a primary suspension device forming the normal front suspension of the engine, and an emergency suspension device. The primary suspension device comprises a base member secured to the pylon and having a suspension shaft which co-operates with the intermediate casing of the engine, and thrust take-up rods connect the intermediate casing to the base member. The emergency suspension device comprises an additional member which is interposed between the pylon and the base member of the primary device and which has a second shaft at its forward end extending parallel to the longitudinal axis X of the engine, the second shaft being received with clearance in a bore provided in the intermediate casing and being equipped with means for enabling take-up of forces along the X, Y and Z axes in the event of failure of an element of the primary suspension device.