Snecma

Laurent Pierre Elysee Gaston Marnas

Didier Hippolyte Hernandez

Romain Nicolas Lunel

Christophe Pieussergues

Mario Cesar De Sousa

Nicolas Pommier

Christian Rene Schnell

Pierre Pascal Sablayrolles

Daniel Francis Paul Bernier

Valentine Bader

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&#xb0; to 80&#xb0; , preferably 15&#xb0; to 75&#xb0;. 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.

Exhaust casing hub comprising stress-distributing ribs

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.

Assembling an annular combustion chamber of a turbomachine

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.

Easily demountable combustion chamber with improved aerodynamic performance

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.

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Vaux Le Penil, France

Laurent Pierre Elysee Gaston Marnas