Snecma

Snecma Moteurs

Pierre Pascal Sablayrolles

Christophe Pieussergues

Guillaume Sevi

Denis Gabriel Trahot

Florian Andre Francois Bessagnet

Laurent Pierre Elysee Gaston Marnas

Patrick Audin

Laurent Marnas

A device for guiding an element in an orifice in a wall of a turbomachine combustion chamber is disclosed. The device includes a coaxial ring and bushing mounted one inside the other. The bushing includes two coaxial annular parts that are fastened to each other by welding and that define a groove for guiding a rim of the ring. Welding zones between the parts of the bushing are situated away from the path of the rim of the ring when moved along a privileged transverse direction of ring movement relative to the bushing when the combustion chamber is in operation.

Device for guiding an element in an orifice in a wall of a turbomachine combustion chamber

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

A turbojet diffuser disposed between a compressor and a combustion chamber, and secured to an outer upstream annular flange of an outer casing of the combustion chamber by suspension means which comprise a first frustoconical wall extending from the outer longitudinal wall of the diffuser towards the combustion chamber, and a second frustoconical wall extending towards the compressor between the first frustoconical wall and the outer casing of the combustion chamber.

Turbojet diffuser

Growing community of inventors

Paris, France

Pierre Pascal Sablayrolles