Snecma

Stephane Henri Guy Touchaud

Denis Jean Maurice Sandelis

Jacques Marcel Arthur Bunel

Christophe Pieussergues

Mario Cesar De Sousa

Nicolas Pommier

Alain Pierre Page

Alain Rene Cayre

Luc Henri Claude Daguenet

Claude Gautier

Jacques Andre Michel Roche

Francois Rene Daniel Bainville

An annular fairing for covering the annular chamber end wall of a turbomachine combustion chamber, and in particular of an airplane turbojet. The fairing presents openings for passing fuel injectors that are supported by the chamber end wall. The fairing is subdivided into a plurality of adjacent sectors, each sector presenting inner and outer fastener edges capable of being fastened on either side of said chamber end wall. Each sector includes a lip on one of its side edges, which lip is connected to the remainder of the sector by a step, said lip being designed to over the side edge of the adjacent sector.

Fairing for a combustion chamber end wall

A fuel injector for a gas turbine engine combustion chamber is disclosed. The fuel injector includes a first fuel supply line for running at idle speed, a second, main, fuel supply line for running at speeds up to full throttle, and first and second injection orifices with which the two fuel supply lines respectively communicate. The injection orifices are arranged in a ring and the first orifices occupy a sector of the ring.

Fuel injector for a gas turbine engine combustion chamber

A diffuser for a single-head annular combustion chamber of an airplane engine, the diffuser comprising a separator formed by a thin sheet connected by structural arms to inner and outer circularly-symmetrical walls of the diffuser, the diffuser angle for each diffusion stream defined by the separator lying in the range about 12&#xb0; to about 13&#xb0;.

Diffuser for an annular combustion chamber, in particular for an airplane turbine engine

A double flow turbo-jet engine includes a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, including a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manifold and a protective tubular screen of the manifold. The gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manifold.

Turbo-jet engine with a protective screen of the fuel manifold of a burner ring, the burner ring and the protective screen

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Vincennes, France

Stephane Henri Guy Touchaud