Snecma

Safran Aircraft Engines

Snecma Société Anonyme

Mario César De Sousa

Didier Hippolyte Hernandez

Denis Jean Maurice Sandelis

Jacques Marcel Arthur Bunel

Eric Conete

Christophe Pieussergues

Olivier Renon

Guillaume Sevi

Nicolas Pommier

Gregory Ghosarossian-Prillieux

Gilles Ulryck

Caroline Aumont

Patrice André Commaret

Benoit Argémiro Matthieu Debray

Dominique Michel Fouquet

Nicolas Christian Raymond Leblond

Grégory Ghosarossian-Prillieux

Brice Arnaud Demoulin

Fabrice Dominguez

Morgan Robin

Bouzid Rabia

Frédéric Noel

Florian André François Bessagnet

A method for perforating a wall, includes calculating mechanical stresses applied on the wall for a use of the wall. The method further includes perforating an orifice in a first determined zone of the wall, the perforation being made using a tool with a cross-section dependent on the mechanical stresses calculated in the first determined zone.

Method for perforating a wall of a combustion chamber

A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards. The bushing is floatingly mounted inside the chimney with its collars axially positioned between the collar of the chimney and the washer. The inner collar comes in operation to bear against the collar of the chimney. The outer collar presents an outside diameter (d1) greater than the inside diameter (d2) of the washer.

Device for mounting a spark plug in a combustion engine of a gas turbine engine

A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.

Combustion chamber for an aircraft engine, and method for attaching an injection system in a combustion chamber of an aircraft engine

A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion.

Fuel injection system for turbojet engine and method of assembling such an injection system

An annular combustion chamber for a turbomachine is disclosed. The combustion chamber includes radially internal and radially external cylindrical walls which are fixed by bolting at their upstream ends to an internal and an external annular flange of an annular chamber end wall, and an annular fairing extending in the upstream direction from the chamber end wall. The internal and external annular ends are fixed by bolting to the flanges of the chamber end wall in axial alignment with the annular ends of the walls of the chamber.

Turbomachine combustion chamber

Growing community of inventors

Cesson, France

Mario César De Sousa