Snecma

Safran Aircraft Engines

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Snecma Moteurs

Snecma Propulsion Solide

Christophe Pieussergues

Denis Jean Maurice Sandelis

Romain Nicolas Lunel

Didier Hippolyte Hernandez

Denis J Sandelis

Guillaume Sevi

Alain Rene Cayre

Pierre Pascal Sablayrolles

Nicolas Christian Raymond Leblond

Denis Jean Sandelis

Jacques Marcel Arthur Bunel

Eric Conete

Michel A Desaulty

Mario Cesar De Sousa

Georges Mazeaud

Dominique Raulin

Georges Habarou

Haris Musaefendic

Laurent Bernard Cameriano

Denis Gabriel Trahot

Jackie Raymond Julien Prouteau

Jean-Paul D Alary

Pierre M Schroer

Luc Henri Claude Daguenet

Benjamin Frantz Karl Villenave

Francois Leglaye

Mario César De Sousa

Julien Marc Matthieu Leparoux

Claude Gautier

Laurent Pierre Elysee Gaston Marnas

Stephane Henri Guy Touchaud

Patrice André Commaret

Pierre André Gabriel Malbois

Dominique Maurice Jacques Lains

Dan Ranjiv Joory

Jackie Prouteau

Laurent Pierre Marnas

Guillaume Aurelien Godel

Olivier Baptiste Bidart

Laurent Marnas

François Leglaye

Clément Jean Henri Bechet

Emmanuel Jean André Greslin

Damien Bonnefoi

Jean-Luc Voisembert

Pierre-Francois Pireyre

Guillaume Aurélien Godel

David Pinchon

Francis Mirambeau

François Pierre Ribassin

Luc Namer

Francois Pierre Georges Maurice Ribassin

Françoise DesChamps

Alain Meriguet

Denis Sandelis

Olivier Bidart

Pierre Sablayrolles

François Pierre Georges Maurice Ribassin

Pierre-François Pireyre

A flame-holder device for a turbojet afterburner comprises an annular row of flame-holder arms, each having an inner branch having a free end and another end, and two outer branches which extend from the other end and diverge from one another in a direction extending from the free end to the other end, such that the inner branch transitions radially outward into the two outer branches which diverge radially outward from one another in two opposing circumferential directions, thereby forming mutually approaching areas between consecutive flame-holder arms for enabling the flame to spread from arm to arm.

Flame-holder device for a turbojet afterburner, comprising three-branched arms

A combustion chamber for a turbomachine including an annular casing delimiting an inner volume of the combustion chamber and provided with a chimney extending to the outside of the inner volume and delimiting a passage for a penetrating part, and a bushing mounted floating on the chimney, further includes: a main air collection chamber open to the upstream arranged facing the downstream portion of the chimney; and a through-opening of the annular casing, connecting the inner volume to the main air collection chamber. The air collected by the main air collection chamber is injected into the inner volume via the through-opening and can cool an annular casing zone downstream of the chimney.

Combustion chamber comprising means for cooling an annular casing zone downstream of a chimney

The invention concerns a turbo engine comprising a combustion chamber () arranged inside the outer housing () and comprising an internal revolution wall () and an external revolution wall (). First stop parts () and second stop parts () fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs ().

Combustion module for a gas turbo engine with chamber bottom stop

The provision of air passage holes through a wall of a gas turbomachine combustion chamber. Multi-perforations are virtually positioned and distributed, even in a first safety zone without air passage openings. Multi-perforations with a virtual inlet or outlet in this first security zone are virtually removed. According to certain criteria, at least some of said removed multi-perforations are then virtually reintegrated, and, from then on a perimeter passing through the virtual inlets and outlets of all the multi-perforations present is defined, in the direction of a primary or dilution hole to be installed, a modified safety zone is defined, then, respecting around said hole and with the freedom to reposition it within this limit, the shape of this hole is redefined.

Configuring and positioning air passage holes in a combustion chamber wall

An air intake swirler for a turbomachine injection system includes an upstream wall and a downstream wall, both of revolution about an axis of the air intake swirler, and fins distributed about the axis and connecting the upstream wall to the downstream wall so as to delimit, between the upstream wall and the downstream wall, air inlet channels each having an inlet and an outlet. The swirler includes two aerodynamic deflectors that respectively extend the downstream walls radially outward and that have a concavity oriented upstream. The aerodynamic deflectors extend radially facing the respective inlets of the air inlet channels and thus make it possible to limit the loss of pressure of the air supplied to the air inlet channels.

Air intake swirler for a turbomachine injection system comprising an aerodynamic deflector at its inlet

A device for cooling of an annular wall of a turbomachine combustion chamber provided with micro-perforations, and in particular the cooling of a region of the wall facing a wake induced by an ignition plug, the device includes, a deflector designed to divert air immersing the ignition plug towards a median plane of the wake and towards the annular wall of the combustion chamber, so as to increase the air pressure within the wake in proximity to the annular wall.

Turbomachine combustion chamber provided with air deflection means for reducing the wake created by an ignition plug

An annular combustion chamber including inner and outer walls forming surfaces of revolution that are connected together upstream by an annular chamber end wall having injection systems passing therethrough. Each injection system includes at least one swirler for producing a rotating stream of air downstream from a fuel injector, and a frustoconical bowl downstream from the swirler and formed with an annular row of air injection orifices, the outer wall having an annular row of primary dilution orifices. The orifices of the bowls are distributed and dimensioned such that sheets of air/fuel mixture present a local enlargement circumferentially intersecting an adjacent sheet of fuel upstream from the primary dilution orifices.

Annular combustion chamber for a turbine engine

A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.

Guiding a sparkplug in a turbine engine combustion chamber

A turbomachine combustion chamber including at least one ignition plug carried by an outer casing and extending within guide means carried by a wall of the chamber, the wall forming a body of revolution. The guide means includes a tubular guide having the plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber, the guide extending at least in part in an air flow stream outside the chamber. The guide means includes a deflector surrounding the portion of the guide that is situated in the air flow stream so as to reduce the aerodynamic pressure on the guide and reduce the contact pressure of the guide on the plug.

Guide for an ignition plug in a turbomachine combustion chamber

A procedure for igniting a combustion chamber of a turbine engine, the chamber being fed with fuel by injectors and including an igniter mechanism igniting the fuel injected into the chamber. The procedure includes an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter mechanism, and in event of non-ignition of the chamber at an end of the initial stage, a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%.

Procedure for igniting a turbine engine combustion chamber

A turbomachine combustion chamber in which a chamber end wall presents an opening for receiving a pre-vaporization bowl, and including a device for injecting air and fuel mounted on the axis thereof, the bowl being floatingly mounted relative to the chamber end wall to move in a predetermined radial direction and flaring downstream so as to form a collar, a deflector forming a thermal shield being made integrally with the bowl beside the chamber end wall so that the floating movement of the bowl-and-deflector assembly takes place in a sliding plane situated between the deflector and the chamber end wall.

Turbomachine combustion chamber

A turbomachine including an annular combustion chamber, a sectorized turbine nozzle arranged at an outlet from the chamber, and a sealing mechanism interposed axially between the chamber and the nozzle, the sealing mechanism including an annular gasket that is axially resilient. The gasket includes a first axial bearing mechanism for bearing against a downstream end of the chamber and a downstream annular lip that is sectorized, each sector of the downstream lip being in alignment with a sector of the nozzle and including a second axial bearing mechanism for bearing against an upstream end of the nozzle sector.

Sealing between a combustion chamber and a turbine nozzle in a turbomachine

An aircraft turbomachine with a housing, and first and second fuel injection systems, where each system includes an injector fitted with an attachment plate traversed by three mounting holes positioned according to a first configuration for the first system and according to a second configuration distinct from the first for the second system. Each system also includes a reception device installed on the housing, a sealing joint interposed between the plate and the reception device, and securing screws which attach the plate on to its reception device. Sealing joints are identical for the first and second fuel injection systems.

Turbomachine with separate fuel injection systems, using identical sealing joints

A fuel injection system for an annular combustion chamber of a turbomachine including a support device for supporting and centering a fuel injector head; and a bowl arranged downstream from the support device and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface is disclosed. The upstream radial surface includes a device which disturbs the flow of cooling air and increases the heat exchange area between the air and the collar.

Fuel injection system for a combustion chamber of a turbomachine

A system for injecting a mixture of air and fuel into a turbomachine combustion chamber is disclosed. The system includes a fuel injector and a Venturi with an interior surface delimiting a premixing chamber. The Venturi includes an internal annular airflow cavity which is connected by air outlet ducts to the premixing chamber. The air outlet ducts open onto the interior surface of the Venturi so as to prevent to deposition of soot and the formation of coke on this surface.

System for injecting a mixture of air and fuel into a turbomachine combustion chamber

Growing community of inventors

Nangis, France

Christophe Pieussergues