Snecma Moteurs

Gw&eacute;na&euml;lle Calvez

Didier Hippolyte Hernandez

Alexandre Forestier

Eric Conete

Alain Tiepel

Marion Michau

Didier Georges Feder

Jos&eacute; Rodrigues

Christophe Viguier

Alain Schuler

Fr&eacute;d&eacute;ric Ravet

The invention provides an injection system for injecting an air/fuel mixture into a combustion chamber of a gas turbine engine, the injection system having a longitudinal axis and comprising fuel injection means, interposed between first and second air injection means, the fuel injection means being disposed in an annular internal cavity of a Venturi, the fuel injection means comprising at least a first fuel admission circuit provided with at least one fuel injection orifice, and a plurality of second fuel admission circuits independent from the first fuel admission circuit(s), each being provided with at least one fuel injection orifice so as to define a plurality of independent modes of injecting the air/fuel mixture depending on determined operating speeds of the engine, the fuel injection orifice of the first fuel admission circuit being formed in the upstream wall of the Venturi so as to inject fuel towards the combustion chamber in a general direction that is substantially perpendicular to a flow of air coming from the first air injection means, and the fuel injection orifices of the second fuel admission circuits being formed in the downstream wall of the Venturi so as to inject fuel towards the combustion chamber in a general direction that is substantially perpendicular to a flow of air coming from the second air injection means.

Multimode system for injecting an air/fuel mixture into a combustion chamber

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means on a ring of composite material fixed securely to said composite material combustion chamber, the flexibility of said metal fixing tongues allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal annular shells.

Fastening a CMC combustion chamber in a turbomachine using brazed tabs

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

Connection for a two-part CMC chamber

In a turbomachine comprising inner and outer annular shells of metal material containing, in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material having a plurality of air feed orifices in a primary zone and/or in a dilution zone; and an annular nozzle of metal material forming the inlet stage with fixed blades for a high pressure turbine, provision is made for the combustion chamber to be held in position between the inner and outer annular metal shells by means of a plurality of flexible metal tongues having first ends interconnected by respective metal rings fixed securely to said inner and outer annular shells by first fixing means, and second ends fixed securely to the composite material combustion chamber at it air feed orifices by second fixing means.

Fastening a CMC combustion chamber in a turbomachine using the dilution holes

An annular combustion chamber has outer and inner axially-extending side walls of composite material and an end wall of metal material held in position on the outer and inner side walls by fixing means. Provision is made for the fixing means to pass through annular cavities that are designed to receive cylindrical end portions of the outer and inner side walls, and that are created between peripheral edges of the end wall and facing portions folded downstream, a determined amount of clearance J being provided between the peripheral edges and the facing faces of the outer and inner side walls in such a manner as to allow expansion to take place freely, in operation, in a radial direction between said end wall and said side walls.

Fixing metal caps onto walls of a CMC combustion chamber in a turbomachine

In an annular combustion chamber having inner and outer axially-extending side walls of composite material and an end wall of metal material, provision is made to hold the end wall in position between the side walls of the annular combustion chamber by means of a plurality of flexible metal tongues fixed firstly to said side walls by fixing means and secondly to said end wall by brazing or welding, said end wall further comprising means for providing sealing between said end wall and said side walls.

Growing community of inventors

Melun, France

Gwénaëlle Calvez

Growing community of inventors

Melun, France

Gw&eacute;na&euml;lle Calvez

Gwénaëlle Calvez