Snecma

Snecma Moteurs

Martine Bes

Didier Hippolyte Hernandez

Denis Gabriel Trahot

Sylvie Coulon

Gilles Lepretre

Delphine Roussin

An annular combustion chamber for a turbomachine comprises inner and outer annular walls united by a transverse wall, the inner and outer walls are extended at their downstream ends by inner and outer fastener flanges for fastening respectively to inner and outer shells of a turbomachine casing in order to hold the combustion chamber in position, the inner flange being provided with a plurality of holes for feeding cooling air to a high pressure turbine of the turbomachine, the air feed holes through the inner flange being distributed circumferentially over at least two rows disposed in a staggered configuration.

Annular combustion chamber for a turbomachine with an improved inner fastening flange

This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element. The means of intervention offers a means of controlling the clearance of the labyrinth seal clearance.

Labyrinth seal device for gas turbine engine

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Morsang sur Orge, France

Martine Bes