Snecma

Snecma Moteurs

Gilles Lepretre

Didier Hippolyte Hernandez

Denis Gabriel Trahot

Martine Bes

Bertrand Monville

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

A jet engine that provides for the sealing of bleeding air to the cabin, the air passing through a cavity delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to the external casing and to an external engine casing shell, this external casing shell being fastened to the annular structure by bolting. A tube is provided between the orifice in the strut and the outlet vent, a first end of which tube is mounted in the outlet vent by a connection which is free to rotate and prevented from translational movement, and a second end of which tube is mounted in the orifice by a connection which is free to rotate and free to move translationally.

Provision of sealing in a jet engine for bleeding air to the cabin using a tube with a double ball joint

The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell () of the compressor and an annular structure () connected to the shell, and, on the other hand, by the external casing () of the diffuser grating and a strut () connected to said external casing and to an external engine casing shell (), this external casing shell () being fastened to the annular structure () by bolting together flanges, using sealing means provided between the annular structure () and the external casing () of the diffuser grating. The sealing means comprise a split annular segment () whose radially internal part () is housed in a radially sliding and sealed manner in a groove () provided at the periphery of the upstream part () of the external casing () of the grating of the diffuser, the periphery () of said segment bearing on the internal surface () of a cylindrical sleeve () which is integral with the annular structure () and surrounds said segment ().

Provision of sealing for the cabin-air bleed cavity using a segment seal

The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell fastened to the annular structure. A first seal is fitted in a first groove provided around the upstream part of the external casing of the diffuser grating, the strips of this first seal bearing on the downstream end of a first projection integral with the annular structure. A second seal is fitted in a second groove provided under said annular structure, the strips of this second seal bearing on the downstream end of a second projection integral with said annular structure and on the end of a third projection formed on the upstream part of the external casing of the diffuser.

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Epinay Sous Senart, France

Gilles Lepretre