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

Jerome E Jolu

Michel A Desaulty

Pierre Charles Mouton

Jean-Claude Christian Taillant

Serge M Meunier

Xavier M Bardey

Josette Benoist

Paul Martyez

Sylvie Poutonnet

Jacques A Rauner

Gilles C Meunier

Philippe A Gouyon

Patrice J-m Rosset

Jacques Renvier

A nozzle of a turbine stator of a turbine engine, wherein at least two of the vanes are fixed to each inner platform and to opposite each outer platform, and a maintaining unit is configured to maintain each sector with respect to a case of the turbine stator and to connect sectors together and has a rotational maintaining element, a radial maintaining element and an axial maintaining element. The radial maintaining element is flexible so as to permit a radial expansion of each sector and is constituted by an elastic joint fixed to the case so as to surround the sectors.

Sectored, one-piece nozzle of a turbine engine turbine stator

The seal prevents any particles absorbed by the turbo jet engine from sliding between the upper surface of the disk (1) of the high pressure turbine and the labyrinth (2) secured to the latter. This seal includes a body (5C) placed in a cavity (6) of the labyrinth (2) and a lip (5L) resting on the upper surface (1AM) of the disk (1) so that on stopping there is a small space (6) between the labyrinth (2) and the seal (5). Application for all aircraft turbo jet engines. FIG. 2.

Metallic lip seal and turbo jet engine equipped with said seal

A gas turbine engine is disclosed having an air compressor and a generally annular combustion chamber, with a generally annular diffuser located between the compressor and the combustion chamber so as to direct air exiting from the compressor toward the combustion chamber. The diffuser has inner and outer walls and defines an exit which is located adjacent to an opening in an upstream wall portion of the combustion forming a dome cowl. The dome cowl divides the air emanating from the diffuser exit into a primary air stream passing through the opening and one or more secondary air streams which pass between the walls defining the combustion chamber and the walls of a casing enclosing the combustion chamber assembly. A guide is associated with the diffuser for directing water in the air passing through the diffuser away from the opening such that it will not pass directly into the combustion chamber. Guide vanes may be located on an external surface of the dome cowl so as to direct the water in the secondary air-flow such that it does not enter openings defined by the outer combustion chamber wall, thereby preventing the water from entering the combustion chamber.

Gas turbine engine with improved water ingestion prevention

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Pringy, France

Jerome E Jolu