Snecma

Jerome Etienne Robert Cameau

Fabrice Marcel Noel Garin

Alain Paul Madec

Maurice Guy Judet

Jean-Marc Michel Lesaine

Florence Valerie Bon

The invention proposes a casing () of an aircraft turbine (), intended to support a set of ring sectors () which partly delimits a channel for the passage of a gas stream through the turbine (),

Turbine casing made of two materials

The present disclosure aims at achieving a mounting of a turbomachine stator blading while avoiding a delicate machining process of the engine casing. It also aims at simplifying the mounting as well as at reducing the costs, and at decreasing the number of item references for the engine. To achieve these objects, the turbomachine uses an extension of the engine casing. A turbomachine comprises at least one stator blading for air or gas stream flowing on the internal engine casing. The stator blading comprises a rim which is assembled on a radial extension of engine casing with an axial fastener. In a preferred embodiment of the turbomachine, the engine casing presents an annular wall provided with fingers originating axially from this wall and extending according to a curvature so that they present a radial extension tip against the rim of the stator blading.

Method for mounting a stator blading of a turbomachine, an engine casing and a turbomachine comprising at least one stator blading mounted on this engine casing

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Combs la Ville, France

Jerome Etienne Robert Cameau