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

Societe Nationale Detude Et De Construction De Mothers D'aviation 'snecma'

Michel Gerard Hacault

Marc R Marchi

Eric Stephan Bil

Anne-Marie Arraitz

Didier Marie Mortgat

Laurent Philippe Leray

Jacques R Serre

Bertrand J Heurtel

Michel Jean-Pierre Pernot

Michel Jean Loubet

Thierry Christian Sanz

Jean Manuel Morcillo

A method of reducing the gap between a liner and a turbine distributor of a turbojet engine. The method allows for the improvement of the seal on the inside of the distributor of the high pressure turbine at the lower platform. The method includes the steps of: applying a protective deposit to the lower part of the external surface of the liner, before carrying out a filling by diffusion brazing between the liner and the distributor. The protective deposit, preferably a anti-adherent ceramic, makes it possible for the braze to avoid fixing the liner onto the distributor at the lower platform level. The method also has applications to turbojet engines.

Method of reducing the gap between a liner and a turbine distributor of

This seal (6) running between gaps (6) between two stator sectors of a gas urbine engine is made up of several thin flexible slabs, capable of sliding one over the other, which gives a better seal.

Seal of stacked thin slabs that slide within reception slots

The rotor of a turbomachine has a rotor blade stage formed by sectors which are each secured to a rotor drum by radially inwardly directed, axially spaced flanges on the blade platform of the sector cooperating with radially outwardly directed, axially spaced flanges on the drum. The cooperating downstream flanges of the drum and the blade platform have at least one pair of registering holes through which a cylindrical pin extends, the pin having a radial collar interposed between the two flanges and an annular groove positioned downstream from the collar. The assembly is held in position by scalloped segments which are inserted into an annular groove in the drum on the downstream side of the downstream flange, and which are shifted circumferentially to engage edges thereof in the grooves of the pins before being locked by tongues at opposite ends of the segments.

Rotor blade fixing for turbomachine rotors

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Massy, France

Michel Gerard Hacault