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

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

Didier Marie Mortgat

Marc R Marchi

Eric Stephan Bil

Anne-Marie Arraitz

Michel Gerard Hacault

Laurent Philippe Leray

Georges Mazeaud

Carmen Miraucourt

Michel Jean-Pierre Pernot

Christian Kaincz

Jean Manuel Morcillo

Thierry Christian Sanz

Michel Jean Loubet

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

A hollow turbine blade equipped with a cooling system comprises a pair of internal partitions connected to the intrados and extrados walls of the blade and dividing the interior of the blade into at least one internal cavity extending from the root end to the tip end of the blade, a median partition connected to the two internal partitions to divide the cavity defined between the two internal partitions into two half-cavities, the median partition leaving an aperture at or near one end of the blade to establish communication between the two half-cavities, air inlet holes opening into the half-cavity on the intrados side of the median partition at or near the other end of the blade, air flow disturbing regions disposed on at least part of the internal face of the intrados wall opposite the median partition, and air outlet holes provided in the extrados wall opposite the median partition. Preferably each half-cavity is divided into two passages by half-partitions extending between the median partition and the intrados and extrados walls from root to tip of the blade.

Hollow turbine blade with internal cooling system

Growing community of inventors

Combs la Ville, France

Didier Marie Mortgat