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

Xavier, J Guyonnet

Gilles Alain Charier

Jean-Louis Picard

A turbojet engine includes a combustion chamber located upstream of a turbine, the turbine having a rotor disk integrally bladed with vanes and including a channel blowing gas from a position outside a wall of the combustion chamber to a peripheral zone of the rotor disk adjacent to the vanes, a channel divided in front of a zone adjacent to the vanes into an internal channel and an external channel surrounding the internal channel, wherein the internal channel has a greater cross-section than the external channel and wherein the external channel converges upon approaching an outlet thereof so as to accelerate the gas flowing therethrough and prevent gas which passed through the internal channel from being dispersed.

Growing community of inventors

St Fargeau Ponthierry, France

Xavier, J Guyonnet