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

Xavier Ja Guyonnet

Gilles Alain Charier

Jean-Louis Picard

Jean-Louis Bertrand

Turbo aero engine including a heating arrangement for the internal portions (12) of turbine disks on revving up so as to reduce the temperature gradient in the disks. Heating gas passes through pipes (11) integral with the stator and reheats the disks by passing through a gasket (13) designed with the tongues (18) and orifices (20 and 22) which allow the gas to circulate towards the zones to be heated when the revving up has firstly heated the portions of the machine close to the pipes (11) and then makes it possible to interrupt the communication when the temperatures even out and the original heat expansions become uniform and offset the orifices (20 and 23).

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St. Fargeau Ponthierry, France

Xavier Ja Guyonnet