Safran Helicopter Engines

Stéphane Raphaël Yves Richard

Bertrand Guillaume Robin Pellaton

Olivier Pierre Descubes

Jean-Luc Breining

Mathieu Cladiere

Christophe Nicolas Henri Viguier

Jerome Dinquel

Gabriel Gorka Exilard

Nicolas Christophe Perra

Mathieu Pierre Cladiere

An assembly for a turbomachine includes at least one turbine having a turbine disc with an internal bore and an annular cavity which is arranged upstream of the disc. The assembly further includes a fire safety system with a cooling device that supplies the cavity with cooling air via injection means. The fire safety system includes means that divide the annular cavity into first and second cavities. A cooling air speed is maintained at the outlet of the injection means and the cooling air in the first cavity is guided to the internal bore of the turbine disc. A diffuser co-operates with the injection means and an annular cover co-operates with the diffuser and covers first attachment members arranged in the cavity. A radially outer surface of the cover at least partially guides the cooling air at the outlet of the diffuser.

Fire safety system for a turbomachine comprising means for maintaining a cooling air speed and corresponding turbomachine

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MOISSY-CRAMAYEL, France

Stéphane Raphaël Yves Richard