Patent ID: 6916151

Claim:
Ventilation device for a high pressure turbine rotor of a turbomachine, the turbine rotor being arranged on the downstream part of a combustion chamber and comprising an upstream turbine disk fitted with blades and a downstream turbine disk fitted with blades, said device comprising a cooling circuit fitted with injectors on the upstream side of the upstream disk and supplied with a cooling airflow D taken from the back of the combustion chamber, wherein said cooling circuit is arranged such that the cooling airflow D originating from the injectors passes through orifices formed in an upstream flange of the upstream disk so that the upstream flange of the upstream disk can be fixed on an upstream flange of the downstream disk, so that this cooling airflow D circulates in the axial downstream direction between an inner reaming in the upstream disk and the upstream flange of the downstream disk so that the upstream flange of the downstream disk can be fixed on a downstream flange of a high pressure compressor and so that the upstream disk can be centered, said ventilation device also comprising a single labyrinth fixed to one of the two turbine disks and being inserted between these two disks, such that the cooling airflow D is divided into a first flow F 1 circulating between a downstream face of the upstream disk and an upstream face of the single labyrinth towards the blades of the upstream disk, and into second flow F 2 circulating between an upstream face of the downstream disk and a downstream face of the single labyrinth towards the blades of the downstream disk.