Abstract: A turbo-engine includes a compressor connected by a shaft to a turbine and includes a plurality of disk stages subjected to a thermal gradient, a gas vein in which the gas circulates from upstream to downstream of the compressor, and a mechanism for ventilating the disks so as to limit their thermal gradient. The ventilation mechanism includes at least, a first and a second source for obtaining the gas from the vein, as well as an operating device so as to independently bring the gas obtained from the first source and the gas obtained from the second source to the disks of the compressor and the turbine. The operating device includes a gas pipe coaxial and outside the shaft, wherein between the pipe and the shaft a cylindrical passage for the gas is provided.

Abstract: The rotor of a fan disposed in the annular noncombusted air flow duct of a urbojet propulsion engine of the bypass type is carried by a rotary body which includes the rotor assembly of a multi-stage turbine driven by noncombusted air supplied thereto by an axisymmetrical auxiliary duct which diverts noncombusted air from the primary duct of the engine just downstream of the compressor.