Circuit for ventilating compressor and turbine disks

A turbo-engine comprising:

• a compressor, a turbine and a transmission shaft connecting the compressor to said turbine, said compressor and said turbine each including a plurality of stages of disks subjected to a thermal gradient, said compressor including a gas vein in which gas circulates from an upstream portion to a downstream portion of the compressor, and
• ventilators for ventilating at least some of the stages of said disks so as to limit the thermal gradient of said disks wherein said ventilators include at least a first and second source for obtaining gas from the vein as well as a control device to independently communicate gas from the first source and gas from the second source to the stages of disks of the compressor and the turbine wherein the control device includes a compartment located upstream of a high pressure stage of said compressor, a gas pipe communicated with said compartment and located outside of and coaxial with the shaft and a cylindrical passage, located between the gas pipe and the shaft, to which gas from the second source is communicated via said compartment, wherein the gas pipe has a plurality of oblong openings through which the gas circulating in the cylindrical passage flows, and wherein a plurality of partitions are located around each opening for ensuring that the gas circulating in the gas pipe is contained.