초록 ▼

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

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.

대표청구항 ▼

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

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.