초록 ▼

Turbo aero engine including a heating arrangement for the internal portions (12) of turbine disks on revving up so as to reduce the temperature gradient in the disks. Heating gas passes through pipes (11) integral with the stator and reheats the disks by passing through a gasket (13) designed with t

Turbo aero engine including a heating arrangement for the internal portions (12) of turbine disks on revving up so as to reduce the temperature gradient in the disks. Heating gas passes through pipes (11) integral with the stator and reheats the disks by passing through a gasket (13) designed with the tongues (18) and orifices (20 and 22) which allow the gas to circulate towards the zones to be heated when the revving up has firstly heated the portions of the machine close to the pipes (11) and then makes it possible to interrupt the communication when the temperatures even out and the original heat expansions become uniform and offset the orifices (20 and 23).

대표청구항 ▼

A turbo aero engine including a rotor, a stator, a combustion chamber upstream of a turbine belonging to the rotor and party constituted by a disk, wherein it includes a channel for sending and blowing hot gas from a drawing off zone of the turbo aero engine to a central zone of the disk, the sendin

A turbo aero engine including a rotor, a stator, a combustion chamber upstream of a turbine belonging to the rotor and party constituted by a disk, wherein it includes a channel for sending and blowing hot gas from a drawing off zone of the turbo aero engine to a central zone of the disk, the sending channel being composed of a portion opening into the drawing off zone and integral with the stator, and another portion integral with the rotor, the two portions being joined by an annular assembly including concentric walls for closing the portions, the walls, however, being perforated by orifices, and further including for one of the portions, circular parallel peaks established on the wall of said one portion being adjusted towards the other of the portions where the peaks approximately touch the wall, and delimiting grooves with certain of the grooves having no orifices, the orifices of the other portion being situated so that, according to the differential heat expansions in the turbo aero engine at different operating conditions, they open either in front of the grooves without orifices for certain conditions or in front of the grooves with orifices for other conditions.