DUAL-CYCLE TURBINE ROTOR COOLING SYSTEM Russian patent published in 2021 - IPC F01D5/08 F01D5/18 F01D25/12 

FIELD: mechanical engineering.

SUBSTANCE: invention relates to dual-cycle turbine rotor cooling systems and can be used in the manufacture of high-temperature turbines of gas turbine engines. The dual-cycle cooling system of the turbine rotor contains working blades, each of which has corresponding channels, an annular twisting device with nozzles for intermittent supply of cooling air to the channels of the blades, external and internal annular cavities, a turbine impeller disk and a cover disk with through holes, and a labyrinth seal limiting the outer annular cavity. The entrance of the outer annular cavity is connected to the air cavity of the combustion chamber, and the exit is connected to the entrance of the annular twisting device, the nozzles of the latter are connected to the channels of the blades. The system is equipped with a pneumatic channel, the inlet of which is connected to the flow part of the compressor, and the outlet via through holes in the cover disk is connected to the entrance to the inner cavity, additional through pneumatic channels made in the turbine rotor disk, the inlet of each of which is connected to the outlet of the inner annular cavity, and the outlet is connected to the channels of the blades, and a throttle to ensure the required air flow, installed in the pneumatic channel.

EFFECT: increase in the efficiency of the system by combining critical and noncritical flow cooling schemes in the blade.

1 cl, 3 dwg