GAS TURBINE ROTOR COOLING DEVICE Russian patent published in 2012 - IPC F01D5/08 F01D25/08 

FIELD: machine building.

SUBSTANCE: gas turbine rotor cooling device includes pneumatic drives, cooler, cooled rotating blades with independent cooling systems of entry edge and feather of blade, which are connected to channels in the shank, annular swirling pneumatic device, labyrinth seals and annular cavities. One of annular cavities is formed with stator and rotor part between compressor and turbine and the other one is formed with covering disc and disc of impeller. Flow-through part after compressor is connected by means of pneumatic drive to pneumatic inlet of cooler. Pneumatic outlet of cooler is connected to annular cavity above rotor between compressor and turbine, which has labyrinth seal with increased gap in the area of turbine, behind which a row of holes is located in the covering disc. Holes are connected with the inlet to extension-type tubular pneumatic drives the outlet of each of which is connected to inlet connection pipe of the channel of cooling system of entry edge of cooled turbine rotating blade. Pneumatic outlet of cooler is connected to annular swirling pneumatic device opposite the outlet of which there located in the covering disc is a row of holes with outlet to annular cavity which is connected to longitudinal channels of cooling system of turbine rotating blade feather, which are located in shanks of blades.

EFFECT: cost-effective cooling of rotor of high-temperature gas turbine.

9 cl, 5 dwg