GAS-TURBINE ENGINE Russian patent published in 2010 - IPC F01D5/08 F01D11/02 

FIELD: machine building.

SUBSTANCE: gas-turbine engine consists of compressor of high pressure with after-compressor labyrinth packing at output, of combustion chamber, of double-step turbine of high pressure and also of turbine of low pressure positioned downstream. A flange of behind-compressor labyrinth packing is made with an internal circular closed cavity at output connected with a flow part of the turbine of low pressure via internal cavities of the first nozzle and the first working blades of the low pressure turbine. Via labyrinth packing the closed cavity at input is connected with the air cavity at output from the compressor and with the channel of air supply from an intermediate step of the compressor for cooling the second working blade of the high pressure turbine.

EFFECT: raised reliability and efficiency of engine by lowering temperature of gas before turbine and cooling air at input into the second working blade of high pressure turbine due to elimination of leaks of behind-compressor hot air.

3 dwg