TURBINE OF DOUBLE-CIRCUIT GAS TURBINE ENGINE Russian patent published in 2014 - IPC F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: turbine of a double-circuit gas turbine engine includes turbines of high and low pressures with supports of turbine rotors. Inside the rotor of the low pressure turbine there is an air cavity of high pressure connected at the inlet to the air cavity of the first nozzle block of the low pressure turbine, and at the outlet via the rear labyrinth seal - with a flow path of the low pressure turbine. The air cavity of high pressure is limited at the inner side - by the first and second labyrinth seals. Seals separate the air cavity of high pressure from the air cavity of low pressure. The air cavity of low pressure is divided into front and rear cavities. The front cavity is arranged between the high pressure turbine support and a cone flange of the low pressure turbine shaft. The rear cavity is located between the cone flange of the low pressure turbine shaft and low pressure turbine support. The first and second labyrinth seals are located relative to each other in such a manner that the ratio of the minimum diameter along sealing combs of the first labyrinth seal to the minimum diameter along sealing combs of the second labyrinth seal makes 1.2…2.0.

EFFECT: invention makes it possible to increase reliability and efficiency of a turbine.

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