BYPASS GAS TURBINE ENGINE COOLED TURBINE Russian patent published in 2019 - IPC F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: bypass gas turbine engine cooled turbine contains manifold with the high-temperature air source connection unit, manifold with the low-temperature air source connection unit, inter-disk cavity, the high and low pressure turbines impellers, the high and low pressure turbines with rotor blades and discs, high and low pressure turbines disks trunnions, guide vane blades, high and low pressure turbines rear supports with bearings, high and low pressure turbines pressurization cavities and pre-oil cavities. Cavities of the same name are connected to each other. Inter-disk cavity is communicated with the high-temperature air source. High and low pressure turbines oil cavities communicate to each other through the system of holes made in the low pressure turbine disk trunnion. Low pressure turbine pre-oil cavity is communicated to the atmosphere by means of placed in the low pressure turbine rear support air ducts. High-pressure turbine pre-oil cavity is communicated to the low-temperature air source. High and low pressure turbines pre-oil cavities are communicated to the same oil cavities through the high pressure turbine movable oil seal and the low pressure turbine movable oil seal, respectively. Cooled turbine is equipped with made in the high-pressure turbine rear support additional air ducts and channels. On the one side channels are communicated to the high and low pressure turbines interconnected pressurization cavities, and on the other side, are through additional air ducts to the area where the pressure is lower than in the pressurization cavities.

EFFECT: invention is aimed at increase in the engine efficiency and reliability by the used oil properties preservation, increase in the bearing reliability and its durability, as well as the coke appearance elimination and the oil and coke ignition during operation, which increases the engine life.

5 cl, 2 dwg