BYPASS GAS TURBINE ENGINE COOLED TURBINE Russian patent published in 2018 - IPC F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: bypass gas turbine engine cooled turbine contains distributing manifold with the high-temperature air source connection unit, manifold with the low-temperature air source connection unit, communicated with the high-temperature air source inter-disk cavity, the high and low pressure turbines impellers, the high and low pressure turbines rear supports with bearings; high and low pressure turbines oil cavities communicate to each other through the system of holes made in the low pressure turbine disk trunnion; the high and low pressure turbines pressurization cavities and pre-oil cavities. Low-pressure turbine pre-oil cavity is connected to the atmosphere by means of placed in the low-pressure turbine rear support air ducts, and the high-pressure turbine pre-oil cavity is connected to the low-temperature air source. High-pressure and low-pressure turbine pre-oil cavities communicate to each other and through the movable oil seals to the same-name oil cavities. Cooled turbine is equipped with placed in the high-pressure turbine pre-oil cavity dividing partition by the channels made in the high-pressure turbine rear support, outlets and the thermal screen. Thermal screen is made of two shells having the air gap between them, is installed in thee low-pressure turbine pre-oil cavity and with the high-pressure turbine rear support forms the additional air duct. Dividing partition divides the high-pressure turbine pre-oil cavity into two chambers, one of which is connected to the high-pressure turbine pressure chamber and through channels is to the low-pressure turbine pre-oil cavity, and another chamber through an additional air duct and outlets is communicated to the low-pressure turbine pre-oil cavity.

EFFECT: invention is aimed at increase in the engine efficiency and reliability.

1 cl, 3 dwg