DOUBLE-FLOW GAS TURBINE ENGINE Russian patent published in 2019 - IPC F02C7/06 F01D25/12 F02C7/12 

FIELD: engine building.

SUBSTANCE: invention relates to gas turbine engines, particularly, to support pressurization systems. Known double-flow gas turbine engine comprising a system of supercharging supports, which includes cavities of supercharging supports and pre-oil cavities of low-pressure compressor and high-pressure compressor, cavity of supercharging supports and pre-oil cavities of turbine, valve breathing-in compressor, valve breathing-in turbine supplying the air duct, which is made integral for the entire engine supercharging system, communicated with the switching valve and at least with two inputs spaced along the gas-air path, one of the inputs of which is interconnected with one of the high pressure compressor stages, and the other one is installed in gas-air channel after low pressure compressor, cavities of supercharging of low pressure compressor and high pressure compressor and turbine support supercharging cavity by air ducts are interconnected and through movable seals with engine gas-air path, air duct communicating supercharging cavity of high pressure compressor and turbine supercharging cavity is located in intershaft zone formed by high and low pressure shafts, pre-oil cavities are communicated with similar supercharging cavities and oil cavities of oil system via movable seals, pre-oil cavities of low- and high-pressure compressors are interconnected by air ducts with a valve breathing-in compressor, and turbine pre-oil cavities are interconnected by air ducts with valve breathing-in turbine, on the proposal, in interval area turbine supercharging cavity is integrated with pre-oil cavity of turbine, valve breathing-in compressor and valve breathing-in turbines by their outlets are connected with low pressure area, wherein ratio of gas passage area of valve passage passage breathing-in compressor μ_KF_K to gas flow area of flow passage of valve breathing-in turbines μ_TF_T is equal to 0.4…0.7, where μ_K is coefficient of valve consumption breathing-in compressor; F_K – geometric area of flow passage of valve breathing-in compressor; μ_T is coefficient of valve consumption breathing-in turbines; F_T – geometric area of flow passage of valve breathing-in turbines. For aviation engines, valve breathing-in compressor and valve breathing-in turbines by their outlets can be communicated as low pressure area with environment, and for ground-based engines, valve breathing-in compressor and valve breathing-in turbines by their outlets can be interconnected as low-pressure area with space of mine of ground installation (cooling tower) or with space of waste gas cleaning device or with space of device with controlled pressure level.

EFFECT: implementation of this invention increases service life and reliability of engine components by preventing oil ingress into engine gas-air path, avoiding formation of coke on hot elements of rotor structure, as well as due to stable cooling of rotor shafts with cold air; this invention ensures absence of oil vapors in aircraft air conditioning system and in pilot's life support system.

3 cl, 1 dwg