GAS TURBINE ENGINE Russian patent published in 2019 - IPC F02C7/06 F02C7/14 

FIELD: machine building.

SUBSTANCE: invention relates to gas turbine engine building, particularly, to gas turbine engines support pressurization systems. Gas turbine engine comprising a low pressure compressor with supports, a high pressure compressor with a support, a high pressure turbine and a low pressure turbine with supports and disks forming between each other an inter-disk space of turbines, a high-pressure source, a low-pressure source, a supercharging switching valve, a centralized supercharging system of supports, each of which includes a supercharging cavity and a pre-oil cavity. Cavities of supercharging via charging valve are interconnected by supplying air ducts and with high pressure source, and with low pressure source, and air ducts with each other. Inter-disk cavity of turbines via movable seals is interconnected with gas-air channel of engine, and with pre-oil cavities of turbines. According to the invention, the gas turbine engine is equipped with a heat exchanger equipped with a cooling air path and a cooled air path, at that, cooling air duct communicated with low pressure source and gas-air outlet downstream of low pressure turbine. In its inlet the cooled air path is interconnected with the high pressure source, and by the outlet through the air ducts it is interconnected with the supercharging switching valve and/or with the inter-disk cavity of the turbines.

EFFECT: implementation of this invention due to reduction of oil temperature provides stability of its properties and further multiple use in oil supply line to bearings of support, improved operating conditions of high and low pressure turbine bearings and, as a result, increased service life and durability, as well as exclusion of coke formation on elements of turbine support structure.

3 cl, 1 dwg