BYPASS GAS TURBINE ENGINE Russian patent published in 2021 - IPC F02K3/115 F02C7/14 

FIELD: engines.

SUBSTANCE: invention relates to cooling systems of bypass gas turbine engines. The known bypass gas turbine engine containing a high-pressure compressor, wherein the dummy cavity is separated from the flow channel of the compressor by a labyrinth seal, a combustion chamber, a high-pressure turbine with coolable rotor blades, the cooling line whereof is connected via a swirling apparatus, the internal cavities of the nozzle blades of the high-pressure turbine and an air-to-air heat exchanger with the air cavity of the combustion chamber, a low-pressure turbine with coolable blades of a nozzle apparatus and an inter-disk cavity, the supply air ducts whereof are connected via the air-to-air heat exchanger of the low-pressure turbine with the dummy cavity of the compressor, according to the claim, is equipped with a flow controlling element installed on the cooling line of the rotor blades of the high-pressure turbine and with an additional flow controlling element installed on the supply air ducts of the blades of the low-pressure turbine nozzle apparatus and the inter-disk cavity and providing the area ratio in the closed position equal to:

wherein F_closed is the total flow area of the additional flow controlling element in the closed position, and F_open is the total flow area of the additional flow controlling element in the open position.

EFFECT: application of the invention makes it possible, by simultaneously or independently reducing the consumption of cooling air supplied for cooling the low-pressure nozzle blades and pressurisation of the inter-disk cavity, as well as for cooling the rotor blades of the high-pressure turbine in modes with partial or total cooling deactivation, to reduce the specific fuel consumption in said modes, increasing the cost efficiency of the entire engine in general.

1 cl, 2 dwg