DOUBLE-FLOW GAS-TURBINE ENGINE Russian patent published in 2013 - IPC F02C7/18 F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: double-flow gas-turbine engine includes a high-pressure compressor, a combustion chamber, a high-pressure turbine with cooled moving blades, and a low-pressure turbine. Dummy cavity of the compressor is separated from a flow part of the compressor with a labyrinth seal. A moving blade cooling line is connected through a swirling unit, inner cavities of nozzle blades of the high- pressure turbine and an air-to-air heat exchanger of the high-pressure turbine to an air cavity of the combustion chamber. The low-pressure turbine is provided with a supercharging line of an inter-disc cavity and with cooling line of its nozzle blades connected to dummy cavity of the compressor through the air-to-air heat exchanger. A cavity adjacent to side surface of the high-pressure turbine disc on the swirling unit side between the shaft and the swirling unit is combined with dummy cavity of the compressor. On the cooling line of high-pressure moving blades there installed is a flow-controlling element. The cooling line of nozzle blades of the low-pressure turbine is separated from the supercharging line of the inter-disc cavity, and its connection to dummy cavity is made through a controlled valve. The air-to-air heat exchanger is made in the form of an air-to-air heat exchanger of the low-pressure turbine and an additional air-to-air heat exchanger, which are installed on the supercharging line of the inter-disc cavity and on the cooling line of nozzle blades of the low-pressure turbine respectively.

EFFECT: reduction of cooling air flow rate for cooling of moving blades of the high- pressure turbine and for cooling of nozzle blades of the low-pressure turbine in modes with partial trip of cooling without deterioration of their cooling reliability; increase in economy of an engine and its efficiency and reduction of specific fuel flow rate in more continuous operating modes.

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