FIELD: cooling.
SUBSTANCE: cooling system of turbine elements of a three-circuit turbojet engine contains a low pressure compressor, a channel of the second circuit, the input of which is connected to the output of the low pressure compressor, and the output – to the turbine cavity. Cooling system of the turbine elements is equipped with an air-to-air heat exchanger installed in the channel of the third circuit and interconnected by the inlet and outlet with the channel of the second circuit. Behind the air-to-air heat exchanger in the direction of gas flow movement in the channel of the second circuit there is a gas flow expansion device. Device for expansion of gas flow is made in the form of blades of turbine expander.
EFFECT: invention is aimed at improving cooling efficiency of turbine engine components.
5 cl, 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| THREE-TIER WORKING BLADE OF TURBO-FAN | 2016 |
|
RU2634509C2 |
| TWO-ENGINED AIRCRAFT POWER PLANT AND POWER PLANT CONTROL METHOD | 2020 |
|
RU2746294C1 |
| TURBO ENGINE AND METHOD FOR OPERATION THEREOF | 2017 |
|
RU2674172C1 |
| TURBOJET ENGINE | 2019 |
|
RU2727532C1 |
| TWO-LOOP GAS-TURBINE FAN ENGINE | 2006 |
|
RU2320885C2 |
| METHOD OF GAS TURBINE ENGINE COOLING | 2013 |
|
RU2529989C1 |
| UNIT OF NOZZLE BLADES WITH CHANNEL FOR AIR TRANSIT FROM AIR-TO-AIR HEAT EXCHANGER | 2023 |
|
RU2819127C1 |
| COMBUSTION CHAMBER FOR TURBOJET THREE-CIRCUIT ENGINE WITH TWO HIGH PRESSURE TURBINES | 2018 |
|
RU2699161C1 |
| TURBOJET ENGINE | 2021 |
|
RU2764941C1 |
| TURBINE AIR COOLING CIRCUIT HEAT EXCHANGER | 2004 |
|
RU2332579C2 |
