FIELD: machine building.
SUBSTANCE: invention relates to high-temperature turbines of gas turbine engines, namely to methods of cooling working blades of turbines of gas turbine engines for various purposes. Task of increasing the engine efficiency is solved by the method of cooling the working blades of the turbine of the bypass gas turbine engine and the device for implementing this method. Air intended for cooling working blades 13, after compression in the compressor with rotor 2, is bled from the air path behind pre-chamber diffuser 8 through inlets 18 of air channels 19 of the heat exchange modules 14 and through outlets 20, hollow posts 9 of pre-chamber diffuser 8 are directed into swirling apparatus 11, and then through air channels 12 into inner cavities of its working blades 13. Fuel from fuel manifold 6 is supplied through inlets 15 to fuel channels 16 and through their outlets 17 to fuel nozzles 10 of flame tube of combustion chamber 5. Heat exchange is performed through walls of fuel channels 16 with removal of heat from air intended for cooling of working blades 13 of turbine. Air cooled in heat exchange modules 14 is fed from swirling apparatus 11 via channels 12 into inner cavities of working blades 13 of the turbine. Heated in heat exchange modules 14 fuel is supplied with spray to combustion chamber 5, where during combustion it transfers to working body of thermodynamic cycle of engine (gas-air mixture) along with heat released during its combustion reaction, heat removed to it from air, intended for cooling of turbine working blades 13.
EFFECT: higher engine efficiency.
2 cl, 2 dwg
