FIELD: engines and pumps.
SUBSTANCE: method of turbine cooling consists in using cold resource of air relieved downstream the last stage of the fan in the bypass turbojet engine into a channel (the second circuit), which connects the fan to the output device (an afterburner). The channel (the second circuit) is located under the turbine blades. The turbine is made in the form of radially arranged plates with a hub in their centre and hollow blades at the periphery. Inside the plates there are channels, which connect inner cavities of the blades with the inner cavity of the shaft. Via the channels the air downstream the last stage of the fan together with the fuel supplied via the nozzle (nozzles) into the inner cavity of the shaft under the pressure of at least 10 MPa, are relieved into a gas-air path of the turbine. Plates may have ribbed surface.
EFFECT: method makes it possible to increase gas temperature upstream and downstream the turbine of the bypass turbojet engine up to 2600-2700 K as a result of improved cooling.
2 cl, 2 dwg
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