FIELD: machine building.
SUBSTANCE: device for cooling the working blades of a turbine in a bypass gas turbine engine with the inner cavity of each blade being divided into the cavity at the leading edge and the remaining cavity by a partition wall, comprises the following sequentially set units: air-air heat exchanger, control valves, air duct, turbine stator spinning unit, air ducts in the runner connected to remaining cavities of the working blades, additional air duct, additional turbine stator spinning unit, additional air ducts in the runner. The air-air heat exchanger is set in the external circuit and is connected to the air cavity of the combustion chamber by its input and to the air manifold by its output. The air duct passes through the inner cavities of nozzle blades. The cavities at the blades' leading edges are connected to the air source via additional control valves. The additional air duct passes through the additional inner cavities of nozzle blades. The air manifold is used as the air source for cooling the cavities at the blades' leading edges. The inputs of the control and additional control valves are connected to the air manifold. The outputs of the additional control valves are communicated to the additional spinning unit via the additional air duct passing through the inner cavities of nozzle blades and the additional air duct of the turbine stator. At the reduction of motor speed and temperature of gas before the turbine the flow rate of the cooling air is decreased by decreasing the area of flow section of the control valves and additional control valves. As a result of the above the flow rate of cooling air passing through the air-air heat exchanger is decreased, and along with keeping the flow rate of air passing through the external circuit, the efficiency of the air-air heat exchanger is increased, hereupon the temperature of cooling air supplied for cooling of a working blade is additionally decreased.
EFFECT: invention allows for the decrease of temperature of cooling air supplied for cooling the inner cavities of turbine working blades and, in particular, the cavities located at the leading edges of the working blades.
3 cl, 2 dwg
