Development turbine air-cooling system of GTE to increase its operating parameters

The results researching of structural schemes cooling for turbines of aircraft bypass gas turbine engines are presented. A new scheme of supplying cooling air to the high-pressure turbine working blades is proposed. The front cavity of the nozzle and rotor blades is cooled continuously, regardless of the engine’s operating mode. The air for cooling the working blade of the high-pressure turbine is supplied by the transit tube through the vane from the cavity, which is located in front of the place where is supply locking, which ensures constant boost of the blade front cavity. To eliminate the heating from the turbine disk and centrifugal pumping, the swirling device is installed directly under the blade lock, where the supply of cooling air to the cavity is organized. The turbine disk is cooled by the second row of swirling device with air taken from the secondary zone of the combustion chamber. The swirling devices rows are separated by brush seal and labyrinth. The higher efficiency of the brushes, the location of the swirling device cooling the disk under the labyrinth in the upper part of the disk, the decrease in the number of labyrinth teeth and, as a result, the pressure drop across the labyrinth between the disk cooling cavity and the dummy cavity eliminates heating air cooling blade because the main part of the hotter air is to be directed down the disk and, further, along the shaft of the high-pressure rotor into the dummy cavity. © 2021, Shanghai Jiao Tong University.