COOLED TURBINE OF BYPASS GAS TURBINE ENGINE Russian patent published in 2017 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: cooled turbine of the bypass turbine engine comprises a turbine nozzle assembly with nozzle blades, a disc with working blades installed in the turbine flow part, a multi-channel air duct. The multi-channel air duct passes through inner cavities of the nozzle blades, its inlet cavity communicates with air cooling source. The outlet cavity of the multi-channel air duct is connected, on the one hand, through an additional stator twisting device, additional air-free diffuser and additional air channels with inner cavity of each working blade located at the edge of the input, and on the other side, through a stator twisting device, blade-free diffuser and air channels with remaining cavity of each working blade. The blade-free diffuser and additional blade-free diffuser are arranged on turbine nozzle device and are in the form of channels, which inlet cavities are connected to the stator twisting device and additional stator twisting device, respectively. The outlet cavity of additional blade-free diffuser channel is connected through additional air channels to inner cavity of each working blade located at input edge. The outlet cavity of the blade-free diffuser channel is connected through air channels with the remaining cavity of each working blade. The outlet cavities of the channels form an annular gap therebetween that is equipped with a movable seal and separated by additional movable seals from the turbine flow part and from the cavity formed by stator twisting device and the disc with working blades.

EFFECT: invention makes it possible to reduce costs for manufacture and assembly of turbine assembly components by reducing the weight of parts and metal capacity of the structure.

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