GAS TURBINE ENGINE COOLED TURBINE Russian patent published in 2017 - IPC F01D5/08 

FIELD: engines and pumps.

SUBSTANCE: cooling turbine includes a turbine nozzle unit with nozzle vanes, the disc with rotor blades installed in the flow part of the turbine, multi-duct passing through the inner cavity of nozzle vanes. Air inlet cavity communicated to a source of cooling air. Output chamber duct is connected, on the one hand, via a further apparatus twist stator additional bladeless diffuser and additional air passages with the interior of each rotor blade located at the front edge, and on the other hand, through the apparatus spins stator bladeless diffuser and air channels the rest of the cavity of each rotor blade. Additional bladeless diffuser placed on the turbine nozzle unit and is formed as a channel, whose inlet chamber is connected with the additional twist machine stator, and the outlet chamber is connected through air channels with an additional inner cavity of each rotor blade located at the leading edge. The cavity at the exit of the additional bladeless diffuser movable seals separated from the turbine flowing part and on the cavity inlet bladeless diffuser.

EFFECT: invention allows to reduce the weight and metal turbine site design, simplify the technology of its manufacture and assembly, to increase safety margins and engine life while maintaining the efficiency of the cooling of the turbine blades working.

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