BYPASS GAS TURBINE ENGINE COOLED TURBINE Russian patent published in 2017 - IPC F01D5/08 F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: bypass gas turbine engine cooled turbine includes a turbine nozzle unit with nozzle blades, a disk with working blades, a multi-duct. Input chamber of the multi-duct is connected to the cooling air source, and output chamber is connected, on the one hand, via an additional stator twist apparatus, additional vaneless diffuser and additional air passages with the interior of each working blade located at the front edge. On the other hand, the output chamber of the multi-duct is connected via the stator twist apparatus, vaneless diffuser and air passages with the remaining cavity of each working blade. The cavity at the output of the additional stator twist apparatus is separated from the cavity at the input of the vaneless diffuser by movable sealing. The additional vaneless diffuser is made in the form of a channel formed by two walls, one of which is located on the turbine nozzle unit, and the other is made in the form of a cover disk connected to the disk with working blades. The additional air passages are located in the body of the cover disc and are separated by an additional movable sealing from the flowing part of the turbine at the input, and an annular collector connected to the internal cavity of each working blade, located at the front edge, is formed at the output. Air passages connected to the remaining cavity of each working blade are located between the disk with the working blades and the cover disk and are provided with ribs. The cover disk is fixed by means of a bayonet connection in the axial direction relative to the disk with the working blades, and by means of an abutment in the radial direction.

EFFECT: invention allows to reduce the weight of components and construction metal consumption, simplify the technology of mounting and assembly of the turbine construction unit, increase its resource and reliability.

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