FIELD: engines and pumps.
SUBSTANCE: gas turbine engine includes a plurality of blades assembled into an annular row of blades and partially forming a hot gas path and a cooling fluid path, a branch unit disposed on the base side of a blades row and pumping elements (130) distributed around branch unit, configured to impart movement in the narrowest gap of the cooling fluid path to the flow of the cooling fluid flowing through it. The cooling fluid path extends from the rotor cavity to the hot gas flow path. A plurality of injection members (130), a branch unit and a base of a blades row are effective to impart a spiral motion to the flow of the cooling fluid when it enters the hot gas path.
EFFECT: aerodynamic efficiency of the blade is improved, thereby increasing the efficiency of the engine, the service life of the blade is increased.
6 cl, 10 dwg
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