FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft equipment. The gas turbine engine multistage turbine features two-space nozzle blades of the second stage. The blade air space, arranged the first along the gas stream, communicates, via the blade front tenon air space axial pipe, with the space feeding air onto the first turbine nozzle blade. The aforesaid pipe is arranged in the chamber between the turbine casing and the first stage split ring and mounted at the front and rear, along the gas stream, radial ribs of the turbine casing. High-pressure air forced, via the pipe with minimum losses, into the baffle cools the blade intake edge to up the turbine reliability.
EFFECT: higher reliability thanks to high-efficiency cooling.
2 dwg
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