FIELD: aviation.
SUBSTANCE: group of inventions relates to the field of aircraft engine building. Rotor of the HPT of the engine comprises an impeller of a HPT including a disc and a blade rim with a system of working blades. Each HPT blade includes root and blade airfoil with convex-concave profile of walls. Impeller disc is made in form of mono-element including hub and band with rim. HPR shaft is formed by a combination of cantilever annular elements made as an integral part of the disc for connection with the HPC shaft and the HPT tip. Rotor of the HPT comprises a pressure disc forming together with the rotor disk an annular channel for supply of cooling air flow from the air swirling device to the air flow of the HPT blades. In disc rim there is diffuser channel of tract, continued in lock, leg and shank of shank of rotor blade of HPT with outlet to cooled cavity of blade. Distributing header of distribution of cooling air in cavity of blade is interconnected with channel of cyclone cooling of blade. For this purpose cyclone channel is equipped with two rows of holes – inlet row of holes in separating wall and outlet row of hole in blade back. Greater part of the blade airfoil is equipped with a vortex matrix supplemented at the outlet from the cavity of the blade airfoil by a turbulence promoter. Air twist device is equipped with system of confusor cylinder-cone nozzles.
EFFECT: invention is aimed at improving cooling efficiency of heat-stressed HPT elements, reliability and life-time of the HPT and engine in general.
9 cl, 8 dwg
