FIELD: mechanical engineering; gas-turbine engines of aircraft and ground application.
SUBSTANCE: according to invention, in multistage compressor of gas-turbine engine containing rotor in which disks and working blades are provided with longitudinal "dovetail" lock joints, working blades are arranged in groups with one type-size of lock joint. First and last groups from side of compressor inlet include, each, four stages, and ratio of number z of stages of compressor to number k of groups of working blades in compressor is 3-4.
EFFECT: improved reliability of compressor at reduction of its cost owing to reduction of number of type-sizes of lock joints and cost of their designing and finishing.
3 dwg
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