FIELD: mechanical engineering; compressors of gas-turbine engines of aircraft and ground application. SUBSTANCE: in proposed compressor of gas-turbine engine containing rotor and stator with fitted in blades and guide vanes by means of dovetail joints, according to invention, recess of width 1 and depth h is made from side of blade lock foot. Sides of recess are parallel to end faces of lock at H/h=2.5-12; L/n=2.5-7 and L/l=1.4-2, where H is radial height of blade lock; L is axial length of blade lock; n is distance from end face of lock to recess along axis of compressor. EFFECT: improved reliability and increased efficiency owing to reduction of level of stresses in zone of concentrators, weight of disks and parasitic air leakage. 3 dwg
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