FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: invention relates to compressors of gas-turbine engines of aircraft and ground application. Proposed compressor of gas-turbine engine has rotor with disks and conical flange of rear shaft. According to invention, conical flange of rear shaft is made integral with disk last in direction of air flow. Last but one disk is made T-shaped in cross section with axial ring ribs which are enclosed by rims of preceding and last disk forming bushing of compressor rotor. Preceding and last disks are made conical, with flanges pointed to rotor axis and connected with body of last but one by fastening members.
EFFECT: increased reliability and efficiency of compressor owing to reduced level of stresses in intermediate working rings and disk rim and reduced number of bolted joints.
2 dwg
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