FIELD: aircraft and gas-turbine engines. SUBSTANCE: stage 1 disk is mounted directly on shaft 6. Disks 1 and 7 are provided with external fastening flanges 3, 9 placed on axially directed cylindrical shells 2, 8. Disk 7 is coupled with shaft 6 through additional bushing 12. Fastening flanges 3, 4 are located on side of moving-blade exit edges. EFFECT: improved reliability due to reduced stresses at shell-to-disk and shell-to-flange joints. 2 dwg
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