FIELD: mechanical engineering; gas-turbine engines of aircraft and ground application.
SUBSTANCE: according to invention disks of rotor arranged between first and last disks are provided with balancing ring projections on radius of fillet from plate to rim, part of disks is provided with balancing projections from side of compressor inlet, and rest of disks, starting from nth disk to one but last disk, are provided with balancing projections from side of compressor outlet at n=(0.4-0.6)z; H=(1-4)R; L=(0.8-4)R; h=(0.05-0.2(R; 1=(0.05-0.2)R where n is ordinal number of disk from compressor inlet side; z is number of compressor stages; R is radius of fillet from plate to rim of disk along balancing projection; H is radial height of balancing projection from side of disk rim; L is axial length of balancing projection from side of disk plate; 1 is thickness of balancing projection from side of disk plate; h is thickness of balancing projection from side of disk rim.
EFFECT: improved reliability of multistage compressor by eliminating unbalance of disks installed between first and last stages.
5 dwg
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|---|---|---|---|
| COMPRESSOR ROTOR OF GAS TURBINE ENGINE | 2000 |
|
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| SEALING DEVICE BEHIND COMPRESSOR OF GAS- TURBINE ENGINE | 2000 |
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|
RU2362028C2 |
