FIELD: aircraft industry.
SUBSTANCE: invention relates to compressors of gas-turbine engines of aircraft and ground application. Invention is aimed at increasing efficiency, gas-dynamic stall margin and reliability of multistage axial-flow compressor by increasing pressure in third, forth and fifth stages starting from compressor intake, as compared with first and following stages. Proposed axial-flow multistage compressor, each stage of which includes working and guide blades, has thirteen stages, and ratio of values of ring areas of passage part at inlet Fin and at outlet Fout for first stage from side of compressor inlet Fin1/Fout1 is 1.166-1.176, for fourth stage it is Fin4/Fout4=1.30-1.33 and for last stage Fin13/Fout13=1. Guide blades of first and second stages are made turnable.
EFFECT: increased efficiency and gas dynamic stall margin of compressor.
2 dwg
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