| 摘要 |
FIELD: aviation industry. SUBSTANCE: proposed axial- flow multi-stage compressor contains solid rotor drum 1 with working blades, stator housing 2 with set of rings 3 over working blades and guide vane assemblies 4. outer surface of stator housing 2 getting into channel of second circuit is made streamlined, and stator housing 2 and rings 3 are made non- split. Ring groove is made in stator housing 2 over working blades. Rings 3 and guide vane assemblies 4 are installed in stator housing 2 by means of cylindrical intermediate sleeve 5 located in said ring groove and furnished with ring bead 6 on inner surface from inlet side and ring outer flange 7 from outlet side rigidly coupled with stator housing 2 and combustion chamber housing 8. EFFECT: enhanced reliability in operation. 3 cl, 5 dwg
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