AXIAL-FLOW COMPRESSOR ROTOR OF GAS-TURBINE ENGINE Russian patent published in 1995 - IPC

Abstract RU 2037074 C1

FIELD: manufacture of aircraft engines. SUBSTANCE: labyrinth disk secured on disk of last impeller by means of bayonet joint is additionally secured by means of bolts running through circular fin provided on labyrinth disk. Circular fin divides chamber between disks into two chambers one of which is brought in communication with rotor interior. Both chambers are brought in communication with unloading chamber by means of bypass holes provided in labyrinth disk and located over the same circumference as fastening bolts. Circular fin in zigzag in its form; that is why, it embraces bypass holes on the respective side. EFFECT: enhanced efficiency. 4 dwg

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RU 2 037 074 C1

Authors

Kuznetsov V.A.

Tunkin A.I.

Dates

1995-06-09—Published

1992-05-14—Filed