ROTOR OF GAS TURBINE ENGINE COMPRESSOR Russian patent published in 2002 - IPC

Abstract RU 2186259 C2

FIELD: mechanical engineering; gas turbine engines of aircraft and ground applications. SUBSTANCE: according to invention, in rotor of compressor of gas turbine engine, including shaft, working disks and behind-the compressor labyrinth secured on disk of last stage by bayonet joint, plates of disks of first and last stages are made with thickening in axial direction. Ratio of height to thickness of plate of behind-the-compressor labyrinth is within 10 and 50. EFFECT: improved reliability of construction owing to strengthening of disks of first and last stages and reducing stresses in plate of behind-the compressor labyrinth at axial deformations. 2 dwg

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RU 2 186 259 C2

Authors

Tunkin A.I.

Kuznetsov V.A.

Dates

2002-07-27—Published

2000-09-19—Filed