| 摘要 |
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 |
