Research progress on non-synchronous vibration of axial compressor rotor blade

被引：0
|
作者：
Wang S. [1 ,2 ]
Chen Y. [1 ]
Wu Y. [1 ]
Zhang S. [2 ]
Cao Z. [2 ]
机构：
[1] School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai
[2] AECC Sichuan Gas Turbine Establishment, Chengdu
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 17期
关键词：
aeroelasticity; axial compressor; flow instabilities; non-synchronous vibration of rotor blade; vibration suppression;
D O I：
10.7527/S1000-6893.2022.28044
中图分类号：
学科分类号：
摘要：
The unsteady fluid-solid-thermal-acoustic coupling problem of aeroengines involves multiple aspects such as engine performance，airworthiness，and safety，which are unavoidable in the independent development of high performance aeroengines. Non-synchronous vibration of compressor rotor blades is a new type of aeroelasticity problem，involving multidisciplinary intersection. With the increase of aerodynamic load and decrease of damping，new high performance compressors have encountered the non-synchronous vibration problem，leading to excessive vibration stress of the rotor blade，and the blade fracture failure caused by it is also common. However，its mechanism and control method have not been fully understood. The phenomena and characteristics of non-synchronous vibration of axial compressor blades are reviewed and summarized. Then，the research progress of the generation mechanism，influence factors and suppression methods of non-synchronous vibration is reviewed，aiming to expand the theoretical understanding of the non-synchronous vibration induced by unstable flow，as well as to improve the independent design and troubleshooting abilities of advanced aeroengines. Finally，the future development of this field is prospected. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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  • [1] LI Q H, AN L P, XU L, Et al., Design and test verification of high load axial-flow compressor［J］, Acta Aeronautica et Astronautica Sinica, 38, 9, (2017)
  • [2] VAHDATI M, ZHAO F Z, SURESHKUMAR P., An overview of time-domain computational methods for aeroelastic instabilities of multi-stage compressors［J］, Journal of the Global Power and Propulsion Society, 4, pp. 114-127, (2020)
  • [3] HAN L, WEI D S, WANG Y R, Et al., Analysis method of nonsynchronous vibration and influence of tip clearance flow instabilities on nonsynchronous vibration in an axial transonic compressor rotor［J］, Journal of Turbomachinery, 143, 11, (2021)
  • [4] HEGDE S, ZORI L, CAMPREGHER R, (2021)
  • [5] CHEN Y S, ZHANG H B., Review and prospect on the research of dynamics of complete aero-engine systems ［J］, Acta Aeronautica et Astronautica Sinica, 32, 8, pp. 1371-1391, (2011)
  • [6] WU Y D, LI T., Research progress on rotating instability of compressor［J］, Journal of Propulsion Technology, 42, 1, pp. 68-81, (2021)
  • [7] YANG W C, WANG Y R, HAN L, ASME Turbo Expo 2019：Turbomachinery Technical Conference and Exposition, (2019)
  • [8] DEPPE A, SAATHOFF H, STARK U., Spike-type stall inception in axial-flow compressors, Proceedings of 6th European Conference on Turbomachinery-Fluid Dynamics and Thermodynamics, (2005)
  • [9] VO H D, TAN C S, GREITZER E M., Criteria for spike initiated rotating stall［C］∥ASME Turbo Expo 2005： Power for Land, Sea, and Air, pp. 155-156, (2005)
  • [10] GARRISON B., High cycle fatigue（HCF）2000 annual report［R］, pp. 1-4, (2000)
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