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Publishing Language: Chinese

Calculation and error analysis of kinematic accuracy reliability of VSV adjustment mechanism

Yifeng YANG1,2, Yi WANG3,4( ), Aoyu LIU1,2, Jia LI1, Liyang XIE1,2
School of Mechanical Engineering and Automation,Northeastern University,Shenyang 110819,China
Key Laboratory of Vibration and Control of Aero-Propulsion Systems of Ministry of Education,Northeastern University,Shenyang 110819,China
AECC Shenyang Engine Research Institute,Shenyang 110015,China
Research Institute of Aero-Engine,Beihang University,Beijing 102206,China
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Abstract

A kinematic model considering joint clearance is developed for the variable stator vane (VSV) adjustment mechanism of an aero-engine. A reliability model of the mechanism’s kinematic accuracy is constructed considering the failure correlation among stator vanes, as well as the stochastic nature of driving errors, dimensional tolerances, and assembly clearances. Based on the BP neural network (BPNN) surrogate model, the mechanism’s reliability is evaluated through Monte Carlo simulation. The effects of the number of stator vanes and the failure threshold on the system’s reliability are investigated. Compared with the system model of the unit failure independent assumption and the complete correlation, the mechanism system kinematic accuracy reliability model considering failure correlation is more reasonable. Lastly, a method for estimating the complex system’s reliability error caused by surrogate model approximation is proposed, and the accuracy and credibility of the VSV adjustment mechanism’s reliability assessment are confirmed.

CLC number: V233.95;TB114 Document code: A Article ID: 1001-5965(2025)06-2070-11

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Journal of Beijing University of Aeronautics and Astronautics
Pages 2070-2080

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Cite this article:
YANG Y, WANG Y, LIU A, et al. Calculation and error analysis of kinematic accuracy reliability of VSV adjustment mechanism. Journal of Beijing University of Aeronautics and Astronautics, 2025, 51(6): 2070-2080. https://doi.org/10.13700/j.bh.1001-5965.2023.0410

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Received: 24 June 2023
Published: 06 September 2023
© Journal of Beijing University of Aeronautics and Astronautics