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Publishing Language: Chinese

Residual stresses evolution mechanism of thin-walled component and deformation control method

Zhongxi ZHANG1Shuaiqin WANG1Huijuan ZHAO1( )Dinghua ZHANG2Longhao WANG1
School of Mechanical Engineering, Yangzhou University, Yangzhou 225009, China
Key Laboratory of High Performance Manufacturing for Aero Engine, Ministry of Industry and Information Technology, Northwestern Polytechnical University, Xi’an 710072, China
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Abstract

Deformation is one of the most important challenges in the machining of the thin-walled component, especially for the complicated thin-walled component with difficult-to-machining material. The internal stress and machining induced residual stress are evolved during the machining process, causing the poor machining accuracy of the final component. To solve this problem, a deformation control method based on the evolution mechanism of residual stress is proposed. Firstly, the simplified model of the component is obtained through the slice method. The equilibrium equation for clamping point is established by analyzing the loads distribution. The geometric equilibrium equation is then obtained according to the deformation superposition principle and micro deformation theory. The distribution of loads at different instants of machining process is analyzed, and the evolution mechanism of the residual stresses and the equivalent loads is revealed. Secondly, a mathematical model is established to regulate the in-process deformation of the thin-walled component. As the result, the evolution of the residual stresses and the deformation of the final component is controlled. Finally, 3 deformation validation experiments are carried out to process the same thin plates, and the deformation of the thin plates are compared. The experimental results indicate that the maximum deformation can be reduced by 82.2%.

CLC number: V263.1; TH166 Document code: A

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Acta Aeronautica et Astronautica Sinica
Article number: 629365
Cite this article:
ZHANG Z, WANG S, ZHAO H, et al. Residual stresses evolution mechanism of thin-walled component and deformation control method. Acta Aeronautica et Astronautica Sinica, 2024, 45(13): 629365. https://doi.org/10.7527/S1000-6893.2023.29365

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Received: 25 July 2023
Revised: 17 August 2023
Accepted: 07 October 2023
Published: 06 December 2023
© 2024 The Journal of Acta Aeronautica et Astronautica Sinica
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