航空发动机精锻叶片榫头加工夹具设计

doi:10.3969/j.issn.1004-132X.2025.04.007

摘要/Abstract

摘要： 航空发动机精锻叶片是典型的复杂曲面薄壁零件，对叶片榫头进行铣削加工时，不仅定位困难而且极易产生变形和振动。针对上述问题，提出了精锻叶片多点夹紧的夹具设计方法，并设计了一种低应力硬装夹工装夹具。利用静力学分析对装夹位置进行优化，对仿形元件材料进行选取，对装夹方式进行优化。通过模态测试试验和振动测试试验测试夹具效果。试验结果表明，采用仿形元件后，系统的低频段幅值减小了50%，高频段幅值减小了75%，一阶共振频率由210 Hz提高至402 Hz，峰值下阻尼比由17.4%提高至25.9%，振动位移信号有效值减小了35%，加工误差范围减小了59%。

关键词: 航空发动机叶片, 夹具, 有限元分析, 装夹方案, 模态测试

Abstract: Precision forged blades of aeroengine were a typical thin-walled parts with complex curved surface. When milling the blade tenons, it was difficult to locate and easy to produce deformations and vibrations. Aiming at the above problems, a design method of multi-point clamping fixture for precision forged blades was proposed, and a low stress hard clamping fixture was designed. Static analysis was used to optimize the clamping position, select the coping element materials and optimize the clamping method. The effectiveness of the fixture was tested by modal tests and vibration tests. The results show that the low-band amplitude of the system is reduced by 50%, the high-band amplitude by 75%, the first-order resonance frequency is increased from 210 Hz to 402 Hz, the damping ratio under the peak value is increased from 17.4% to 25.9%, the effective value of vibration displacement signals is reduced by 35%, and the machining error margin is reduced by 59%.

Key words: aeroengine blade, Jig and fixture, finite element analysis, clamping scheme, modal test

中图分类号:

V263

张申1, 梁嘉炜2, 吴动波3, 王辉4, 赵兵1, 许立君5, 周奋5. 航空发动机精锻叶片榫头加工夹具设计[J]. 中国机械工程, 2025, 36(04): 703-714.

ZHANG Shen1, LIANG Jiawei2, WU Dongbo3, WANG Hui4, ZHAO Bing1, XU Lijun5, ZHOU Fen5. Design of Jig and Fixture for Machining Precision Forged Blade Tenons of Aeroengine[J]. China Mechanical Engineering, 2025, 36(04): 703-714.

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链接本文: https://www.cmemo.org.cn/CN/10.3969/j.issn.1004-132X.2025.04.007

https://www.cmemo.org.cn/CN/Y2025/V36/I04/703

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