涡轮转子叶片高周振动疲劳性能试验技术研究

林桂瑶; 沙云东; 丁谓; 骆丽

doi:10.7643/issn.1672-9242.2026.09.009

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装备环境工程 ›› 2026, Vol. 23 ›› Issue (9) : 82-92. DOI: 10.7643/issn.1672-9242.2026.09.009

专刊——航空装备结构动力学

涡轮转子叶片高周振动疲劳性能试验技术研究

林桂瑶, 沙云东^*, 丁谓, 骆丽

作者信息 +

Test Technology for High-cycle Vibration Fatigue Performance of Turbine Rotor Blades

LIN Guiyao, SHA Yundong^*, DING Wei, LUO Li

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文章历史 +

摘要

目的研究某型航空发动机涡轮叶片在二阶固有频率（一扭振型）下的振动疲劳失效问题,开展二阶模态下的振动特性分析与试验方法研究。方法通过扫频试验识别叶片共振频率,基于有限元法建立叶片模型进行模态分析,获取叶片多阶模态频率与振型,并与试验结果校核,确定叶片二阶固有频率。通过扭力梯度试验,确定夹持预紧力对叶片频率的影响规律。依据目标振型的振动位移方向,优化激光位移传感器的安装方位。采用叶片动应力与叶尖振动位移同步测试技术,实现振动应力标定。结果扫频试验测得叶片前两阶固有频率与有限元仿真结果吻合良好,仿真进一步提供了前六阶模态频率及振型,叶片所受振动应力（σ）与叶片自振频率（f）、叶片振幅（a）之间服从线性关系。结论该叶片理论、实测振动特性一致,得到了叶片二阶固有频率（一扭振型）下所受应力与叶片自振频率、叶片振幅之间的关系,表明此试验方法有效,可为该叶片提供疲劳数据支撑。

Abstract

The work aims to investigate the vibration fatigue failure of turbine blades of a certain aero-engine under the second-order natural frequency (first torsional mode), and conduct investigations on vibration characteristic analysis and test methodology under the second-order modal condition. Resonance frequencies of the blade were identified via frequency sweep tests. A finite element model of the blade was established for modal analysis to acquire multi-order modal frequencies and mode shapes, whose results were verified against experimental data to determine the second-order natural frequency of the blade. The influence law of clamping preload on blade frequency was obtained through torsion gradient tests. The mounting orientation of laser displacement sensors was optimized according to the vibration displacement direction of the target mode shape. Synchronous measurement of blade dynamic stress and blade tip vibration displacement was adopted to realize vibration stress calibration. The first two natural frequencies measured by frequency sweep tests were in good agreement with finite element simulation results; the simulation further yielded the first six orders of modal frequencies and corresponding mode shapes. The vibration stress (σ) of the blade presents a linear correlation with its natural frequency (f) and vibration amplitude (a). The theoretically calculated and experimentally measured vibration characteristics of the blade are consistent. The quantitative relationship between vibration stress under the second-order natural frequency (first torsional mode) and the blade's natural frequency as well as amplitude is established. The proposed test method is verified effective and can provide fundamental fatigue test data for the researched turbine blade.

导出引用

林桂瑶, 沙云东, 丁谓, 骆丽. 涡轮转子叶片高周振动疲劳性能试验技术研究[J]. 装备环境工程. 2026, 23(9): 82-92 https://doi.org/10.7643/issn.1672-9242.2026.09.009

LIN Guiyao, SHA Yundong, DING Wei, LUO Li. Test Technology for High-cycle Vibration Fatigue Performance of Turbine Rotor Blades[J]. Equipment Environmental Engineering. 2026, 23(9): 82-92 https://doi.org/10.7643/issn.1672-9242.2026.09.009

中图分类号： V216

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