航空发动机钛合金叶片表面强化结构完整性评价

刘川; 张璇; 尚一博; 谭羽; 周留成; 温世峰; 王晨; 潘鑫磊; 易敏

doi:10.16490/j.cnki.issn.1001-3660.2026.19.017

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表面技术 ›› 2026, Vol. 55 ›› Issue (19) : 205-219. DOI: 10.16490/j.cnki.issn.1001-3660.2026.19.017

表界面强化技术

航空发动机钛合金叶片表面强化结构完整性评价

刘川¹, 张璇², 尚一博^1,*, 谭羽^3,*, 周留成^1,4, 温世峰⁵, 王晨¹, 潘鑫磊¹, 易敏²

作者信息 +

Structural Integrity Evaluation of Surface-strengthened Titanium Alloy Blades for Aero-engines

LIU Chuan¹, ZHANG Xuan², SHANG Yibo^1,*, TAN Yu^3,*, ZHOU Liucheng^1,4, WEN Shifeng⁵, WANG Chen¹, PAN Xinlei¹, YI Min²

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文章历史 +

摘要

目的评价航空发动机钛合金叶片表面强化后结构完整性的优劣。方法对经表面强化处理的钛合金材料试样进行表面粗糙度、显微硬度与残余应力梯度分析。结合内部疲劳极限理论,构建融入表面完整性参数的强化叶片表面完整性评价方法模型,并分别通过拉伸疲劳试验与模拟叶片振动疲劳试验对模型有效性进行验证。结果相比于单纯激光强化,激光+喷丸复合强化可以在叶片表面引入硬度更高、残余应力更大、影响层更深的硬化层。疲劳试验显示,激光强化使板状试样的疲劳极限较未强化基材提高了10.9%,而激光+喷丸复合强化使板状试样的疲劳极限显著提高了13.7%。弯曲振动疲劳试验显示,激光强化叶片的疲劳极限提升7.8%,激光+喷丸复合强化叶片的疲劳极限提升13.0%。评价模型的预测结果表明,复合强化的强化效果更好。该预测结论与实验结果一致。结论表面激光强化以及激光+喷丸复合强化可以有效提升TC17钛合金材料和叶片的高周疲劳强度,后者比前者的强化效果更好。本研究提出的航空发动机钛合金叶片表面强化后的结构完整性评价方法模型,能够实现强化工艺效果的高效评估,并可推广至多种表面强化构件的表面质量快速筛选,为构件疲劳性能的预测与评估提供理论支持。

Abstract

Fan and compressor blades are the critical components of aircraft engines. Surface strengthening processes can effectively improve the blade fatigue strength, and are widely used in blade manufacturing. However, the surface strengthening process involves numerous process parameters. The surface state parameters (residual stress, roughness, hardness, etc.) of various strengthening processes are different, resulting in significant differences in the effectiveness of fatigue performance improvement. It is important to evaluate the strengthening processes and the corresponding surface states for blade manufacturing. In the present work, considering the superposition influence of residual stress and vibration stress, a surface state evaluation model for surface strengthened blade was built based on the internal fatigue limit. The model incorporated the Goodman equation to account for mean stress effects, with the measured gradients of residual stress and hardness as input parameters, thus providing a quantitative link between surface integrity and fatigue strength. Two distinct strengthening processes, namely laser shock peening (LSP) and compound LSP and shot peening (SP), were adopted to investigate the TC17 titanium alloy at both the material level and the simulated blade level. The microhardness and residual stress distributions after surface strengthening were tested. Compared with LSP alone, the compound strengthening introduced a hardened layer with higher hardness, larger compressive residual stress, and a deeper influence layer on the blade surface. Fatigue tests were carried out to compare the fatigue limits of materials strengthened by the two approaches. The fatigue test results of the plate-like tensile specimens showed that the fatigue limit of the LSP-treated titanium alloy increased by 10.9%, and that of the titanium alloy treated by compound LSP and SP exhibited a 13.7% improvement. The bending vibration fatigue test results of simulated blade samples showed that the fatigue limit of the LSP-treated material increased by 7.8%, and that of the alloy subjected to compound LSP and SP was enhanced by 13.0%. Both surface LSP and compound LSP+SP could effectively improve the high-cycle fatigue strength of TC17 titanium alloy and its blades, with the latter exhibiting a superior strengthening effect. The evolution laws of microhardness and residual stress were analyzed, and a surface state evaluation model for strengthened blades was built based on the internal fatigue limit theory and the Goodman formula. The model predictions matched the experimental results described above. The surface state evaluation method established in this paper can quickly and effectively evaluate the surface strengthening process effect, and can be used for preliminary assessment of the surface state of strengthened components, providing theoretical guidance for fatigue performance evaluation of blades treated by various methods such as SP, LSP, and compound LSP+SP. Moreover, this method enables rapid screening of optimal process parameters without relying on extensive experimental campaigns, thus saving time and cost in blade manufacturing and offering a practical tool for quality control and life prediction.

导出引用

刘川, 张璇, 尚一博, 谭羽, 周留成, 温世峰, 王晨, 潘鑫磊, 易敏. 航空发动机钛合金叶片表面强化结构完整性评价[J]. 表面技术. 2026, 55(19): 205-219

LIU Chuan, ZHANG Xuan, SHANG Yibo, TAN Yu, ZHOU Liucheng, WEN Shifeng, WANG Chen, PAN Xinlei, YI Min. Structural Integrity Evaluation of Surface-strengthened Titanium Alloy Blades for Aero-engines[J]. Surface Technology. 2026, 55(19): 205-219

中图分类号： TG146.2+3

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