Effect of different shot peening intensities on fatigue resistance of TC17 titanium alloy

Jiali BU; Yang LÜ; Bozhi LIU; Zhenyu HAN; Wenwei TONG; Zhikun GAO

doi:10.13224/j.cnki.jasp.20210257

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Effect of different shot peening intensities on fatigue resistance of TC17 titanium alloy

Structure,Strength and Vibration | 更新时间：2025-04-07

- Effect of different shot peening intensities on fatigue resistance of TC17 titanium alloy
- Journal of Aerospace Power Vol. 37, Issue 6, Pages: 1225-1233(2022)
- 作者机构：
  
  中国航空发动机集团有限公司沈阳发动机研究所，沈阳 110015
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210257
  CLC：
- 稿件说明：
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Jiali BU, Yang LÜ, Bozhi LIU, et al. Effect of different shot peening intensities on fatigue resistance of TC17 titanium alloy[J]. Journal of Aerospace Power, 2022, 37(6): 1225-1233.
DOI：

Jiali BU, Yang LÜ, Bozhi LIU, et al. Effect of different shot peening intensities on fatigue resistance of TC17 titanium alloy[J]. Journal of Aerospace Power, 2022, 37(6): 1225-1233. DOI： 10.13224/j.cnki.jasp.20210257.

摘要

为提升 TC17 钛合金抗疲劳性能，对其表面进行喷丸处理。通过旋转弯曲疲劳试验、断口分析、残余应力场分析、表层组织分析及喷丸前、后钛合金表面完整性分析等手段，开展不同喷丸强度对TC17钛合金抗疲劳性能影响研究。结果表明：喷丸强化后钛合金表面粗糙度增大，由0.315 μm变为0.5~1.0 μm；表层发生塑性变形，晶粒发生细化；表面引入残余压应力，残余压应力层深约为125~151 μm ，最大残余压应力位于层深30 μm附近处。0.3

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喷丸状态旋转弯曲试样疲劳寿命优于其他状态试样，在740 MPa和840 MPa应力水平下，分别比未喷丸状态试样疲劳寿命提升4.5倍与7.5倍。疲劳寿命提升归因于试样表层晶粒细化、高密度位错组织及残余压应力对疲劳裂纹萌生与扩展的抑制作用。0.35

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与0.4

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喷丸状态试样疲劳寿命下降与喷丸强度过大时试样表面粗糙度高，并有脱层及微裂纹生成有关。

Abstract

In order to improve the fatigue resistance of the TC17 titanium alloy，shot peening on the surface was carried out.The effects of different shot peening intensities on fatigue resistance of TC17 titanium alloy were studied by means of rotary bending fatigue test，fracture analysis，residual stress field analysis，microstructure observation and surface integrity analysis before and after shot peening.The results showed that surface roughness of titanium alloy was increased from 0.315 μm to 0.5-1.0 μm after shot peening.Severe plastic deformation occurred on the surface during shot peening and the surface grains were refined.Residual compressive stress was introduced into the surface，the layer depth of residual compressive stress was about 125-151 μm，and the maximum compressive stress appeared about 30 μm in depth from the surface.The fatigue life of the rotary bending sample after 0.3

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shot peening was better than that of other samples.Under the stress levels of 740 MPa and 840 MPa，the fatigue life of 0.3

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shot peened sample increased by 4.5 times and 7.5 times than that of non⁃shot peened sample，respectively.The increase of fatigue life was attributed to the inhibition of fatigue crack initiation and propagation by the refined grains，high⁃density dislocations and residual compressive stress on the surface induced by shot peening.Excessive shot peening intensity caused the high surface roughness，delamination and microcrack formation on the surface，which resulted in the decrease of fatigue life of 0.35

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and 0.4

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shot peened samples.

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