Effect of Combination of Laser Shock Peening and Shot Peening on Surface Integrity and Fatigue Property of K4169 Casting Alloy

LUO Xuekun; ZHANG Wencan; WU Bo; TIAN Kai; WANG Kun; WANG Yiming; WANG Xin

doi:10.16080/j.issn1671-833x.2022.11.057

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Effect of Combination of Laser Shock Peening and Shot Peening on Surface Integrity and Fatigue Property of K4169 Casting Alloy

更新时间：2025-10-30

- Effect of Combination of Laser Shock Peening and Shot Peening on Surface Integrity and Fatigue Property of K4169 Casting Alloy
- Aeronautical Manufacturing Technology Vol. 65, Issue 11, Pages: 57-62(2022)
- 作者机构：
  
  1. 中国航发北京航空材料研究院航空材料先进腐蚀与防护航空重点实验室,北京,100095
  2. 中国航发湖南动力机械研究所,株洲,412002
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671-833x.2022.11.057
  CLC：
- Published：2022
- 稿件说明：
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罗学昆，张文灿，吴波，田凯，王琨，王一鸣，王欣. 激光冲击/ 喷丸复合强化对K4169 铸造合金的表面完整性和疲劳性能的影响[J]. 航空制造技术, 2022, 65(11): 57-62.

LUO Xuekun， ZHANG Wencan，WU Bo，TIAN Kai，WANG Kun，WANG Yiming，WANG Xin. Effect of Combination of Laser Shock Peening and Shot Peening on Surface Integrity and Fatigue Property of K4169 Casting Alloy[J]. Aeronautical Manufacturing Technology, 2022, 65(11): 57-62.
罗学昆，张文灿，吴波，田凯，王琨，王一鸣，王欣. 激光冲击/ 喷丸复合强化对K4169 铸造合金的表面完整性和疲劳性能的影响[J]. 航空制造技术, 2022, 65(11): 57-62. DOI： 10.16080/j.issn1671-833x.2022.11.057.

LUO Xuekun， ZHANG Wencan，WU Bo，TIAN Kai，WANG Kun，WANG Yiming，WANG Xin. Effect of Combination of Laser Shock Peening and Shot Peening on Surface Integrity and Fatigue Property of K4169 Casting Alloy[J]. Aeronautical Manufacturing Technology, 2022, 65(11): 57-62. DOI： 10.16080/j.issn1671-833x.2022.11.057.

摘要

K4169 合金广泛应用于制造航空发动机静子部件。针对 K4169 合金高温疲劳性能提升的需求，对旋转弯曲疲劳缺口试样进行了激光冲击 / 喷丸复合强化处理。对比分析了单一喷丸与复合强化高温疲劳性能，并采用扫描电镜、白光干涉仪、X 射线应力测量仪及显微硬度计等仪器分析了试样的疲劳断口、表面三维形貌、粗糙度、表面残余应力和显微硬度梯度，探讨了 K4169 铸造合金表面强化机制。结果表明，在 647℃、450MPa 条件下，复合强化表现出比单一喷丸更优异的疲劳寿命提升效果。复合强化后，疲劳裂纹源的数量下降，主裂纹源的萌生位置从表层转移至次表层，疲劳裂纹扩展速率下降。另外，表面微观应力集中系数 K

显著降低，从 2.39 降低至 1.46，表面残余压应力显著提升，从 –258MPa 提高至 –1140MPa，表层形成了深度约 0.20mm 的硬化层。这些表面完整性参数的变化是疲劳性能提升的重要原因。

Abstract

K4169 alloy is widely used to fabricate the stator component of aeroengine. In order to improve the high-temperature fatigue property of K4169 alloy

notch specimens for rotating bending fatigue were treated by the combination processing of laser shock peening (LSP) and shot peening (SP). The fatigue lives of single SP and combination processing (LSP+SP) were compared and analyzed. The fatigue fracture

three-dimensional surface morphology

roughness

surface residual stress and microhardness distribution were characterized by scanning electron microscopy (SEM)

white light interferometer

X–ray diffractometer and microhardness

tester. The mechanism of the combination processing on the fatigue performance was also investigated. The results indicate that the LSP+SP treatment shows better improvement of fatigue life than that of SP under the 647℃

450MPa conditions. After LSP+SP

the number of fatigue crack source decreases

and the location of the main source transferred from the surface to the subsurface. Moreover

the fatigue crack growth rate also decreases. In addition

the micro-stress concentration factor K

of the surface decreased from 2.39 to 1.46

and the surface residual compressive stress increased from –258MPa to –1140MPa. A work hardening layer with the depth of about 0.20mm was also generated. The improvement of fatigue life is considered to be mainly ascribed to the change of above surface integrity parameters.

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