涡轮盘榫槽激光冲击强化数值模拟与试验验证

肖值兴; 毛建兴; 田腾跃; 汪文君; 胡殿印; 王荣桥

doi:10.13224/j.cnki.jasp.20220324

涡轮盘榫槽激光冲击强化数值模拟与试验验证

doi: 10.13224/j.cnki.jasp.20220324

肖值兴¹,
毛建兴^{2, 3, 4},
田腾跃¹,
汪文君^{4, 5},
胡殿印^{2, 3, 4,*, ,},
王荣桥^{1, 3, 4}

1.
北京航空航天大学能源与动力工程学院，北京 100191
2.
北京航空航天大学航空发动机研究院，北京 100191
3.
北京航空航天大学航空发动机结构强度北京市重点实验室，北京 100191
4.
中小型航空发动机联合研究中心，北京 100191
5.
中国航发湖南动力机械研究所，湖南株洲 412002

基金项目: 国家自然科学基金（51875020, 52022007）；国家科技重大专项（J2019-Ⅳ-0009-0077）

详细信息

作者简介:
肖值兴（1997-），男，硕士生，主要从事金属疲劳及表面强化研究

通讯作者:
胡殿印（1980-），女，教授、博士生导师，博士，主要从事航空发动机结构强度与可靠性研究。E-mail：hdy@buaa.edu.cn

中图分类号: V261.8
计量
- 文章访问数: 101
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- 被引次数: 0
出版历程
- 收稿日期: 2022-05-10
- 网络出版日期: 2022-09-30

Numerical simulation and experimental verification on laser shock peening for turbine mortise

XIAO Zhixing¹,
MAO Jianxing^{2, 3, 4},
TIAN Tengyue¹,
WANG Wenjun^{4, 5},
HU Dianyin^{2, 3, 4,*
, ,},
WANG Rongqiao^{1, 3, 4}

1.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
2.
Research Institute of Aero-Engine，Beihang University，Beijing 100191，China
3.
Beijing Key Laboratory of Aero-Engine Structure and Strength， Beihang University，Beijing 100191，China
4.
United Research Center of Mid-Small Aero-Engine，Beijing 100191，China
5.
Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
提出了基于离散化思想的曲面结构激光冲击强化数值模拟方法，通过空间几何关系和能量守恒原理实现受冲击区域、压力的精准定义，可实现任意曲面、任意角度的激光冲击强化数值模拟，并依据网格无关性要求确定了靶材网格尺寸。利用该方法，探究了激光冲击强化后涡轮盘榫槽结构特征部位的残余应力分布规律，与试验结果相比预测误差在20%以内。研究表明：激光冲击强化后涡轮盘榫槽部位引入一定深度范围内的残余压应力，但因曲面结构特征导致的工艺可达性影响，残余应力数值低于相同工艺水平下的平面结构，且在不同方向上存在差异性。
- 激光冲击强化 /
- 曲面结构 /
- 涡轮盘榫槽 /
- GH4720Li合金 /
- 残余应力
Abstract:
A numerical simulation method of laser shock peening of curved structure based on the idea of discretization was proposed. The precise definition of the impacted area and pressure was realized through the spatial geometric relationship and the principle of energy conservation, and the numerical simulation of laser shock peening of any curved surface and any angle can be realized. Then the target mesh size was determined according to the requirements of mesh independence. Using this method, the residual stress distribution law of the characteristic for the turbine mortise structure after laser shock peening was explored. Compared with the experimental results, the prediction error was less than 20%. The research showed that the residual compressive stress in a certain depth range was introduced into the mortise of the turbine disk after laser shock peening, but due to the process accessibility caused by the structural characteristics of the curved surface, the residual stress value was lower than the plane structure at the same process level, and there were differences in different directions.
- laser shock peening /
- curved surface structure /
- turbine mortise /
- GH4720Li superalloy /
- residual stress

HTML

图 1 榫槽激光冲击强化示意图

Figure 1. Schematic diagram of mortise laser shock peening

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图 2 激光冲击压力时间曲线

Figure 2. Laser shock pressure time curve

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图 3 激光冲击区域判断

Figure 3. Laser shock area judgment

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图 4 激光冲击强化模型

Figure 4. Laser shock peening model

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图 5 不同网格尺寸下的残余应力

Figure 5. Residual stress under different grid sizes

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图 6 曲面激光冲击强化网格收敛曲线

Figure 6. Mesh convergence curve of laser shock peening on curved surface

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图 7 半榫槽有限元模型及网格划分

Figure 7. Finite element model and mesh generation of half mortise

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图 8 榫槽激光冲击强化残余应力场

Figure 8. Mortise laser shock peening residual stress field

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图 9 榫槽激光冲击强化模拟及试验结果

Figure 9. Simulation and experimental results of mortise laser shock peening

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表 1 GH4720Li材料参数^[17]

Table 1. Material parameters of GH4720Li^[17]

E/GPa v A/MPa B/MPa C n

219 0.31 1142 1 947 0.026 0.882

下载: 导出CSV

表 2 不同结构表面残余应力

Table 2. Surface residual stress of different structures

$\varphi$ 残余应力/MPa
平面上齿面下齿面

0° −678.51 −668.89 −413.42
90° −677.93 −633.42 −338.03

下载: 导出CSV

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