榫连接结构微动疲劳模拟件设计及试验

鄢林; 胡殿印; 田腾跃; 毛建兴; 王荣桥

doi:10.13224/j.cnki.jasp.20220606

榫连接结构微动疲劳模拟件设计及试验

doi: 10.13224/j.cnki.jasp.20220606

鄢林^1,,
胡殿印^{2, 3, 4},
田腾跃¹,
毛建兴^{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.
中小型航空发动机联合研究中心，北京 100191
4.
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

基金项目: 国家自然科学基金（52022007）；国家科技重大专项（2017-Ⅳ-0004-0041，J2019-Ⅳ-0009-0077，J2019-Ⅳ0016-0084)

详细信息

作者简介:
鄢林（1996-），男，博士生，主要从事微动疲劳方面的研究。E-mail：dlyanlin@buaa.edu.cn

通讯作者:
王荣桥（1968-），男，教授、博士生导师，博士，主要从事发动机结构强度可靠性、多学科优化设计等研究。E-mail：wangrq@buaa.edu

中图分类号: V231.95
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- 文章访问数: 44
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- 被引次数: 0
出版历程
- 收稿日期: 2022-08-21
- 网络出版日期: 2024-01-02

Design and experiment of simulated specimen for fretting fatigue of turbine attachment

YAN Lin^1
,,
HU Dianyin^{2, 3, 4},
TIAN Tengyue¹,
MAO Jianxing^{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.
United Research Center of Mid-Small Aero-Engine，Beijing 100191，China
4.
Beijing Key Laboratory of Aero-Engine Structure and Strength，Beihang University，Beijing 100191，China

摘要

摘要:
提出了基于损伤控制参量一致的榫连接结构微动疲劳模拟件设计方法。在几何相似的基础上，保证最大相对滑移距离与临界距离内等效应力分布的一致性，确定模拟件的二维结构尺寸；在此基础上，以临界裂纹长度内应力强度因子一致为目标，优化分析确定模拟件的三维结构尺寸；开展了某型发动机涡轮榫连接结构模拟件的微动疲劳试验，试验观测到裂纹萌生于接触面边缘，裂纹初期扩展方向垂直于接触面，断裂时的裂纹长度与仿真结果相比误差小于5%，由此验证模拟件设计方法的合理性。
- 榫连接结构 /
- 模拟件 /
- 微动疲劳 /
- 裂纹萌生 /
- 裂纹扩展
Abstract:
A method was proposed to design the simulated specimen for fretting fatigue of turbine attachment based on the consistency of damage control parameters. Afterwards, a simulated specimen for the turbine attachment of a certain aero-engine was designed. Firstly, based on geometric similarity, two-dimensional structural dimension of the simulated specimen was determined by ensuring the consistency of the maximum relative slip distance and the equivalent stress distribution within the critical distance; and then, three-dimensional structural dimension of the simulated specimen was determined by optimization analysis with the objective of consistency of the stress intensity factor within the critical crack length. Finally, fretting fatigue test of the simulated specimen was performed. It was found that the crack was initiated at the edge of the contact surface, the direction of the crack growth was perpendicular to the contact surface and the crack length at fracture was within 5% in error with the simulation, thus verifying the rationality of the design method of the simulated specimen.
- turbine attachment /
- simulated specimen /
- fretting fatigue /
- crack initiation /
- crack growth

HTML

图 1 涡轮叶盘结构有限元模型

Figure 1. Finite element model of the turbine disc and blade

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图 2 涡轮榫连接结构有限元分析结果

Figure 2. Finite element analysis results for turbine attachment

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图 3 榫连接结构模拟件的关键尺寸

Figure 3. Critical dimensions for simulated specimen

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图 4 榫槽宽度对相对滑移距离的影响规律

Figure 4. Effect of groove width on relative slip distance

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图 5 榫连接结构模拟件初始几何构型

Figure 5. Initial geometrical configuration of the simulated specimen

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图 6 损伤参数对设计变量的灵敏度分析结果

Figure 6. Results of sensitivity analysis of damage parameters to design variables

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图 7 模拟件和真实结构von Mises应力分布的对比

Figure 7. Comparison of von Mises stress distribution with the simulated specimen and turbine attachment

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图 8 模拟件裂纹扩展分析

Figure 8. Crack growth analysis of the simulated specimen

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图 9 榫连接结构微动疲劳模拟件（单位：mm）

Figure 9. Simulated specimen for fretting fatigue of turbine attachment （unit：mm）

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图 10 榫连接结构模拟件试验结果

Figure 10. Test results of the simulated specimen of turbine attachment

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表 1 涡轮盘及叶片材料力学性能

Table 1. Material properties of the turbine disc and blade

材料	温度/℃	弹性模量/GPa	切变模量/GPa	泊松比	线膨胀系数/10⁻⁶ ℃⁻¹
GH4720Li	400	201		0.36	11.94
GH4720Li	600	190		0.37	12.55
DD6	650	107.5	100	0.37	13.34
DD6	980	80.5	74.2	0.38	14.88

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表 2 榫连接结构模拟件榫头部分的试验结果

Table 2. Test results for the tenon part of the simulated specimen

编号	温度/℃	最大载荷/kN	载荷比	寿命（循环次数）/10⁴
T1	600	12.98	0.1	8.89
T2	600	12.98	0.1	8.59
T3	600	12.98	0.1	6.80
T4	600	12.98	0.1	8.17
T5	600	12.98	0.1	11.90
T6	600	12.98	0.1	7.68
T7	600	12.98	0.1	8.16
T8	600	12.98	0.1	6.38
T9	600	12.98	0.1	14.69

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表 3 榫连接结构模拟件榫槽部分的试验结果

Table 3. Test results for the groove part of the simulated specimen

编号	温度/℃	最大载荷/kN	载荷比	寿命（循环次数）/10⁴
C1	600	12.98	0.1	27.49
C2	600	12.98	0.1	25.72
C6	600	12.98	0.1	29.49

下载: 导出CSV

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