基于三参数临界距离模型的轮盘偏心孔低周疲劳寿命预测

陈欢欢; 胡殿印; 王贵灿; 黄宏扬; 郭民昕; 钱正明; 毛建兴; 王荣桥

doi:10.13224/j.cnki.jasp.20250366

基于三参数临界距离模型的轮盘偏心孔低周疲劳寿命预测

doi: 10.13224/j.cnki.jasp.20250366

陈欢欢^{1, 2,},
胡殿印^{1, 3, 4},
王贵灿¹,
黄宏扬^{1, 2},
郭民昕²,
钱正明²,
毛建兴^{1, 3, 4,*, ,},
王荣桥^{3, 4, 5}

1.
北京航空航天大学航空发动机研究院，北京 100191
2.
中国航发湖南动力机械研究所，湖南株洲 412002
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.
北京航空航天大学能源与动力工程学院，北京 100191

基金项目: 国家重点研发计划（2024YFB4609000）；国家科技重大专项（J2019-Ⅳ-0009-0077，Y2022-Ⅶ-0007-0049，J2022-Ⅳ-0011-0025，Y2022-Ⅳ-0001-0018）；北京市自然科学基金（3252007）

详细信息

作者简介:
陈欢欢（1988-），男，高级工程师，硕士，主要从事结构强度与可靠性方向研究。E-mail：chenhuan2023@buaa.edu.cn

通讯作者:
毛建兴（1989-），男，副研究员，博士，主要从事结构强度与可靠性方向研究。E-mail：maojx@buaa.edu.cn

中图分类号: V232.3
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出版历程
- 收稿日期: 2025-08-03
- 网络出版日期: 2026-09-01

Prediction of low-cycle fatigue life of eccentric holes in disk based on a three-parameter critical distance model

Chen Huanhuan^{1, 2
,},
Hu Dianyin^{1, 3, 4},
Wang Guican¹,
Huang Hongyang^{1, 2},
Guo Minxin²,
Qian Zhengming²,
Mao Jianxing^{1, 3, 4,*
, ,},
Wang Rongqiao^{3, 4, 5}

1.
Research Institute of Aero-Engine，Beihang University，Beijing 100191，China
2.
Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，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.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China

摘要

摘要:
为提升航空发动机轮盘关键部位疲劳寿命评估精度，支撑长寿命高可靠性轮盘设计，聚焦轮盘偏心孔低周疲劳寿命精准预测，提出三参数临界距离模型，解决传统临界距离模型因应力梯度与寿命复杂关联导致拟合精度受限问题。核心创新在于：引入归一化应力梯度与高应力区尺寸，建立三参数临界距离表达式，揭示应力梯度与临界距离的强相关性，通过缺口件试验验证高/低应力梯度下临界距离随寿命的差异化演变规律，构建完整寿命评估流程，结合弹塑性有限元仿真与Smith-Watson-Topper疲劳寿命模型，实现临界距离的直接解算与寿命精准预测。轮盘偏心孔模拟件低周疲劳试验验证表明，所提出的三参数临界距离模型将寿命预测误差从传统方法的3倍分散带外精准至1.5倍分散带内，显著提升轮盘应力集中部位的寿命预测精度，为航空发动机轮盘强度设计、安全裕度优化及延寿决策提供直接支撑，具有重要工程实用价值。
- 应力梯度 /
- 临界距离 /
- 低周疲劳 /
- 损伤参量 /
- 寿命预测
Abstract:
To enhance the fatigue life assessment accuracy for critical regions of aero-engine turbine disks and support high-reliability, long-life disk design, the challenge of accurate low-cycle fatigue (LCF) life prediction for disk eccentric bore structures was addressed. An innovative three-parameter critical distance (TCD) model was proposed to overcome the limitations of traditional TCD models, which suffered from restricted fitting accuracy due to the complex relationship between stress gradients and fatigue life. The core innovations lied in: introducing normalized maximum stress gradient and high-stress zone dimensions to characterize stress gradient effects, establishing the three-parameter critical distance expression; revealing a strong correlation between stress gradients and critical distance, and validating through notch specimen LCF tests demonstrating differential evolution of critical distance with life under contrasting high and low stress gradients; establishing a comprehensive life assessment framework integrating elastoplastic finite element simulation with the Smith-Watson-Topper fatigue life model, enabling direct critical distance calculation and accurate life prediction. Validation via LCF testing on simulated disk eccentric bore specimens demonstrated that the proposed model significantly reduced life prediction error, bringing results from outside the triple error dispersion band of traditional methods to within a 1.5-fold dispersion band. A substantial improvement in prediction accuracy for life-critical regions with stress concentrations was achieved, directly supporting the aero-engine turbine disk strength design, safety margin optimization, and life extension decision-making, and underscoring its significant practical engineering value.
- stress gradient /
- critical distance /
- low cycle fatigue /
- damage parameter /
- life prediction

HTML

图 1 偏心孔模拟件与真实轮盘损伤参量对比

Figure 1. Comparison of damage parameters between eccentric hole simulating specimen and real disk

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图 2 偏心孔模拟件图纸（单位：mm）

Figure 2. Drawing of eccentric hole simulating specimen （unit：mm）

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图 3 缺口件图纸（单位：mm）

Figure 3. Drawing of notched specimen （unit：mm）

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图 4 偏心孔模拟件低周疲劳试验结果

Figure 4. Low cycle fatigue test results of eccentric hole simulating specimens

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图 5 偏心孔模拟件断口观测结果

Figure 5. Fracture observation result of eccentric hole simulating specimens

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图 6 缺口件低周疲劳试验结果

Figure 6. Low cycle fatigue test results of notched specimens

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图 7 SWT模型拟合结果

Figure 7. Fitting results of SWT model

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图 8 缺口件临界距离取值

Figure 8. Critical distance values of notched specimens

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图 9 基于临界距离法的疲劳寿命预测流程

Figure 9. Fatigue life prediction process based on the critical distance method

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图 10 σ_n=900 MPa下偏心孔模拟件孔边应力分布

Figure 10. Stress distribution at the hole edge of the eccentric hole simulating specimens under σ_n=900 MPa

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图 11 三种载荷下偏心孔模拟件孔边SWT参量分布

Figure 11. SWT distribution at the hole edge of the eccentric hole simulating specimens under three loads

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图 12 采用不同临界距离模型的疲劳寿命预测精度对比

Figure 12. Comparison of fatigue life prediction accuracy using different critical distance models

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表 1 GH4169力学性能

Table 1. Mechanical properties of GH4169

温度/℃	E/GPa	μ	σ_0.2/MPa
20	200	0.3	1030
400	176	0.31	960
500	163	0.32	920
600	150	0.32	880

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表 2 SWT模型参数取值

Table 2. Parameter values of the SWT model

参数	数值
$ {\sigma }^{\prime}_{\text{f}} $	917.07
$ {\varepsilon }^{\prime}_{\text{f}} $	1.00
b	−0.025
c	−0.6892

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表 3 缺口件临界距离取值

Table 3. Critical distance values of notched specimens

缺口件类型	中值寿命	临界距离 L_PM/mm	临界距离 L_LM/mm
K_t=4.9	24456	0.122	0.265
	28381	0.111	0.237
	50087	0.097	0.230
K_t=2.0	14585	0.174	0.361
	22459	0.237	0.495
	49383	0.348	0.727

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表 4 缺口件临界距离及应力梯度取值

Table 4. Critical distance and stress gradient values for notched specimens

缺口件类型	中值疲劳寿命	临界距离 L_PM/mm	临界距离 L_LM/mm	最大应力梯度G	高应力区范围 L_pe/mm
K_t=4.9	24456	0.122	0.265	5.731	0.0010
	28381	0.111	0.237	5.793	0.0015
	50087	0.097	0.230	5.870	0.0019
K_t=2.0	14585	0.174	0.361	0.870	0.0042
	22459	0.237	0.495	0.875	0.0063
	49383	0.348	0.727	0.882	0.0090

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表 5 三参数临界距离模型参数取值

Table 5. Parameter values of the three-parameter critical distance model

参数	取值（点法）	取值（线法）
A	0.1861	0.3894
B	−0.3362	−0.3029
C	−0.01	−0.01

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表 6 三参数模型计算偏心孔模拟件临界距离

Table 6. Critical distances of the eccentric hole simulating specimens from three-parameter model calculations

中值寿命	最大应力梯度G	高应力区 L_pe/mm	临界距离 L_PM/mm	临界距离 L_LM/mm
88465	0.518	0.0191	0.242	0.494
33031	0.492	0.0230	0.245	0.501
12280	0.466	0.0153	0.251	0.512

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表 7 基于断裂力学理论的临界距离模型SWT计算结果

Table 7. SWT calculation results of critical distance model based on fracture mechanics theory

平均应力计算方式	中值寿命	临界距离 L/mm	SWT参量/ （MPa·mm/mm）
点法	88465	0.0038	3.117
	33031		3.544
	12280		4.231
线法	88465	0.0153	3.094
	33031		3.524
	12280		4.208

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表 8 三参数临界距离模型SWT计算结果

Table 8. SWT calculation results of three-parameter critical distance model

平均应力计算方式	中值寿命	临界距离 L/mm	SWT参量/ （MPa·mm/mm）
点法	88465	0.242	2.676
	33031	0.245	3.084
	12280	0.251	3.611
线法	88465	0.494	2.623
	33031	0.501	3.033
	12280	0.512	3.574

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