基于临界距离理论的修复叶片疲劳极限评估

柯镇汭; 尚一博; 李斌; 赵振华; 周留成; 王晨; 易敏

doi:10.13224/j.cnki.jasp.20230665

基于临界距离理论的修复叶片疲劳极限评估

doi: 10.13224/j.cnki.jasp.20230665

柯镇汭^1,,
尚一博^{2, 3},
李斌^{2, 3,*, ,},
赵振华⁴,
周留成^{3, 5},
王晨^{2, 3},
易敏¹

1.
南京航空航天大学航空航天结构力学及控制全国重点实验室，南京 210016
2.
空军工程大学基础部，西安 710051
3.
空军工程大学航空动力系统与等离子体技术全国重点实验室，西安 710038
4.
南京航空航天大学能源与动力学院，南京 210016
5.
空军工程大学航空工程学院，西安 710038

基金项目: 国家科技重大专项（J2019-Ⅳ-0014-0082）；陕西省自然科学基础研究计划项目（2023-JC-QN-0044，2023-JC-QN-0094，2024JC-YBQN-0065）

详细信息

作者简介:
柯镇汭（1999-），男，硕士生，研究方向为固体力学。E-mail：657478871@qq.com

通讯作者:
李斌（1991-），男，讲师，硕士，主要从事航空结构强度领域的研究工作。E-mail：18840367753@163.com

中图分类号: V232.4
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- 被引次数: 0
出版历程
- 收稿日期: 2023-10-18
- 网络出版日期: 2025-07-13

Fatigue limit evaluation of repaired blades based on the theory of critical distance

KE Zhenrui^1
,,
SHANG Yibo^{2, 3},
LI Bin^{2, 3,*
, ,},
ZHAO Zhenhua⁴,
ZHOU Liucheng^{3, 5},
WANG Chen^{2, 3},
YI Min¹

1.
State Key Laboratory of Mechanics and Control for Aerospace Structures，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Fundamentals Department，Air Force Engineering University，Xi’an 710051，China
3.
National Key Lab of Aerospace Power System and Plasma Technology，Air Force Engineering University，Xi’an 710038，China
4.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
5.
Aviation Engineering School，Air Force Engineering University，Xi’an 710038，China

摘要

摘要:
外物损伤是影响航空发动机风扇和压气机叶片服役安全的重要因素。对于尺寸较小的外物损伤缺口，通常采用机加或手工打磨方式进行维修。为了准确评估机加和打磨修复的缺口叶片疲劳性能，本文首先测试了机加和打磨修复叶片的高周疲劳极限，然后基于临界距离理论建立了疲劳极限评估模型，分析了不同应力选取方法对模型精度的影响，并与经典Peterson模型进行了对比。结果表明：基于临界距离理论建立的模型可以准确预测机加和手工打磨等修复工艺的缺口叶片疲劳极限；在临界距离模型中，使用主应力绝对值的最大值进行预测与使用沿叶片长度方向正应力进行预测差别很小；其模型精度（平均误差小于11%）远高于Peterson经典模型（平均误差26.03%）。
- 钛合金叶片 /
- 修复处理 /
- 高周疲劳极限 /
- 临界距离理论 /
- Peterson模型
Abstract:
Foreign object damage is an important factor affecting the service of aeroengine fan and compressor blades. Small foreign object damaged notch can be typically repaired by machining or polishing. To evaluate the fatigue properties of the machined and polished blades, the high-cycle fatigue strength of the machined and polished blades was tested, and the fatigue limit prediction model was built based on the theory of critical distance, and compared with the classical Peterson model. The influences of different stress selection methods on the accuracy of the model were analyzed. The results showed that the model based on the theory of critical distance can accurately predict the fatigue limit of repaired notched blades, including a variety of repair processes, such as machining and polishing. There was little difference between the prediction using the maximum absolute value of the principal stress and the normal stress along the blade length. The model accuracy from theory of critical distance (average error less than 11%) was much higher than the classical Peterson’s model (average error 26.03%).
- titanium blade /
- repair treatment /
- high-cycle fatigue limit /
- theory of critical distance /
- Peterson model

HTML

图 1 TC17显微组织（SEM图像）

Figure 1. Microstucture of TC17 （SEM image）

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图 2 模拟叶片试样

Figure 2. Simulated blade sample

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图 3 缺口叶片图

Figure 3. Notched blade diagram

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图 4 振动试验夹具和试件

Figure 4. Fixtures and specimens of vibration test

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图 5 步进法示意图

Figure 5. Schematic diagram of the step method

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图 6 叶片有限元仿真网格

Figure 6. Finite element simulation mesh of the blade

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图 7 有限元仿真计算的Mises应力云图

Figure 7. Mises stress nephogram of the finite element simulation

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图 8 Ⅰ-3#打磨叶片振动疲劳断口的微观特征

Figure 8. Ⅰ-3# microscopic features of polished blade’ vibration fatigue fracture

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图 9 基于临界距离理论的缺口叶片疲劳极限评估模型建模过程

Figure 9. Modeling process of notched blade fatigue limit prediction based on the critical distance theory

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图 10 机加/打磨修复叶片的疲劳极限预测结果

Figure 10. Fatigue limit predicted results of machined/polished repaired blades

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表 1 疲劳极限测试结果

Table 1. Results of fatigue limit tests

试件编号	类型	缺口宽度2b/mm	缺口深度a/mm	应力集中系数	测点处疲劳极限/MPa	结构疲劳极限/MPa
Ⅰ-1#	机加	4	1	1.597	43.85	259.38
Ⅰ-2#	机加	6	1	1.314	56.31	333.05
Ⅰ-3#	打磨	17.05	1.662	1.306	54.88	272.33
Ⅱ-1#	机加	4	1	1.523	34.48	266.80
Ⅱ-2#	机加	6	1	1.347	36.18	279.97
Ⅱ-3#	打磨	16.13	2.12	1.397	47.55	291.92

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表 2 模型的预测结果

Table 2. Predicted results of the model

参数		Ⅰ-1#	Ⅰ-2#	Ⅰ-3#	Ⅱ-1#	Ⅱ-2#	Ⅱ-3#
参数		σ_e=259.38 MPa	σ_e=333.05 MPa	σ_e=272.33 MPa	σ_e=266.80 MPa	σ_e=279.97 MPa	σ_e=291.92 MPa
临界距离模型（主应力）	r_c/mm	0.86	1.59	1.62	1.01	1.07	1.92
	r_c平均值	η = 2.0，r_c = 1.3558 mm
	预测值/MPa	305.18	314.30	258.95	300.44	301.67	254.94
	误差/%	10.20±4.95
临界距离模型（正应力）	r_c/mm	0.84	1.56	1.60	0.98	1.05	1.90
	r_c平均值	η = 2.0，r_c = 1.3325 mm
	预测值/MPa	305.44	314.25	258.72	300.96	301.67	254.47
	误差/%	10.30±4.99
Peterson 模型	预测值/MPa	315.20	381.29	383.14	330.49	372.07	358.16
Peterson 模型	误差/%	26.03±8.48

下载: 导出CSV

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