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浙江大学学报(工学版)
浙江大学学报(工学版)  2019, Vol. 53 Issue (4): 621-627    DOI: 10.3785/j.issn.1008-973X.2019.04.002
机械与能源工程     
航空发动机叶轮超高周疲劳寿命预测方法
王延忠1,2(),杨凯1,齐荣华1,陈燕燕1,李菲1,高浩2
1. 北京航空航天大学 机械工程及自动化学院，北京 100191
2. 三明学院 机电工程学院，福建 三明 365004
Ultra-high cycle fatigue life prediction method for aero engine impeller
Yan-zhong WANG1,2(),Kai YANG1,Rong-hua QI1,Yan-yan CHEN1,Fei LI1,Hao GAO2
1. School of Mechanical Engineering and Automation, Beihang University, Beijing 100191, China
2. College of Mechanical and Electrical Engineering, Sanming University, Sanming 365004, China
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摘要：

为了预测航空发动机叶轮的超高周疲劳寿命,以某型叶轮为研究对象，研究叶轮叶片在不同载荷状态下的应力和疲劳寿命. 建立叶轮的有限元模型，通过仿真分析叶轮叶片在离心、气动载荷作用下的应力变化情况；考虑叶轮叶片的表面状态，修正应力结果；基于位错偶极子模型及相关理论，建立TC4材料的超高周寿命预测模型；结合修正交变应力和寿命预测模型，实现了航空发动机叶轮的寿命预测. 对比分析现有模型和该模型下的寿命预测结果，结果表明：2种模型在低、高周范围内预测寿命的变化趋势一致；利用该模型有效解决了叶轮疲劳寿命的预测问题，预测值较贴近测试寿命；叶轮表面状态对疲劳寿命的预测结果影响较大，因为考虑了表面状态，寿命预测结果更贴近测试寿命值.
关键词： 航空发动机叶轮;  位错偶极子;  超高周疲劳;  寿命预测;  表面状态    
Abstract:

The stress and fatigue life of impeller of special equipment under different load conditions were analyzed in order to predict the ultra-high cycle fatigue life of aero-engine impellers. A finite element model of the impeller was established, and the stress changes of impeller blade which bears centrifugal and aerodynamic loads were simulated and analyzed. The results of further revise stress were achieved by considering surface state of impeller blade. An ultra-high cycle fatigue life prediction model for TC4 was established based on the dislocation dipole model and related theory. The service life for aero engine impeller was predicted by using the revised data and the prediction models. The service life predicted by existing model and the proposed model were compared. Results indicated that the changing of service life predicted by these two models showed the same trend in both low cycle and high cycle ranges. The problem of predicting the fatigue life of the impeller can be solved more effectively by the proposed model, and the predicted data was closer to the tested data. The surface state of the impeller had a greater impact on the prediction of fatigue life, because the predicted data was closer to the tested ones when considering the surface state.
Key words: aero-engine impeller    dislocation dipole    ultra-high cycle fatigue    life prediction    surface state
收稿日期: 2018-03-12 出版日期: 2019-03-28
CLC:  V 232  
作者简介: 王延忠（1963—），男，教授，博导，从事抗疲劳制造研究. E-mail： yzwang63@126.com
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王延忠
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李菲
高浩

引用本文:

王延忠,杨凯,齐荣华,陈燕燕,李菲,高浩. 航空发动机叶轮超高周疲劳寿命预测方法[J]. 浙江大学学报(工学版), 2019, 53(4): 621-627.

Yan-zhong WANG,Kai YANG,Rong-hua QI,Yan-yan CHEN,Fei LI,Hao GAO. Ultra-high cycle fatigue life prediction method for aero engine impeller. Journal of ZheJiang University (Engineering Science), 2019, 53(4): 621-627.

链接本文:

http://www.zjujournals.com/eng/CN/10.3785/j.issn.1008-973X.2019.04.002    或    http://www.zjujournals.com/eng/CN/Y2019/V53/I4/621

图 1  某型号离心叶轮
图 2  叶轮疲劳寿命计算模型
图 3  叶轮有限元模型
图 4  总压比随网格数量变化图
图 5  应力集中系数模型
Rs δa/MPa Mk/MPa Nf
?1 750 553 35 700
?1 725 553 135 600
?1 700 553 127 300
?1 675 553 168 950
?1 650 553 739 300
?1 625 553 2 173 600
表 1  TC4疲劳寿命数据[24]
拟合参数 现有模型 本文模型
$\alpha $ 0.255 1 0.035 4
h 0.021 3 —
kh — 0.003 7
表 2  疲劳寿命模型的参数拟合
图 6  2种模型的疲劳寿命预测结果对比图
图 7  叶片静态分析应力结果
图 8  叶片瞬态分析结果
图 9  粗糙度和应力集中系数的关系曲线
图 10  修正交变应力
寿命预测前提条件 原模型 本文模型
不考虑表面质量 — 1.38×108
考虑表面质量 — 3.59×108
表 3  寿命预测结果
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