航空发动机叶片高低周复合疲劳寿命预测与损伤机理研究  被引量:3

Aero-engine blade high and low circumference composite fatigue life prediction and damage mechanism research

在线阅读下载全文

作  者:王妍 毕俊喜 葛新宇[2] 王柳璎 王永相 WANG Yan;BI Junxi;GE Xinyu;WANG Liuying;WANG Yongxiang(School of Aviation,Inner Mongolia University of Technology,Hohhot 010051,China;School of Mechanical Engineering,Inner Mongolia University of Technology,Hohhot 010051,China;Hohhot Zhonghuan Industry and Trade Co,Ltd,Hohhot 010051,China)

机构地区:[1]内蒙古工业大学航空学院,呼和浩特010051 [2]内蒙古工业大学机械工程学院,呼和浩特010051 [3]呼和浩特众环工贸股份有限公司,呼和浩特010051

出  处:《内蒙古工业大学学报(自然科学版)》2023年第4期324-329,共6页Journal of Inner Mongolia University of Technology:Natural Science Edition

基  金:国家自然科学基金项目(52165019);内蒙古自治区直属高校基本科研业务费项目(JY20220305)。

摘  要:针对航空发动机叶片在服役期间承受交变载荷极易发生疲劳损伤和高低周复合疲劳寿命预测问题,开展了叶片损伤机理分析和基于高低周复合载荷的耦合疲劳寿命预测模型研究。首先,分析了航空发动机叶片的损伤机理和失效模式,并依据叶片振动特性进行了模态分析。其次,在Zhu模型的基础上,提出了一种基于改进-Zhu模型的高低周复合疲劳寿命预测模型。最后,将Miner模型、Zhu模型和所提出改进-Zhu模型的疲劳寿命预测结果与高低周复合疲劳试验数据进行对比。结果表明:所提出的改进-Zhu模型计算精度在1.5倍误差范围内,预测结果相对较小,验证了其可行性和有效性。研究工作为可靠预测航空发动机叶片的工作寿命和疲劳强度设计提供了一定参考。In response to the problem of fatigue damage and high and low circumferential composite fatigue life prediction of aero-engine blades under alternating loads during service,the analysis of blade damage mechanism and the study of coupled fatigue life prediction model based on high and low circumferential composite loads were carried out.Firstly,the damage mechanism and failure mode of the aero-engine blade are analyzed,and the modal analysis is carried out based on the blade vibration characteristics.Then,based on the Zhu model,a high and low circumferential composite fatigue life prediction model based on the improved-Zhu model is proposed.Finally,the fatigue life prediction results of Miner model,Zhu model and the proposed improved-Zhu model are compared with the high and low circumferential composite fatigue test data.The results show that the calculation accuracy of the proposed improved-Zhu model is within 1.5 times of the error range and the prediction results are relatively small,which verifies its feasibility and validity.The research work provides a certain reference for reliable prediction of the working life and fatigue strength design of aero-engine blades.

关 键 词:航空发动机叶片 高低周复合疲劳 疲劳损伤 寿命预测 

分 类 号:V232.4[航空宇航科学与技术—航空宇航推进理论与工程]

 

参考文献:

正在载入数据...

 

二级参考文献:

正在载入数据...

 

耦合文献:

正在载入数据...

 

引证文献:

正在载入数据...

 

二级引证文献:

正在载入数据...

 

同被引文献:

正在载入数据...

 

相关期刊文献:

正在载入数据...

相关的主题
相关的作者对象
相关的机构对象