基于运营数据的发动机压气机叶片裂纹扩展规律研究  

RESEARCH ON THE LAW OF ENGINE COMPRESSOR BLADE CRACK PROPAGATION BASED ON OPERATION DATA

作　　者：师利中[1] 董硕 刘雪峰[1] 陈健 SHI LiZhong;DONG Shuo;LIU XueFeng;CHEN Jian(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China;AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 201306,China)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]中国航发上海商用航空发动机制造有限责任公司,上海201306

出　　处：《机械强度》2024年第3期602-610,共9页Journal of Mechanical Strength

摘　　要：为研究航空发动机实际服役中转子叶片在复杂载荷作用下的裂纹损伤扩展规律,基于航空发动机运营数据构建叶片的裂纹扩展寿命曲线,同时采用断裂力学理论建立裂纹扩展速率公式。以高压压气机叶片为实例,通过流固耦合方法构建压气机叶片结构的载荷模型,分别采用Paris、Walker、Newman裂纹扩展速率公式对压气机叶尖区域进行三维裂纹扩展分析。仿真结果表明,三种裂纹扩展速率公式在裂纹扩展前期预测结果与发动机运营数据裂纹扩展曲线具有一致性,可较好地描述叶片裂纹扩展规律;在裂纹稳定扩展阶段,Walker和Newman公式预测结果相对危险,Paris公式预测结果吻合度较高,并且能与厂家技术手册中关于其损伤发展控制要求相互印证。In order to study the crack damage propagation law of rotor blades under complex loads in the actual service of aero⁃engines,the crack propagation life curve of blades was constructed based on the operational data of aero⁃engine,and the crack propagation rate formula was established by fracture mechanics theory.Taking the high⁃pressure compressor blade as an example,the load model of the compressor blade structure was constructed by the fluid⁃solid coupling method.The Paris,Walker and Newman crack growth rate formulas were used to analyze the three⁃dimensional crack propagation in the tip region of the compressor blade.The simulation results show that the prediction results of the three crack propagation rate formulas are consistent with the crack propagation curve of the engine operation data in the early stage of crack propagation,which can better describe the crack propagation law of the blade.In the stage of stable crack propagation,the prediction results of Walker and Newman formulas are relatively dangerous,and the prediction results of Paris formula are in good agreement with each other,and can be mutually confirmed with the requirements of damage development control in the manufacturer′s technical manual.

关 键 词：压气机叶片 运营数据 断裂力学 裂纹扩展速率公式 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]