摘要
有限元模拟鸟撞风扇叶片损伤成本高,为解决工程问题,采用经典叶栅鸟撞切割模型建立了鸟撞风扇叶片动载荷数学模型,结合鸟撞部件试验结果,以拟合技术明确风扇叶片损伤程度与最大关键动载荷计算值间的函数关系,形成叶片损伤预测响应面,实现对鸟撞风扇叶片损伤的快速预测,并建立基于响应面法的鸟撞风扇叶片损伤预测工作流程。结合涡扇发动机吞鸟试验技术要求、风扇结构设计特征及已开展的鸟撞部件试验结果,建立叶片损伤预测响应面,初步识别2种鸟撞方案的径向弯曲、弦向弯曲,并计算撕裂范围分别不超过0.3867和0.3941,撕裂与弦向弯曲相关性显著,呈抛物线变化趋势。结果表明:预测的损伤在可接受的安全性水平范围内,预测方法能够识别损伤范围及趋势,可为后续鸟撞有限元模拟、试验策划、安全性分析、风扇叶片抗鸟撞设计等工作提供量化的技术支持。
The cost of finite element simulation of bird strike fan blade damage is high.In order to solve engineering problems,the classic bird strike cascade slicing model is used to establish the mathematical model for the dynamic load of bird impact.Combined with the results of bird strike component tests,the fitting technology was used to clarify the functional relationship between the degree of fan blade damage and the calculated value of the maximum critical dynamic load,and the blade damage prediction response surface was formed.Rapid prediction of fan blade damage due to bird strike was realized,and the prediction workflow based on the response surface method was established.Combined with the requirements of the turbofan engine bird ingestion test,the fan structural features,and the results of the conducted bird strike component tests,the blade damage prediction response surface was established,the radial bending,and chordwise bending of two bird-strike schemes were preliminarily identified,and the tearing ranges do not exceed 0.3867 and 0.3941,respectively.The tearing and the chordwise bending are significantly correlated,showing a parabolic trend.The results show that the predicted damage is within the acceptable safety level.The prediction method can identify the damage range and trend.It can provide quantitative technical support for subsequent work such as bird strike finite element simulation,test planning,safety analysis,fan blade bird strike resistant design,etc.
作者
刘洋
罗忠
张海洋
沈丽娟
赵凤飞
张宗锴
LIU Yang;LUO Zhong;ZHANG Hai-yang;SHEN Li-juan;ZHAO Feng-fei;ZHANG Zong-kai(AECC Shenyang Engine Research Institute,Shenyang 110015;School of Mechanical Engineering&Automation,Northeastern University,Shenyang 110819)
出处
《航空发动机》
北大核心
2024年第2期95-100,共6页
Aeroengine
基金
航空动力基础研究项目资助。
关键词
鸟撞
风扇叶片
损伤
响应面法
航空发动机
bird strike
fan blade
damage
response surface method
aeroengine
