摘要
针对现有的仿真方法和试验方法无法评估受感部装机使用时受到的气动载荷和温度载荷对耙体结构强度和固有频率的影响的问题,提出了使用流-热-固耦合方法开展模拟装机状态受感部的结构强度和模态特性研究。首先使用计算流体力学仿真方法得到受感部表面温度和压力分布;将表面温度数据导入Steady-state Thermal模块中进行稳态热分析,得到耙体温度分布;将气动载荷和温度载荷导入静强度分析模块,进行热应力和静应力仿真,计算得到耙体最大变形为0.336 mm,耙体最大应力为97.867 MPa;开展预应力下的受感部模态分析,发现相比传统方法,预应力模态分析计算得到前六阶固有频率均高于传统方法计算结果,且能够避开发动机典型状态固有频率10%以上,所设计的受感部已经装机使用,验证了计算结果的可靠性。
Aiming at the problem that the existing simulation and test methods can't evaluate the influence of aerodynamic load and temperature load on the structural strength and natural frequency of the probe when the probe is installed,the flow-thermal-solid coupling method was proposed to study the structural strength and modal characteristics of the probe measured in the simulated installation state.Firstly,the CFD(computational fluid dynamics) simulation method was used to obtain the temperature and pressure distribution of the probe surface.The temperature data was imported into the Steady-state Thermal module for steady-state thermal analysis to obtain the probe temperature distribution.The aerodynamic load and temperature load were introduced into the static strength analysis module,and the thermal stress and static stress simulation were carried out,and the maximum deformation of the probe body is calculated to be 0.336 mm and the maximum stress of the probe body is 97.867 MPa.The measured probe modal analysis under pre-stress was carried out,and it is found that the natural frequencies of the first six orders are higher than the calculation results of the traditional method,and the natural frequency of the probe differs from the engine more than 10%,and the designed probe has been installed and used,the reliability of the calculation results is verified.
作者
贾文杰
宋江涛
王世栋
JIA Wen-jie;SONG Jiang-tao;WANG Shi-dong(Chinese Flight Test Establishment,Xi’an 710089,China)
出处
《科学技术与工程》
北大核心
2024年第26期11457-11462,共6页
Science Technology and Engineering
