摘要
基于热力耦合扩展逐层/实体元方法(TM-XLWM/SE)对热障涂层结构传热过程中的力学行为进行了研究。首先,利用热力耦合扩展逐层方法和三维实体元方法分别建立了热障涂层和金属基体的控制方程,然后,根据热障涂层和基体连接区域的位移、温度协调和内力平衡条件,将热障涂层和基体控制方程耦合为总体控制方程。依据总体控制方程,编写了相应的C++程序,通过与有限元软件Comsol建立的三维弹性模型进行对比,验证了方法的正确性。最后,对含分层损伤和界面脱黏损伤的热障涂层结构进行了热力耦合研究,得到了损伤对热力响应的影响规律。同时,所研究的外形更接近真实的发动机涡轮叶片,具有一定的实际应用价值。
Based on the thermomechanical extended-layerwise/solid-element method(TM-XLWM/SE),the mechanical behavior of thermal barrier coatings structure is studied during heat transfer.Firstly,the governing equations of the thermal barrier coating and the metal substrate are established by using the thermomechanical extended-layerwise method and the solid-element method,and then the governing equations of the thermal barrier coating and the metal substrate are coupled into the final governing equations according to the conditions of displacement,temperature coordination and internal force balance in the connecting region.According to the final governing equation,the corresponding C++code is developed.By comparison with the three-dimensional elastic model developed by Comsol,the correctness of TM-XLWM/SE to analyze thermal barrier coating structure is verified.Finally,thermal barrier coatings structures with delamination and interface debonding are studied,and the corresponding influence law is obtained.The structure studied is more similar to the real engine turbine blade,which has certain practical application value.
作者
李顶河
麻硕
Li Dinghe;Ma Shuo(Civil Aviation University of China,Tianjin 300300,China)
出处
《航空科学技术》
2021年第9期12-24,共13页
Aeronautical Science & Technology
基金
天津市教委科研计划项目(2018KJ241)。
关键词
热障涂层结构
动态热力耦合分析
分层损伤
界面脱黏
扩展逐层
thermal barrier coatings structure
dynamic thermomechanical analysis
delamination damage
interface debonding
XLWM
