基于氧化和烧结的涡轮导向叶片热障涂层区域失效分析  

Failure Analysis of Thermal Barrier Coating Area of Turbine Guide Blades Based on Oxidation and Sintering

作　　者：余鋆 张涛 YU Yun;ZHANG Tao(Beijing Aircraft Maintenance Engineering Corporation,Beijing 100000,China;Tianjin Key Laboratory of Civil Aircraft Airworthiness and Maintenance,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]北京飞机维修工程有限公司,北京100000 [2]中国民航大学天津市民用航空器适航与维修重点实验室,天津300300

出　　处：《中国陶瓷》2024年第8期30-38,共9页China Ceramics

摘　　要：研究氧化与烧结共同作用下对涡轮导向叶片热障涂层区域失效情况的影响有着重要意义。使用UG构建三维叶片流场模型并采用Fluent对其进行温度场分析,观察各区域下的热生长氧化物生长行为和烧结情况对涂层物性参数和氧化层厚度重新标定,利用ANSYS获得各区域涂层应力分布与大小,分析了区域热障涂层失效原因。结果表明不均匀温度场导致的氧化与烧结行为差异性,是造成涡轮导向叶片热障涂层损伤程度不同的根本原因。在叶盆区域涂层出现高应力集中现象,最大拉应力可达+299 MPa,这一分析为部件寿命评估提供借鉴。Studying the impact of oxidation and sintering on the failure of thermal barrier coating areas of turbine guide blades is of significant importance.Using UG to construct a three-dimensional blade flow field model and Fluent to analyze the temperature field.The thermal growth oxide growth behavior and sintering conditions in various regions were observed to recalibrate the coating’s physical properties and oxide layer thickness.ANSYS was utilized to obtain the distribution and magnitude of the coating stresses in each region,and the causes of thermal barrier coating failure in these regions were analyzed.The results show that the variability of oxidation and sintering behaviors due to the uneven temperature field is the root cause of the different damage levels of the thermal barrier coatings on the turbine guide blades.High stress concentration occurs in the coating of the blade basin region,with the maximum tensile stress reaching+299 MPa.This analysis provides a reference for component life assessment.

关 键 词：涡轮导向叶片 热障涂层 温度场 TGO层 应力大小与分布 

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] V263.6