某型航空发动机涡轮导向叶片热障涂层可靠性分析  

Reliability analysis of thermal barrier coatings on turbine guide vanes of a certain type of aero-engine

作　　者：王者 王志平 丁坤英 张涛 王远航 WANG Zhe;WANG Zhiping;DING Kunying;ZHANG Tao;WANG Yuanhang(Tianjin Key Laboratory of Civil Aircraft Airworthiness and Maintenance,Civil Aviation University of China,Tianjin300300,China;MTUMaintenanceZhuhai Co.Ltd,Zhuhai 519000,China)

机构地区：[1]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 [2]珠海保税区摩天宇航空发动机维修有限公司,珠海519000

出　　处：《航空学报》2024年第22期281-295,共15页Acta Aeronautica et Astronautica Sinica

基　　金：天津市研究生科研创新项目(2021YJSO2B08)。

摘　　要：针对某型民用航空发动机涡轮导向叶片热障涂层的可靠性进行了研究,建立了基于运行条件的叶片表面温度分布模型和基于温度分布的涂层失效模型,并采用Monte-Carlo模拟法计算了涡轮导向叶片热障涂层在不同服役时间和温度下的失效概率,预测了涡轮导向叶片服役寿命并与实际服役结果进行比较。结果表明:热障涂层的最大失效概率区域位于涡轮导向叶片的前缘和叶盆区域。以60%的失效概率为完全失效界限,在热气流作用下,叶片前缘区域的热障涂层平均寿命只有3857h,叶盆区域的平均寿命为7584h,叶背和后缘区域的平均寿命可达到104h以上。模拟计算服役可靠度与涡轮导向叶片实际检测结果的吻合度随服役时间变化始终保持在60%以上,证明使用的可靠性评价方法具有可信度和实用性。The reliability of the thermal barrier coating on the turbine guide blades of a certain civil aviation engine was studied,the blade surface temperature distribution model based on operating conditions,and the coating failure model based on temperature distribution were established.Moreover,the failure probability of the thermal barrier coating on the turbine guide blades at different service times and temperatures was calculated by Monte-Carlo simulation,the turbine guide blades'service life was predicted and compared with the actual service results.The results show that the maximum failure probability of the thermal barrier coating is located at the leading edge of the turbine guide blade and the blade basin area.With 60%failure probability as the limit of complete failure,the average life of the thermal barrier coating in the leading edge region of the blade is only 3857 h,the average life of the leaf basin region is 7584 h,and the average life of the backside and trailing edge regions of the blade is more than 10*h under the action of hot air flow.The agreement between the simulated service reliability and the actual inspection results of the turbine guided blades with the change of service time always stays above 60%,which proves that the reliability evaluation method used has credibility and practicality.

关 键 词：航空发动机 涡轮导向叶片 热障涂层 失效分析 可靠性 

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]