航空发动机涡轮叶片热冲击试验  

Thermal Shock Test of Aeroengine Turbine Blade

作　　者：沈晨 张江伟 韦瑾 Shen Chen;Zhang Jiangwei;Wei Jin

机构地区：[1]中国航发动力股份有限公司,西安710021

出　　处：《机械制造》2023年第9期73-77,共5页Machinery

摘　　要：某型航空发动机涡轮叶片在使用过程中发生疲劳断裂故障,为避免故障再次发生,对涡轮叶片的材料和结构进行改进,以提高涡轮叶片的振动疲劳强度和热疲劳强度。对改进前后的涡轮叶片进行热冲击试验,论述了试验原理,介绍了试验过程,并分析了试验结果。试验结果表明,改进后涡轮叶片的平均温度比原涡轮叶片低,叶身温度分布更均匀。进气边是涡轮叶片最易产生热疲劳裂纹的部位,改进后涡轮叶片的热疲劳寿命更长。A certain type of aeroengine turbine blade experienced fatigue fracture failure during use.In order to avoid the recurrence of the failure,the material and structure of the turbine blade were improved to improve the vibration fatigue strength and thermal fatigue strength of the turbine blade.Thermal shock test was carried out on the turbine blades before and after the improvement,the test principle was discussed,the test process was introduced,and the test results were analyzed.The test results show that the average temperature of the improved turbine blade is lower than that of the original turbine blade,and the temperature distribution of the blade body is more uniform.The inlet edge is the most prone part of the turbine blade to generate thermal fatigue crack,and the thermal fatigue life of the improved turbine blade is longer.

关 键 词：航空发动机 涡轮叶片 热冲击试验 

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]