高温高低周复合载荷试验加载技术  

High Temperature High and Low Cycle Composite Load Test Loading Technology

作　　者：张伟[1] 由于 黄太誉[1] 燕群[1] 徐健[1] ZHANG Wei;YOU Yu;HUANG Tai-yu;YAN Qun;XU Jian(Aero Engine Strength Laboratory,Aircraft Strength Research Institute of China, Xi'an 710065, China)

机构地区：[1]中国飞机强度研究所航空发动机强度研究室,西安710065

出　　处：《科学技术与工程》2022年第10期4222-4228,共7页Science Technology and Engineering

摘　　要：为了获取航空发动机涡轮转子叶片的疲劳寿命,通过电磁感应加热、高低周复合载荷协调加载控制方法实现正交载荷解耦联合加载,研究了转子叶片在高温环境、低周离心载荷和高周振动载荷耦合响应,并基于涡轮叶片模拟试验件,对上述技术进行了验证。结果表明,该试验技术具备可行性和正确性。可见该技术可以实现航空发动机结构部件的多场耦合复杂载荷强度试验加载。In order to obtain the fatigue life of aeroengine turbine rotor blades,orthogonal load decoupling combined loading was realized by electromagnetic induction heating and high-low cycle composite load coordinated loading control method.The coupling responses of rotor blades under high temperature environment,low cycle centrifugal load and high cycle vibration load were studied,and the above technology were verified based on turbine blade simulation test pieces.The results show that the test technology is feasible and correct.It can be seen that this technology can realize multi field coupling complex load strength test loading of aeroengine structural components.

关 键 词：涡轮转子叶片 高温高低周复合载荷 同步协调加载 航空发动机 

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]