航空发动机动力涡轮叶片断裂试验

Fracture Test of Aero-engine Power Turbine Blade

为研究航空发动机动力涡轮叶片的断裂转速随弯曲应力占比的变化规律,基于等效原则设计加工了4种不同弯曲应力占比、共32件模拟叶片,采用有限元法分别计算得到模拟叶片的断裂转速。对模拟叶片进行分组并开展了断裂转速测量试验,获取了模拟叶片的实际断裂转速和断裂形式,采用高速摄像技术录取了模拟叶片断裂过程,得到了叶片断裂转速随弯曲应力占比的变化规律。研究表明,模拟叶片实际断裂转速与计算转速误差不大于1.10%;在一定范围内,随着弯曲应力的降低,叶片的断裂转速大体呈现下降趋势,并且随着叶片的弯曲应力占比越大,叶片的断裂转速下降越快。研究为动力涡轮叶片的强度设计和叶片断裂试验方法提供了参考,具有重要的工程应用价值。

To study the fracture speed of power turbine blades in aero-engine and its variation law with the proportion of bending stress,a total of 32 simulated blades with 4 different ratios of bending stress were designed and processed based on the principle of equivalence.The fracture speed of the simulated blades was calculated by finite element method.The simulated blades were grouped and fracture speed measurement experiments were conducted to obtain the actual fracture speed and fracture form of the blades.The simulated blade fracture test process was recorded by high-speed camera technology,and the variation law of blade fracture speed with the proportion of blade bending stress was obtained.The research results show that the error between the actual fracture speed and the calculated speed of the simulated blades are not greater than 1.10%.Within a certain range,as the bending stress decreases,the fracture speed of the blade generally shows a downward trend,and as the proportion of bending stress in the blade increases,the fracture speed of the blade decreases faster.The research provides a reference for the strength design and blade fracture test methods of real blades,which has important engineering application value.