榫连接结构叶片盘振动特性研究及验证

针对航空发动机榫连接结构叶片盘振动特性分析时,采用一体化处理建模方法导致计算精度降低的问题,开展了榫连接结构叶片盘振动特性研究.提出了一种考虑榫连接刚度的叶片盘建模方法,以燃气涡轮叶片盘对象,采用上述方法完成了考虑榫连接刚度的燃气涡轮叶片盘建模,在此基础上进行了叶片盘振动分析并开展了动应力试验验证.结果表明:采用考虑榫连接刚度的叶片盘模型得到的叶片共振转速计算精度在6％以内,相比于榫连接结构一体化的叶片盘模型,得到的共振转速计算精度提高50％.研究工作可为航空发动机叶片盘振动设计提供指导.

Research and Verification on Vibration Characteristics of the Blade Disk Connect by Tenon

In order to solve the problem that the calculation accuracy was reduced by using the integrated model of tenon connection structure in the analysis of the vibration characteristics of the blade disk.In this paper,a blade disk modeling method considering tenon connection stiffness was proposed.The gas turbine blade disk modeling was completed by using the above method,the dynamic analysis and the dynamic stress test of blade disk vibration were carried out.The result show that the calculation accuracy of blade resonance speed obtained by using the model considering tenon stiffess is less than 6%.Compared with the model with the integration of tenon connection structure,the calculation accuracy of blade resonance speed is improved by 50%.The research can provide guidance for the vibration design of aero-engine blade disk.