论文部分内容阅读
某型直升机发动机出现的尾喷管裂纹故障主要发生在尾喷管前转接段焊缝周围。为分析故障原因,文章建立了该型发动机尾喷管结构的计算模型。对该型喷管整体结构进行了自由振动和模态分析,获得了该喷管模型的多阶自振频率和模态。将有限元分析结果和实验结果对比表明,两者所得的固有频率吻合性较好。
A type of helicopter engine tail nozzle cracks occur mainly in the nozzle before the transition section around the weld. In order to analyze the cause of the failure, the paper established the calculation model of the tail pipe structure of the engine. The whole structure of the nozzle was subjected to free vibration and modal analysis, and the multi-order natural frequency and mode of the nozzle were obtained. The finite element analysis results and experimental results show that the natural frequency of the two obtained good agreement.