航空发动机宽弦风扇叶片鸟撞损伤模型标定

为建立航空发动机风扇叶片抗鸟撞载荷能力的量化预测方法,针对特定的航空发动机宽弦风扇叶片设计,依据发动机在典型工作状态下的吸鸟速度、角度等撞击参数开展叶片鸟撞试验,采用显式动力学数值仿真方法,建立叶片鸟撞试验仿真分析模型,并通过对模型中叶片材料参数、鸟体本构模型参数、鸟与叶片耦合接触参数进行敏感度分析,对模型进行标定.结果表明,标定后的鸟撞分析模型所预测的叶片损伤模式与试验结果一致,预测的损伤位置与试验测量结果误差小于10%. 

Bird strike model calibration for an aero engine wide-chord fan blade

To establish a quantitative prediction method for the anti bird-strike capability of aero engine fan blade, a set of equivalent bird strike tests were performed with the impact parameters, e.g. the velocity and angle of the bird under typical engine operation conditions for a particular titanium wide-chord fan blade design. Then, an explicit dynamic simulation model was built to simulate the bird strike. Through sensitivity analysis, the blade material parameters, the bird body parameters and the blade-bird coupling contact parameters in the simulation model were calibrated based on the test results. The results show that the blade failure mode predicted by the calibrated bird-strike model is consistent with the test, and the prediction error of the failure location is within 10% compared with the test observation error.