大涵道比涡扇发动机风扇部件边线噪声预测

Fan Lateral Noise Prediction of High Bypass Ratio Turbofan Engine

随着现代民用航空发动机涵道比的不断增大,风扇噪声在发动机整机噪声中所占比重也越来越突出,因此对适航条件下的风扇噪声进行预测对发动机的降噪设计和飞机噪声适航验证工作具有重要意义。通过对涡扇发动机风扇部件噪声产生机理和影响其传播的环境因素的研究,并结合飞机起飞程序,建立了涡扇发动机风扇部件边线噪声预测模型。通过编程计算后与实测噪声进行数据对比,基于涡扇发动机风扇部件静态噪声预测值进行动态修正后的涡扇发动机风扇部件边线噪声预测模型可以较好地预测实际情况。

With constant increment of bypass ratio engine on the modern civil airliners,the proportion of fan noise in the total engine noise is becoming higher and higher.Therefore,it is of great significance to the worthiness certification of aircraft and development of new engines by predicting fan noise.Based on the take-off procedure,mechanism of fan noise and environment influences on noise propagation were studied.Comparing prediction values with real data,fan lateral noise prediction method through modification of aeroengine fan static noise can well predict the real case.