摘要
随着涡扇发动机涵道比的不断提高,风扇噪声对于发动机总噪声的贡献量越来越大,因此准确地预测风扇噪声对发动机的降噪设计和适航符合性评估具有重要的意义。在现有风扇噪声半经验预测模型架构的基础上,利用某型号大涵道比涡扇发动机的噪声试验数据,适应性地发展了风扇纯音噪声预测模型,将预测模型中的转/静间距函数与叶片后掠角及工况相关联,并提出考虑不同工况影响的指向性函数,预测精度较现有模型有大幅提升。与试验数据的对比表明,本模型的预测误差在5 dB之内,验证了新开发模型的准确性。
With the continuous improvement of the bypass ratio of turbofan engines,the contribution of fan noise to the total engine noise is increasing.Therefore,accurate prediction of fan noise is of great significance for low-noise engine design and airworthiness compliance assessment.Based on the existing semi-empirical prediction architecture of fan noise,a tone noise prediction model has been developed using measured data of a high bypass ratio turbofan engine.The model associates the rotor/stator spacing function with the vane sweep angle and operating conditions,and the directivity function is improved with various operating conditions.The prediction accuracy has been remarkably improved compared to existing models.Comparing with the experimental data,the prediction error is within 5 dB,illustrating the accuracy of the newly developed model.
作者
洪志亮
赵北星
李旦望
HONG Zhiliang;ZHAO Beixing;LI Danwang(College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China;China Special Vehicle Research Institute,Jingmen 448035,China;AECC Commercial Aero Engine Co.,Ltd,Shanghai 201108,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2024年第6期90-99,共10页
Journal of Propulsion Technology
基金
中央高校基本科研业务费(3122021087)。
关键词
航空器噪声适航审定
涡扇发动机
大涵道比
风扇噪声
噪声预测
经验模型
Aircraft noise airworthiness certification
Turbofan engine
High bypass ratio
Fan noise
Noise prediction
Empirical model
