改进的多级涡轮噪声经验预测模型  

Improved empirical prediction model for multi-stage turbine noise

作　　者：纪良[1] 乔渭阳[1] 王良峰[1] 英基勇[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空工业集团公司商用航空发动机有限责任公司,上海200241

出　　处：《航空动力学报》2015年第5期1210-1218,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51276149)

摘　　要：基于早期的涡轮噪声经验预测模型和涡轮噪声试验数据,对影响涡轮噪声的关键涡轮参数进行了分析,发展了改进的多级涡轮噪声经验预测模型.该模型由单级涡轮噪声计算、涡轮噪声在下游涡轮级中传播的衰减量计算和各级涡轮噪声叠加3个部分组成.采用涡轮噪声试验数据对单级涡轮噪声计算方法进行了验证.结果表明:该单级涡轮噪声计算方法的计算结果误差小于1.5dB.由试验数据拟合得到的涡轮噪声叶片排衰减经验预测模型也被应用于该改进的多级涡轮噪声经验预测模型中.与早期经验预测模型相比,改进模型的计算方法更合理,噪声预测结果更可靠.Based on early empirical prediction models and the test data of turbine noise, the key parameters of turbine which may influence the turbine noise were analyzed. And an improved empirical prediction model for multi-stage turbine noise was developed. This im- proved model was composed of three components： computation for single stage turbine noise, computation for the noise attenuation effect of each downstream turbine stage and su- perposition for the noise of each stage turbine. The calculation method for single stage tur- bine noise had been validated by use of turbine noise test data. Result shows that, the calcu- lation deviation is less than 1.5 dB. An empirical prediction method fitting by experimental data for the propagation attenuation caused by downstream blade rows is also used in the im- proved multi-stage turbine noise prediction model. With comparison to early empirical pre- diction models, the calculation method of the improved model is more reasonable and the noise prediction result is more reliable.

关 键 词：经验预测模型 涡轮噪声 多级 单级 衰减 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]