An experimental study of the stator blade wake in a small axial compressor is performed by using a hotwire anemometer (HWA) under different rotating speeds and mass flow conditions.
基于小型轴流压气机实验台，运用热线风速仪(HWA)，对不同转速、流量工况下，静叶排出口尾迹流动特性进行实验研究。
It has been found that wake loss of the blade has a great impact on the performance and stability of Turbomachinery, and also has been recognized as one of main noise sources of Turbomachinery.
尾迹损失对叶轮机械的工作效率和运行稳定性有很大影响，也是叶轮机械主要的噪声源之一。
Show in the experiment these results, which presents in the paper, may be used for predicting the axially attenuation of wake for the axial compressor blade.
理论分析结果与实测结果的比较表明，本文所提供的分析结果可以用来初步预计轴流压气机叶片尾迹沿轴向的衰减程度。
Experimental results show that under the effect of the rotor wake, the dominant frequencies of pressure fluctuations on stator blades are the rotor blade passing frequency (BPF) and its harmonics.
实验结果表明：在转子尾迹的影响下，静子叶片表面的波动频率是转子的尾迹频率及其倍频。
In addition, the wake interaction of upstream blade row and the expansion wave at rotor exit also cause an unsteady force acting on the downstream rotor blade surface.
此外上游静子尾迹以及动叶尾缘出口膨胀波等也是产生转子叶片表面非定常力的因素。
A rotor discrete free wake geometries and the blade airloads at each instant are presented.
旋翼的尾迹流强烈地影响旋翼桨叶的空气动力分布。
In Chapter 3, based upon the blade second-order lifting-line model and rotor free-wake model, an analytical method is developed for predicting the rotor wake structure and BVI airload.
基于桨叶二阶升力线理论和旋翼自由尾迹模型，本文在第三章建立了一个适合于直升机旋翼尾迹结构及桨-涡干扰气动特性分析的方法和模型。
The results indicated that in the two-blade impeller, the fluid mainly flowed along the suction side, the velocity is very small on the pressure side, and a typical jet-wake flow has been observed.
由测量结果可知：在双叶片叶轮内，流体基本沿叶片吸力面流动，叶片压力面上的相对速度较低，在压力面出口出现了速度很低的回流区，有明显“射流-尾迹”特征。
The results indicated that in the two-blade impeller, the fluid mainly flowed along the suction side, the velocity is very small on the pressure side, and a typical jet-wake flow has been observed.
由测量结果可知：在双叶片叶轮内，流体基本沿叶片吸力面流动，叶片压力面上的相对速度较低，在压力面出口出现了速度很低的回流区，有明显“射流-尾迹”特征。
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