Effect of Saw Tooth Structure on Wake Characteristics of Compressor Blades
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摘要: 航空发动机的效率和噪声一直是人们关注的热点，压气机是航空发动机的重要组成部件，压气机叶片尾缘结构对其尾迹特性影响重大。为此，对某型轴流压气机叶片尾缘进行典型三角形锯齿建模，通过Fluent软件模拟研究锯齿尾缘叶片尾迹区域的三维湍流流场信息，对比不同尺寸的锯齿尾缘叶片与无锯齿尾缘叶片的尾迹流动特征和声场特征，分析锯齿尾缘叶片的流动损失机理及降噪机理。研究发现：流过锯齿尾缘的气流会通过锯齿缝隙从压力面流向吸力面，给予尾迹区域一定的能量补偿，从而减小尾迹的速度亏损和总压损失；尾缘锯齿结构会破坏叶片展向涡流结构，使大尺度涡变成各种不同尺度的小涡，通过涡能量扩散来降低尾缘噪声；在齿宽一定的情况下，存在一个最佳的齿高，使得降低流动损失和降低噪声的效果最佳。Abstract: The efficiency and noise of aero-engine have always been the focus of attention. Compressor is an important component in aero-engine. The trailing edge structure of compressor blade has a great influence on its wake characteristics. For this purpose, a typical triangular saw tooth model is established for the trailing edge of an axial compressor blade. The 3D turbulent flow field information in the wake region of a saw tooth trailing edge blade is simulated by using Fluent software. The wake flow characteristics and sound field characteristics of a saw tooth trailing edge blade with different sizes are compared with those of a saw tooth trailing edge blade without saw tooth trailing edge. The mechanism of flow loss and the mechanism of noise reduction are also discussed. It is found that the flow through the saw tooth trailing edge flows from the pressure surface to the suction surface through the saw tooth slot, and the energy compensation is given to the wake region to reduce the speed loss and total pressure loss of the wake. Eddy energy diffusion can reduce the trailing edge noise, and there is an optimum tooth height in the case of a certain tooth width, which makes the effect of the reducing flow loss and noise be best.
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Key words:
- compressor /
- saw tooth trailing edge /
- wake /
- flow loss /
- mechanism of noise reduction
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表 1 网格无关性验证
网格数 第一层网格厚度/mm Cd 1.2×106 0.005 0.048 8 2.2×106 0.005 0.049 2 3.2×106 0.005 0.049 1 
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表 2 总压损失系数
h/λ 进口总压 进口静压 ξ 0 6 290.67 -62.71 0.11 1 6 204.91 -164.93 0.086 2 6 715.80 344.98 0.086
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