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首页> 外文期刊>International Journal of Applied Mathematics & Statistics >Study of 3D Flow Characteristics Through Endwall Junction Body Airfoil British 9C7/22.5C50 with the Addition of Forward Facing Step Turbulator (FFST)
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Study of 3D Flow Characteristics Through Endwall Junction Body Airfoil British 9C7/22.5C50 with the Addition of Forward Facing Step Turbulator (FFST)

机译：附加有前向步进涡轮（FFST）的通过端壁结体翼型英国式9C7 / 22.5C50的3D流动特性的研究

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摘要

3D flow separation is one form of loss of endwall-body junction. Therefore it is necessary to attempt to reduce these losses. One way to do that is by adding Forward Facing Step Turbulator (FFST). This research aims to study the characteristics of 3D flow separation across the endwall junction body airfoil British 9C7/42.5C50 with and without the addition of FFST. Geometry airfoil has a chord-length 120 mm, the distance between the airfoil to FFST is 2/3 C, and step height (h) 4.8 mm. Analysis of shear stress line obtained through experiments using the technique of Oil Flow Vizualization (OFV) in the wind-tunnel. Free stream velocity in this study, used Reynolds number 1.64×10~5. The results of the study confirmed by velocity-vector and path line analysis, axial total pressure loss coefficient on the exit, which is generated by 3D numerical simulations with the viscous model of k-ε standard. Variation of the angle of attack 4°, 10° and 12°. The results showed that the addition of the FFST, turbulence intensity of inlet flow will increase, so that the flow is more able to resist of friction and adverse-pressure-gradient. The effectiveness of the addition of FFST occurs in angle-of-attack 4°. The results of this study can provide information about the flow phenomena on airfoil end wall junction body British 9C7/42.5C50. It can be used as a consideration in the form of axial compressor inlet nozzle.
机译：3D流动分离是端壁-主体连接处损失的一种形式。因此，有必要尝试减少这些损失。一种方法是添加前向步进涡轮（FFST）。本研究旨在研究在添加和不添加FFST的情况下，穿过端壁结体翼型英国式9C7 / 42.5C50的3D流动分离的特性。几何翼型的弦长为120 mm，翼型到FFST的距离为2/3 C，阶高（h）为4.8 mm。通过使用风洞中的油流Vizualization（OFV）技术进行的实验获得的剪切应力线的分析。在本研究中，自由流速度使用的雷诺数为1.64×10〜5。研究结果通过速度矢量和路径分析，出口处的轴向总压力损失系数确定，该系数是通过使用k-ε标准粘滞模型进行3D数值模拟得出的。迎角的变化为4°，10°和12°。结果表明，加入FFST后，进口流的湍流强度将增加，从而使流动更能抵抗摩擦和反压力梯度。在攻角为4°时，添加FFST的有效性。这项研究的结果可以提供有关翼型端壁结体英国9C7 / 42.5C50上流动现象的信息。可以考虑将其作为轴向压缩机进口喷嘴的形式使用。

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