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首页> 外文期刊>Indian Journal of Science and Technology >Experimental Studies for Visualization of Flow with Boundary Layers in an Axial Compressor Fan Inlet using Pressure Probes
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Experimental Studies for Visualization of Flow with Boundary Layers in an Axial Compressor Fan Inlet using Pressure Probes

机译：使用压力探头可视化轴流压气机进气口中边界层流动的实验研究

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Flow at inlet of fan in an axial compressor must be one dimensional as developed flow so that angular momentum fed by the fan to incoming air is maximum. It is possible with good inlet design and optimum inlet length where we obtain stream line flow into fan with nominal boundary layer thickness. Distortion to the flow at fan inlet in an axial compressor is unavoidable problem. For example in aircraft gas turbine engine; flow at inlet of fan is distorted due to maneuvering of air craft, strong cross winds and atmospherics turbulence at inlet of compressor. Flow at inlet of fan affects boundary layer and hence the performance of compressor. Therefore, visualization of flow with boundary layers in an axial ducted fan setup is carried out for well-defined inlet conditions using pressure probes. To visualize the flow with boundary layer development at the fan inlet, static and stagnation pressure are measured throughout the inlet passage of duct using static and pitot probe and velocity is calculated across the given reference planes of duct using Bernoulli’s equation. Using these data, profile plots are drawn and mathematical models are developed and flow with boundary layer is analyzed. Under normal inlet flow condition flow in the duct inlet is axisymmetric, steady, turbulent and incompressible. Boundary layer develops consistently towards the fan inlet and it is nominal.
机译：轴向压缩机中风扇入口处的流量必须是展开流量的一维，以使风扇馈入进气的角动量最大。良好的进气口设计和最佳的进气口长度是可能的，我们可以以标称边界层厚度获得流向风扇的流线。轴向压缩机中风扇入口处的流量失真是不可避免的问题。例如在飞机燃气涡轮发动机中;由于飞行器的操纵，强劲的侧风和压缩机进口处的大气湍流，风扇进口处的流量会失真。风扇入口处的流量会影响边界层，从而影响压缩机的性能。因此，在轴向导管式风机设置中使用边界压力传感器对边界条件明确的入口条件下的边界层流动进行了可视化。为了可视化风扇入口处边界层形成的流动，使用静态和皮托管探头测量整个管道入口通道的静压和停滞压力，并使用伯努利方程在整个给定的参考平面上计算速度。利用这些数据，绘制轮廓图，开发数学模型并分析边界层的流动。在正常的进口流量条件下，管道进口中的流量是轴对称的，稳定的，湍流的和不可压缩的。边界层始终朝着风扇入口发展，这是名义上的。

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