畸变风流对通风机叶轮构件影响数值模拟研究

    Numerical simulation study on the influence of distorted airflow on the impeller components of ventilation fans

    • 摘要: 基于矿用对旋式通风机因进气道内安置有插板构件而导致风流发生畸变效应为工程背景,采用仿真软件建立通风机相对应的网格结构模型,结合通风机运行效率,模拟结果确定了最优网格划分数量为6.62×106个。进一步采取Kω湍流模型来对通风机内风流运移状态进行模拟,结果表明:插板后方风流在上下两侧靠近通风机内壁位置处各形成一对方向相反的涡流区,且沿轴向方向下侧的一对涡流区逐渐减小直至消失,而上侧的一对涡流区则向底部位置运移延伸后形成了一对新的涡流区;畸变进气条件下风流整体上湍流脉动程度加剧,风流流线在叶片顶部、中部和根部分别呈现为流动分离、均匀分布和流动聚合现象;畸变区内相对气流角度变小,易发生叶片通道堵塞,严重时导致前级叶轮旋转失速;畸变区内风流流经叶轮后,叶片顶部区域压力最大值和最小值分别为4.09 kPa和3.37 kPa,畸变气流对叶片顶部影响显著。

       

      Abstract: Based on the engineering background of the distortion effect of airflow caused by the installation of insert plate components in the intake duct of the mining counter rotating fan, a corresponding grid structure model of this fan was established using simulation software. Combined with the simulation results of the fan's operating efficiency, the optimal number of grid divisions was determined to be 6.62 × 106. Furthermore, the K-ω turbulence model was adopted to simulate the airflow movement inside the ventilation fan. The results showed that the airflow behind the insert plate would form a pair of opposite vortex zones near the inner wall of the ventilation fan on both sides, and the pair of vortex zones on the lower side along the axial direction gradually decreased until they disappeared, while the pair of vortex zones on the upper side migrated and extended towards the bottom position, forming a new pair of vortex zones; Under distorted intake conditions, the overall turbulence and pulsation of the airflow are intensified, and the airflow streamline exhibits flow separation, uniform distribution, and flow aggregation phenomena at the top, middle, and root of the blade, respectively; The relative airflow angle in the distortion zone decreases, which can easily lead to blade channel blockage and, in severe cases, cause the front stage impeller to rotate and stall; After the airflow in the distortion zone passes through the impeller, the maximum and minimum pressure values at the top of the blade are 4.09 kPa and 3.37 kPa, respectively. The distortion airflow has a significant impact on the top of the blade.

       

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