首页> 外文会议>IMECE2009;ASME international mechanical engineering congress and exposition >FLOW INVESTIGATION THROUGH A 30° TURN DIFFUSING DUCT IN SUBSONIC FLOW REGIME
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FLOW INVESTIGATION THROUGH A 30° TURN DIFFUSING DUCT IN SUBSONIC FLOW REGIME

机译:通过亚音速流域中的30度转向扩散管道进行流量调查

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Curved diffusers are an integral component of the gas turbine engines of high-speed aircraft. These facilitate effective operation of the combustor by reducing the total pressure loss. The performance characteristics of these diffusers depend on their geometry and the inlet conditions. In the present investigation the distribution of axial velocity, transverse velocity, mean velocity, static and total pressures are experimentally studied on a curved diffuser of 30° angle of turn with an area ratio of 1.27. The centreline length was chosen as three times of inlet diameter. The experimental results then were numerically validated with the help of Fluent, the commercial CFD softwareThe measurements of axial velocity, transverse velocity, mean velocity, static pressure and total pressure distribution were taken at Reynolds number 1.9 × 105 based on inlet diameter and mass average inlet velocity. The mean velocity and all the three components of mean velocity were measured with the help of a pre-calibrated five-hole pressure probe. The velocity distribution shows that the flow is symmetrical and uniform at the inlet and exit sections and highvelocity cores are accumulated at the top concave surface due to the combined effect of velocity diffusion and centrifugal action. It also indicates the possible development of secondary motions between the concave and convex walls of the test diffuser. The mass average static pressure recovery and total pressure loss within the curved diffuser increases continuously from inlet to exit and they attained maximum values of 35% and 14% respectively. A comparison between the experimental and predicated results shows a good qualitative agreement between the two. Standard k-e model in Fluent solver was chosen for validation. It has been observed that coefficient of pressure recovery C_(pr) for the computational investigation was obtained as 38% compared to the experimental investigation which was 35% and the coefficient of pressure loss is obtained as 13% in computation investigation compared to the 14% in experimental study, which indicates a very good qualitative matching.
机译:弯曲扩散器是高速飞机的燃气涡轮发动机不可或缺的组成部分。这些通过减少总压力损失而促进燃烧器的有效操作。这些扩散器的性能特征取决于其几何形状和入口条件。在目前的研究中,轴向速度,横向速度,平均速度,静压力和总压力的分布是在30°转向角的弯曲扩散器上以面积比1.27进行实验研究的。中心线长度选择为入口直径的三倍。然后在商用CFD软件Fluent的帮助下对实验结果进行了数值验证。 根据入口直径和质量平均入口速度,以雷诺数1.9×105进行轴向速度,横向速度,平均速度,静压力和总压力分布的测量。借助预校准的五孔压力探头测量平均速度和所有三个平均速度分量。速度分布表明,入口和出口处的流动对称且均匀,且流速高 由于速度扩散和离心作用的共同作用,速度核心聚集在顶部凹面。它还表明在测试扩散器的凹壁和凸壁之间可能会发生二次运动。从入口到出口,弧形扩散器内的质量平均静压恢复和总压力损失连续增加,分别达到35%和14%的最大值。实验结果和预测结果之间的比较表明,两者之间在质量上有很好的一致性。选择Fluent求解器中的标准k-e模型进行验证。已经观察到,用于计算研究的压力恢复系数C_(pr)为38%,相比之下,实验研究为35%,而压力损失系数为13%,而实验研究为14%。在实验研究中,这表明了很好的定性匹配。

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