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Computation of the Throat Area of a Turbine Blade Ring

机译:涡轮叶片环喉面积的计算

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The throat area is a geometric parameter of the blade ring necessary to profile its blades and compute the turbine capacity. As applied to the filament flow model, the area is defined by the involute of the throat solid figure ontothe plane formed by the cascade throat located on one of the cylindrical sections of the blade ring and the radius. An equation is derived for computing the area of the involute, which considers the effect of the shape of the ring's tailing outlines and the fillets at the transition from the outlines to the blade feather. Comparison of the area values for several turbines computed by the derived equation and by a more complex method based on a search for the minimum distances from the tailing edge of the blade to the suction surface of the neighboring blade in the channel revealed slight differences. The fluid-dynamic 2D analysis determined the radial boundaries of the filament bands, the parameters of the cascade that lie on a filament's cylindrical surfaces, and the flow velocity normal to the throat section of the filament. The proposed approach to computation of the throat area is common for problems of both designing and analyzing the turbine operation and allows for excluding, in practice, methodological differences in determination of the flow rate and the flow angles at the outlet of the blade ring.
机译:喉部面积是叶片环的几何参数,是叶片轮廓和计算涡轮容量所必需的。当应用于长丝流动模型时,该区域由喉部实体图形渐开线到由位于叶片环的圆柱部分和半径之一上的级联喉部形成的平面上的渐开线限定。导出了一个用于计算渐开线面积的方程式,该方程式考虑了环的尾部轮廓和圆角在从轮廓过渡到叶片羽状过渡时的形状的影响。通过推导方程和一种更复杂的方法(基于从叶片的尾缘到通道中相邻叶片的吸力面的最小距离的搜索)计算出的多个涡轮机的面积值的比较显示出细微的差别。流体动力学2D分析确定了细丝束带的径向边界,细丝的圆柱表面上的级联参数以及垂直于细丝的喉部的流速。对于设计和分析涡轮机运行的问题,所提出的计算喉部面积的方法是常见的,并且在实践中允许排除确定叶片环出口处的流速和流角时的方法学差异。

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