Comparison of Predicted and Experimental Nusselt Number for a Film-Cooled Rotating Blade
Comparison of Predicted and Experimental Nusselt Number for a Film-Cooled Rotating Blade
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薄膜冷却旋转叶片的预测努塞尔数与实验对比
DOI：
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发表时间：
1996
期刊：
影响因子：
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通讯作者：
R. Abhari
中科院分区：
文献类型：
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作者：
V. Garg;R. Abhari
将三维Navier-Stokes代码的预测结果与薄膜冷却旋转涡轮机叶片上获得的努塞尔数数据进行了比较。所选择的叶片是ACE转子，具有五排，包含覆盖整个跨度的93个薄膜冷却孔。这是唯一的薄膜冷却旋转叶片，其实验传热数据可用于本比较。超过225万个网格点用于计算叶片上的流动。通常在静叶气膜冷却计算中，计算区域仅为一个展向气膜孔节距，且在展向具有周期性边界条件。然而，对于旋转叶片，计算域包括从轮毂到叶尖的整个叶片跨度，以及叶尖间隙区域。据作者所知，目前的工作提供了第一个比较的表面传热预测使用三维CFD代码与薄膜喷射和测量的热通量上的完全薄膜冷却的旋转跨音速涡轮机叶片。在与吸力面测量数据的详细比较中，获得了相当好的比较，特别是在轮毂部分附近。然而，在压力面上，数据和预测之间的比较很差。压力面差异的一个潜在原因可能是由于实验中定子-转子相互作用产生的非定常效应，而这些非定常效应在当前数值计算中未建模。
The predictions from a three-dimensional Navier-Stokes code have been compared to the Nusselt number data obtained on a film-cooled, rotating turbine blade. The blade chosen is the ACE rotor with five rows containing 93 film cooling holes covering the entire span. This is the only film-cooled rotating blade over which experimental heat transfer data is available for the present comparison. Over 2.25 million grid points are used to compute the flow over the blade. Usually in a film cooling computation on a stationary blade, the computational domain is just one spanwise pitch of the film-cooling holes, with periodic boundary conditions in the span direction. However, for a rotating blade, the computational domain consists of the entire blade span from hub to tip, as well as the tip clearance region.As far as the authors are aware of, the present work offers the first comparison of the prediction of surface heat transfer using a three dimensional CFD code with film injection and the measured heat flux on a fully film-cooled rotating transonic turbine blade. In a detailed comparison with the measured data on the suction surface, a reasonably good comparison is obtained, particularly near the hub section. On the pressure surface, however, the comparison between the data and the prediction is poor. A potential reason for the discrepancy on the pressure surface could be the presence of unsteady effects due to stator-rotor interaction in the experiments which are not modeled in the present numerical computations.Copyright © 1996 by ASME