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首页> 外文会议>AIAA/ASME/SAE/ASEE joint propulsion conference exhibit >Investigation on the Effects of Wake Rod to Film Cooling Hole Diameter Ratio in Unsteady Wake Studies
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Investigation on the Effects of Wake Rod to Film Cooling Hole Diameter Ratio in Unsteady Wake Studies

机译：非稳态尾流研究中尾流杆与薄膜冷却孔直径比的影响研究

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In recent decades, greater interest in the effect of rotational wakes on gas turbine film cooling applications has produced increasing numbers of studies on these unsteady phenomena. Wakes are primarily shed from upstream components such as transition duct walls, stator vanes, and rotors. Studies have shown that in areas of unsteady flow, the best performing parameters in conventional steady investigations may not be the best for unsteady applications. One common method of modeling the rotor-stator interaction in subsonic flows is the use of spoke wheel type wake generators using cylindrical rods to produce the velocity detriment and local increase in turbulence intensity. Among the results published to date, no mention on the potential effect of the wake rod to film cooling hole diameter ratio has been addressed. Disagreement among investigators concerning the trailing edge thickness and the effect of boundary layer growth has led to diameter ratios from 0.5 to 5.6 in open literature. This investigation measures the effect of the diameter ratio on the adiabatic film cooling effectiveness over three diameter ratios of 2.375, 4.75, and 9.5 in order to determine any dependence on this typically unidentified parameter. Blowing ratios of 0.25, 0.5, and 0.75 will be tested at wake Strouhal numbers of 0 and 0.3 in order to determine the effects for weak and strong injection rates. Measurements are taken in a low speed induced flow annular duct with jet Reynolds numbers of 2000 to 8000. Among the cases studied no discernable trend based on the diameter ratio is found, indicating that this effect is negligible in wake impact comparisons. The effect of wakes is consistent for both weak and strong injection with similar magnitude of wake impact for each diameter ratio tested. The existence or lack of dependence on diameter ratio allows for more purposeful comparisons among present and future investigations which use this method of producing unsteady wakes.
机译：近几十年来，人们对旋转尾流对燃气轮机薄膜冷却应用的影响越来越感兴趣，从而对这些不稳定现象进行了越来越多的研究。尾波主要从上游组件（例如过渡管壁，定子叶片和转子）脱落。研究表明，在非稳定流动区域，常规稳定研究中性能最佳的参数对于不稳定的应用可能不是最佳的。对亚音速流中的转子-定子相互作用进行建模的一种常用方法是使用辐条轮式尾波发生器，该发生器使用圆柱杆来产生速度损失和湍流强度的局部增加。在迄今为止发表的结果中，没有提到尾流杆与薄膜冷却孔直径比的潜在影响。在研究人员之间关于后缘厚度和边界层生长的影响存在分歧，导致公开文献中的直径比从0.5到5.6。该研究测量了直径比对2.375、4.75和9.5的三个直径比对绝热膜冷却效率的影响，以便确定对这个通常未知的参数的依赖。为了确定弱和强注入速率的影响，将在0和0.3的尾Strouhal数下测试0.25、0.5和0.75的吹塑比。在射流雷诺数为2000到8000的低速感应流环形管道中进行测量。在所研究的案例中，没有发现基于直径比的明显趋势，这表明在尾流冲击比较中这种影响可以忽略不计。对于每个测试的直径比，尾流的影响对于弱注入和强注入都是一致的，并且尾流冲击的大小相似。对直径比的存在与否的依赖允许在使用这种产生不稳定尾流的方法的当前和将来的研究之间进行更有目的的比较。

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