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Turbine Vane Endwall Film Cooling Effectiveness of Different Purge Slot Configurations in a Linear Cascade

机译:线性叶栅中不同吹扫槽配置的涡轮叶片端壁膜冷却效率

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This study is concerned with the film cooling effectiveness of the flow issuing from the gap between the nozzle guide vane (NGV) and the transition duct on the NGV endwall, i.e., the purge slot. Different slot widths, positions, and injection angles were examined in order to represent changes due to thermal expansion as well as design modifications. Apart from these geometric variations, different blowing ratios (BRs) and density ratios (DRs) were realized to investigate the effects of the interaction between secondary flow and film cooling effectiveness. The experimental tests were performed in a linear scale-l cascade equipped with four highly loaded turbine vanes at the Institute of Fluid Mechanics and Fluid Machinery of the University of Kaiserslautern. The mainstream flow parameters were, with a Reynolds number of 300,000 and a Mach number (outlet) of 0.6, set to meet real engine conditions. By using various flow conditioners, periodic flow was obtained in the region of interest (ROI). The adiabatic film cooling effectiveness was determined using the pressure sensitive paint (PSP) technique. In this context, nitrogen and carbon dioxide were used as tracer gases realizing two different density ratios DR = 1.0 and 1.6. The investigation was conducted for a broad range of blowing ratios with 0.25 ≤ BR ≤ 1.50. In combination with 10 geometry variations and the aforementioned blowing and density ratio variations, 100 single operating points were investigated. For a better understanding of the coolant distribution, the secondary flows on the endwall were visualized by oil dye. The measurement results will be discussed based on the area! distribution of film cooling effectiveness, its lateral spanwise, as well as its area average. The results will provide a better insight into various parametric effects of gap variations on turbine vane endwall film cooling performance—notably under realistic engine conditions.
机译:这项研究涉及从喷嘴导流叶片(NGV)和NGV端壁上的过渡管道(即吹扫槽)之间的间隙发出的流动的薄膜冷却效果。检查了不同的缝隙宽度,位置和注入角度,以表示由于热膨胀和设计修改引起的变化。除了这些几何变化之外,还实现了不同的吹塑比(BRs)和密度比(DRs),以研究二次流与薄膜冷却效率之间相互作用的影响。实验测试是在Kaiserslautern大学流体力学和流体机械研究所的配备有四个高负荷涡轮叶片的线性1级线性叶栅中进行的。主流流量参数设定为满足实际发动机条件,雷诺数为300,000,马赫数(出口)为0.6。通过使用各种流量调节器,可以在目标区域(ROI)中获得周期性流量。绝热膜的冷却效率是使用压敏涂料(PSP)技术确定的。在本文中,使用氮气和二氧化碳作为示踪气体,实现了两种不同的密度比DR = 1.0和1.6。研究范围是0.25≤BR≤1.50的各种吹炼比。结合10种几何形状变化以及上述吹塑比和密度比变化,研究了100个单个工作点。为了更好地了解冷却液的分布,使用油性染料可视化了端壁上的二次流。测量结果将根据面积进行讨论!薄膜冷却效率的分布,其横向跨度及其平均面积。结果将提供对间隙变化对涡轮叶片端壁薄膜冷却性能的各种参数影响的更好理解,尤其是在实际发动机条件下。

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