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首页> 外文会议>ASME turbo expo: turbine technical conference and exposition >Trailing Edge Cooling of Gas Turbine Airfoil Using Blockages with Straight and Inclined Holes
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Trailing Edge Cooling of Gas Turbine Airfoil Using Blockages with Straight and Inclined Holes

机译：使用带有直孔和倾斜孔的堵塞物对燃气轮机翼型件进行后缘冷却

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This paper describes the detailed experimental studies of heat transfer enhancement and pressure loss characteristics internal cooling passages using single, double and triple blockages equipped with straight and inclined holes. The blockage consist of 7 holes with the diameter, D=6.35mm, which is 0.5 of the height of the channel. Three different hole inclination angles ranging from 0°, 15° and 30° from the horizontal plane are explored. The case with straight holes (0°) is considered as baseline case, while the cases with inclined holes are introduced to enhance heat transfer performance. The transient liquid crystal technique is employed to deduce the heat transfer coefficient on the internal cooling channel, while the pressure loss of the entire channel is measured using pressure taps connected to the digital manometer. Numerical analysis is later performed using ANSYS CFX, based on the shear stress turbulence (SST) model to provide detailed insights about the flow field in the channel, which explains the heat transfer phenomena caused by varying the hole inclination angle. The heat transfer performance of the blockages is higher than conventional configuration using vortex generators, i.e., pin-fins by approximately two folds, while accompanied by much higher pressure loss. The proposed inclined holes array exhibits more effective impingement effects resulted in a substantial cooling performance compared to the baseline case by approximately 50%. This design can be applicable to the trailing edge of gas turbine airfoils, which can provide high heat transfer rate and pressure loss from repeated significant area contractions.
机译：本文介绍了使用带有直孔和斜孔的单，双和三重堵塞对内部冷却通道进行传热增强和压力损失特性的详细实验研究。堵塞物由7个直径为D = 6.35mm的孔组成，直径为通道高度的0.5。研究了与水平面的0°，15°和30°范围内的三种不同的孔倾斜角。带有直孔（0°）的情况被认为是基准情况，而引入带有倾斜孔的情况是为了增强传热性能。采用瞬态液晶技术来推导内部冷却通道上的传热系数，而整个通道的压力损失则使用连接到数字压力计的压力抽头进行测量。随后，基于剪应力湍流（SST）模型，使用ANSYS CFX进行了数值分析，以提供有关通道中流场的详细见解，从而解释了因孔倾角变化而引起的传热现象。堵塞物的传热性能高于使用涡流发生器的常规构造，即针状翅片约两倍，同时伴随着更高的压力损失。所提出的倾斜孔阵列表现出更有效的碰撞效果，与基准情况相比，可提供显着的冷却性能，约为50％。该设计可适用于燃气涡轮机翼型的后缘，该后缘可提供高的传热速率和重复出现的大面积收缩而造成的压力损失。

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