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首页> 外文会议>The 2001 ASME International Mechanical Engineering Congress and Exposition, 2001, Nov 11-16, 2001, New York, New York >Heat Transfer of a Chordwise-Oriented Internal Cooling Passage around a Turbine Airfoil
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Heat Transfer of a Chordwise-Oriented Internal Cooling Passage around a Turbine Airfoil

机译：涡轮翼型沿弦向的内部冷却通道的热传递

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摘要

An innovative design of closed-loop cooling system for a stator airfoil consists of a number of internal cooling passages wrapping around both pressure and suction sides of the airfoil. The cooling passages feature (1) jet impingement post a sharp 90-degree turn at the passage inlet, (2) tabulators on the outermost wall, and (3) a nearly 180-degree turn in the trailing edge. In addition, the passage has an irregular cross-section and varies throughout its entire length. A series of heat transfer tests have been performed at Re=17,000 ～ 61,000, compared to this tests which uses a new approach, so-called the hybrid liquid crystal technique. The magnitude of local heat transfer coefficient rises sharply in three regions. The first maximum occurs in the region subjected to direct jet impingement as the flow turns into the channel. Compounded with the inlet effect, this maximum, in fact, is the highest heat transfer coefficient over the entire passage. The second and third peaks, both are comparable in magnitude, locate near the trailing edge of the airfoil where the flow experiences a 180-degree turn and near the passage exit with a 90-degree turn. The average value of heat transfer coefficient over the entire passage is about 1.9～2.5 times higher than that with fully developed turbulent flow in a straight channel. This level of enhancement is comparable to that of the conventional rib-turbulators with a 90-degree angle-of-attack.
机译：定子机翼的闭环冷却系统的创新设计包括围绕机翼压力侧和吸力侧的许多内部冷却通道。冷却通道的特点是：（1）射流撞击在通道入口处急转90度；（2）最外壁的制表器；（3）后缘急转180度。另外，通道具有不规则的横截面并且在其整个长度上变化。与使用新方法的混合液晶技术进行的传热测试相比，在Re = 17,000〜61,000处进行了一系列传热测试。局部传热系数的幅度在三个区域急剧上升。当流量进入通道时，第一最大值出现在受到直接射流冲击的区域。实际上，与入口效应相结合，该最大值是整个通道中的最高传热系数。第二个和第三个峰值在大小上都相当，位于机翼的后缘附近，在该处气流经历了180度的转弯，而在通道出口附近则发生了90度的转弯。整个通道中的传热系数平均值比在直通道中充分发展的湍流时高约1.9〜2.5倍。这种增强水平可与具有90度攻角的传统肋骨湍流器相比。

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