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首页> 外文会议>ASME turbo expo >Mist/air Cooling in a Two-Pass Rectangular Rotating Channel with 45-deg Angled Rib Turbulators
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Mist/air Cooling in a Two-Pass Rectangular Rotating Channel with 45-deg Angled Rib Turbulators

机译：双通矩形旋转通道中的雾/空气冷却，带有45°角肋肋湍流器

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摘要

Increasing the turbine inlet temperature can increase the gas turbine cycle efficiency. In order to increase the turbine inlet temperature significantly, an advanced cooling system has to be essentially developed. Injection of mist to the coolant fluid is considered a promising technique to protect the hot components such as combustor liners, combustor transition pieces, and turbine vanes and blades. A series of experiments conducted in the past proved the success of mist cooling technology in the laboratory environment. Favorable results from the numerical simulation further encourage continuous exploration of employing mist-cooling technology in the actual gas turbine working environment in various applications. The present study focuses on applying mist cooling to the rotating mist/air internal cooling passage with rib turbulators using numerical simulation. In the first part, the computational fluid dynamics (CFD) models of smooth and ribbed channels without mist and rotation are validated with the experimental results available in literature. The agreement between the predicted and experimental values in the lower Reynolds number (Re) range is within 3% deviation, and, at higher Re range, the deviation is about 10%. For the smooth channel, the agreement with experimental result is good for the entire range of Re values. In the second part, the rotational effect on the smooth and ribbed channels is predicted and analyzed. In the last part, the mist cooling enhancement on the ribbed channel with rotation is simulated. The secondary flows created due to channel bend and rotation are specifically analyzed. The results show that the mist cooling enhancement is about 30% at the trailing surface and about 20% at the leading surface of the first passage with 2% mist injection. In the second passage, 20% enhancement is predicted for both the surfaces.
机译：增加涡轮机入口温度可以提高燃气轮机循环效率。为了显着增加涡轮机入口温度，必须基本上开发先进的冷却系统。将雾注入冷却剂流体被认为是一种有希望的技术，以保护诸如燃烧器衬里，燃烧器过渡件和涡轮机叶片和叶片的热部件。在过去进行的一系列实验证明了实验室环境中的雾气冷却技术的成功。来自数值模拟的有利结果进一步促进了在各种应用中采用实际燃气轮机工作环境中使用雾气冷却技术的持续探索。本研究专注于利用数值模拟将雾气冷却与肋湍流器施加到旋转雾/空气内部冷却通道。在第一部分中，使用文献中的实验结果验证了没有雾和旋转的光滑和肋道通道的计算流体动力学（CFD）模型。较低雷诺数（RE）范围内预测和实验值之间的协议在3％范围内，并且在较高的RE范围内，偏差约为10％。对于平滑通道，与实验结果的协议适用于整个RE值范围。在第二部分中，预测并分析了对光滑和肋网通道的旋转效应。在最后一部分中，模拟了具有旋转的肋沟道上的雾气冷却增强。专门分析由于信道弯曲和旋转而产生的二次流动。结果表明，在尾部表面的雾气冷却增强约为30％，在第一通道的前表面处具有约20％，具有2％的雾注射。在第二段中，对两个表面预测20％增强。

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