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首页> 外文会议>ASME turbine blade tip technical symposium 2013 : Turbine blade tip steady and unsteady aerodynamics ... >MEASUREMENT OF BLADE TIP HEAT TRANSFER AND LEAKAGE FLOW IN A TURBINE CASCADE WITH A MULTI-CAVITY SQUEALER TIP
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MEASUREMENT OF BLADE TIP HEAT TRANSFER AND LEAKAGE FLOW IN A TURBINE CASCADE WITH A MULTI-CAVITY SQUEALER TIP

机译：带有多腔防风罩的涡轮机叶栅中叶尖传热和泄漏流的测量

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摘要

Tip leakage flow induces high heat transfer to the blade tip and causes significant aerodynamic losses. In this paper, we propose a multi-cavity squealer tip with an additional rib in the squealer cavity. Our study investigated the effects of the rib location and shape on the blade tip heat transfer and the total pressure loss. Experiments were performed in a five-bladed linear cascade using a low speed wind tunnel. The blade chord, pitch, and span length were 126mm, 102.7mm, and 160mm, respectively. The Reynolds number, based on the blade chord and cascade exit velocity, was 2.44×10~5, and a tip clearance of 1.25% of the blade span was considered. The additional rib was installed in the squealer tip cavity near the leading edge, the mid-chord, and the training edge, respectively. The shape of the rib was also varied from rectangular to triangular in order to minimize the rib surface area exposed to the hot gas. The secondary flow and total pressure loss were measured using a seven-hole probe at one-chord downstream of the blade trailing edge, and the heat transfer coefficient distributions were measured by utilizing the hue-detection based transient liquid crystal technique. Flow measurement results indicated that the proposed multi-cavity tip reduced the total pressure loss. The blade tip heat transfer measurement results showed that the proposed multi-cavity tip was able to reduce the maximum heat transfer region near the cavity floor near the leading edge, but the heat transfer on the second cavity floor increased due to the leakage flow reattachment.
机译：尖端泄漏流引起向叶片尖端的高热传递，并导致明显的空气动力学损失。在本文中，我们提出了一种多腔式squealer笔尖，在squealer腔中有一个附加肋。我们的研究调查了肋骨位置和形状对叶片尖端传热和总压力损失的影响。使用低速风洞以五叶片线性叶栅进行实验。叶片弦长，螺距和跨度长度分别为126mm，102.7mm和160mm。根据叶片弦长和叶栅出口速度，雷诺数为2.44×10〜5，叶尖间隙为叶片跨度的1.25％。附加的肋骨分别安装在前缘，中弦和训练边缘附近的尖叫器顶端腔中。肋的形状也从矩形变为三角形，以使暴露于热气体的肋表面积最小。使用七孔探针在叶片后缘的一弦下游测量二次流量和总压力损失，并利用基于色相检测的瞬态液晶技术测量传热系数分布。流量测量结果表明，所建议的多腔头可减少总压力损失。叶片尖端传热测量结果表明，所提出的多腔尖端能够减小靠近前缘的空腔底部附近的最大传热区域，但由于泄漏流的重新附着，第二空腔底部的传热增加。

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