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Local heat transfer for finned-tube heat exchangers using oval tubes

机译:使用椭圆形管的翅片管热交换器的局部传热

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This paper presents the results of an experimental study of forced convection heat transfer in a narrow rectangular duct fitted convection heat transfer in a narow rectangular duct fitted with either a cirular tube or an eelliptical tube in cross-flow. The duct was designed to simulate a single passage in a fin-tube heat exchanger. Heat transfer measurements were obtained using a transient technique in which a heated airflow is suddennly introduced to the test section. High-resolution local fin-surface temperature distributions were obtained at several times after initiation of the transient using an imaging infrared camera. Corresponding local fin-surface heat transfer coefficient distributions were then calculated from a locally applied one-dimensional semi-infinite inverse heat condition model. Heat transfer results were obtained over an airflow rate ranging f rom 1.56 x 10~(-3) to 15.6 x 10~(-3) kg/s. These flow rates correspond to a duct height Reynolds number range of 630 - 6300 with a duct height of 1.106 cm and a duct width-to-height ratio, W/H, of 11.25. The test cylinder was sized such that the diameter-to-duct height ratio, D/H is t. The elliptical tube had an aspect ratio of 3:1 and a/H equal to 4.33. Results presented in this paper reveal visual and quantitative details of local finsurface heat transfer distributions in the vicinity of circular and oval tubes and their relationship to the complex horseshoe vortex system that forms in the flow stagnation region. Fin surface stagnation-region Nusselt numbers are shown to be proportional to the square-root of Reynolds number.
机译:本文介绍了在狭窄的矩形管道中强制对流传热的实验研究结果,在狭窄的矩形管道中对流传热在装有横流的圆管或椭圆管的纳罗矩形管道中进行。该管道设计为模拟翅片管热交换器中的单通道。使用瞬态技术获得传热测量结果,其中突然将热气流引入测试部分。使用成像红外摄像机在瞬变开始后的数次获得高分辨率的局部鳍片表面温度分布。然后从局部应用的一维半无限逆热条件模型中计算出相应的局部鳍片表面传热系数分布。在1.56 x 10〜(-3)kg / s至15.6 x 10〜(-3)kg / s的气流速率下获得了传热结果。这些流速对应于630-6300的管道高度雷诺数范围,管道高度为1.106厘米,管道宽高比W / H为11.25。确定测试圆柱体的尺寸,以使直径与管道的高度比D / H为t。椭圆管的纵横比为3:1,a / H等于4.33。本文介绍的结果揭示了圆形和椭圆形管附近局部翅片表面传热分布的视觉和定量细节,以及它们与在流动停滞区域中形成的复杂马蹄涡流系统的关系。鳍表面停滞区域的Nusselt数与雷诺数的平方根成正比。

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