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Heat transfer investigation in rotating smooth square U-duct with different wall-temperature ratios and channel orientations

机译:具有不同壁温比和通道方向的旋转光滑方形U型管的传热研究

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摘要

Effect of wall-temperature ratios (TR) and channel orientations (β) on heat transfer in rotating smooth square U-duct is experimentally investigated. The inlet Reynolds number and rotation number (Ro) range from 10,000 to 30,000 and 0 to 2.0, respectively. Three TR cases (0.08, 0.12, and 0.16) and two channel angles (0°,45°) are selected. The effect of TR on heat transfer distribution can be unified by considering the wall-to-bulk temperature ratio ((T_b/T_w)~n) which the exponent n varies from stationary to rotation. Compared with TR = 0.16, smaller TR case has larger critical Ro on the leading surface of the first pass and larger exceed-Ro of the second pass. Compared with β = 0° channel, β = 45° channel shows negative effect on heat transfer as Ro increases over the critical Ro. The channel orientation also enlarges the critical Ro on the leading surface of the first pass. The correlations between the critical Ro (Ro_c) and the location (X/D), including wall-temperature ratios (TR) and channel orientations (β), are developed into simple expression. The correlations demonstrate that the minimum heat transfer in the whole channel can be determined by the specified rotational states. And thus the correlations for minimum Nu/Nu_s ratio as a function of Ro(0 < Ro < 1.0) are developed for different wall-temperature ratios and channel orientations.
机译:实验研究了壁温比(TR)和通道方向(β)对旋转光滑方形U型管中传热的影响。入口雷诺数和旋转数(Ro)分别从10,000到30,000和0到2.0。选择了三种TR情况(0.08、0.12和0.16)和两个通道角度(0°,45°)。可以通过考虑指数n从固定到旋转变化的壁-体温度比((T_b / T_w)〜n)来统一TR对传热分布的影响。与TR = 0.16相比,较小的TR情况在第一遍的引导面上具有较大的临界Ro,而在第二遍的超出面具有较大的Ro。与β= 0°通道相比,β= 45°通道在Ro超过临界Ro时对传热产生负面影响。通道方向还扩大了第一遍前导表面上的临界Ro。临界Ro(Ro_c)与位置(X / D)之间的相关关系,包括壁温比(TR)和通道方向(β),已发展为简单的表达式。相关性表明,可以通过指定的旋转状态确定整个通道中的最小传热。因此,针对不同的壁温比和通道方向,建立了最小Nu / Nu_s比与Ro(0 <Ro <1.0)的关系。

著录项

  • 来源
  • 作者单位

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics & Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics & Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics & Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;

    R&D Center, Dept of Discipline Engineering, AVIC Commercial Aircraft Engine Co., Ltd., Shanghai 201108, China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Heat transfer; Rotating channel; Wall-temperature ratio; Channel orientation; Critical rotation number;

    机译:传播热量;旋转通道;壁温比;渠道定位;临界转速;

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