Numerical Simulation on Flow and Heat Transfer in a Square Channel with Three-Dimensional Turbulator

被引：0
|
作者：
Guo T. [1 ]
Zhu H.-R. [1 ]
Chen J. [1 ]
Han Z.-Y. [1 ]
机构：
[1] School of Power and Energy, Northwestern Polytechnical University, Xi'an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2018年 / 39卷 / 11期
关键词：
Flow character; Heat transfer character; Numerical simulation; Three-dimension turbulator;
D O I：
10.13675/j.cnki.tjjs.2018.11.014
中图分类号：
学科分类号：
摘要：
In the internal cooling channels of turbine blade, the turbulators are usually employed to enhance the heat transfer and take away the heat conducted into the blade walls, therefore protect the blade. A kind of three dimension turbulaor is investigated in a square duct. The effects of the flow and structure parameters on the flow and heat transfer characters are studied. The height of the turbulator is 1/8 of the channel equivalent diameter. The Reynolds number is changed from 1.5×10 4 to 8.0×10 4 . The pitches between turbulators in the flow direction are 3~10 times of the turbulator's height. The results show that the change of the Reynolds number only affects the heat transfer intensity, and does not affect the heat transfer distribution character. The aligned arrangement of turbulator may cause higher heat transfer enhancement than the staggered arrangement. With the increase of pitch between the turbulators, the average Nusselt number ratio and the flow resistance coefficient ratio of the channel are decreasing. This decreasing trend slows down when the pitch is greater than 8 times of turbulator's height. The best heat transfer enhancement can be achieved when the front angle of turbulators is about 80°. © 2018, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：2522 / 2530
页数：8
相关论文
共 12 条
  • [1] Zhu L.-Y., Xu G.-Q., Influence of Turbine Cooling Technology on Aero-Engine Performance, Journal of Propulsion Technology, 35, 6, pp. 796-798, (2014)
  • [2] Chanteloup D., Juaneda Y., Bolcs A., Combined 3D Flow and Heat Transfer Measurements in a 2-Pass Internal Coolant Passage of Gas Turbine Airfoils
  • [3] Han J.C., Heat Transfer and Friction in Channels with Two Opposite Rib-Roughened Walls, Journal of Heat Transfer, 106, 4, pp. 774-781, (1984)
  • [4] Han J.C., Heat Transfer and Friction Characteristics in Rectangular Channels with Rib Turbulators, Journal of Heat Transfer, 110, 2, pp. 321-328, (1988)
  • [5] Ekkad S.V., Han J.C., Detailed Heat Transfer Distributions in Two-Pass Square Channels with Rib Turbulators, International Journal of Heat & Mass Transfer, 40, 11, pp. 2525-2537, (1997)
  • [6] Han J.C., Dutta S., Ekkad S.V., Gas Turbine Heat Transfer and Cooling Technology, (2000)
  • [7] Zhang Z.-W., Zhu H.-R., Wang Z.-W., Et al., Influence of Bleed Hole Location on Heat Transfer Inrectangular Channels with Ribs, Journal of Propulsion Technology, 32, 4, pp. 582-585, (2011)
  • [8] Guo T., Zhu H.-R., Li G.-C., Et al., Flow in Channel with Rib Turbulators and Double-Row Bleed Holes, Journal of Propulsion Technology, 28, 4, pp. 400-402, (2007)
  • [9] Rongguang J., Saidi A., Sunden B., Heat Transfer Enhancement in Square Ducts with V-Shaped Ribs, Journal of Turbomachinery, 125, 4, pp. 469-476, (2002)
  • [10] Ozceyhan V., Gunes S., Heat Transfer Enhancement in a Tube Using Triangular Ribs
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