Research Papers: Energy Systems Analysis

Computational Fluid Dynamics Modeling Flow Field and Side-Wall Heat Transfer in Rectangular Rib-Roughened Passages

[+] Author and Article Information
Gongnan Xie

e-mail: xgn@nwpu.edu.cn

Weihong Zhang

Engineering Simulation and
Aerospace Computing (ESAC),
Northwestern Polytechnical University,
P.O. Box 552, 710072 Xi'an,
Shaanxi, China

Bengt Sunden

Department of Energy Sciences,
Lund University,
P.O. Box 118, SE-22100 Lund, Sweden
e-mail: bengt.sunden@energy.lth.se

1Corrresponding author.

Contributed by the Advanced Energy Systems Division of ASME for publication in the JOURNAL OF Energy Resources Technology. Manuscript received July 3, 2012; final manuscript received December 24, 2012; published online May 27, 2013. Assoc. Editor: Mansour Zenouzi.

J. Energy Resour. Technol 135(4), 042001 (May 27, 2013) (8 pages) Paper No: JERT-12-1155; doi: 10.1115/1.4023332 History: Received July 03, 2012; Revised December 24, 2012

In order to achieve higher thermal efficiency and power output, the gas turbine inlet temperature of gas turbine engine is continuously increased. However, the increasing temperature may exceed the melting point of the blade material. Rib turbulators are often used in the midsection of internal cooling ducts to augment the heat transfer from blade wall to the coolant. This study uses computational fluid dynamics (CFD) to investigate side-wall heat transfer of a rectangular passage with the leading/trailing walls being roughened by continuous or truncated ribs. The inlet Reynolds number is ranging from 12,000 to 60,000. The detailed three dimensional (3D) fluid flow and heat transfer over the side-wall are presented. The overall performances of ribbed passages are compared. It is suggested that the usage of truncated ribs is a suitable way to augment the side-wall heat transfer and improve the flow structure near the leading edge especially under the critical limitation of pressure drop.

Copyright © 2013 by ASME
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Fig. 1

Various cooling methods for a turbine blade

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Fig. 2

The rectangular duct with ribs (unit: mm)

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Fig. 3

Rib configurations

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Fig. 4

Centerline Nusselt number, Re = 8000

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Fig. 5

Grid of numerical model

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Fig. 6

Velocity contours at different planes, Re = 20,000

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Fig. 7

Temperature contours on the side-wall, Re = 20,000

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Fig. 8

Heat transfer and pressure drop

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Fig. 9

Normalized Nusselt number and friction factor

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Fig. 10

Centerline normalized Nusselt number

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Fig. 11

Streamwise direction of Nusselt number at different z/H, Re = 20,000

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Fig. 12

Thermal performance of both rib configurations

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Fig. 13

Heat transfer coefficient versus pumping power




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