0
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.

FIGURES IN THIS ARTICLE
<>
Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 4

Centerline Nusselt number, Re = 8000

Grahic Jump Location
Fig. 3

Rib configurations

Grahic Jump Location
Fig. 2

The rectangular duct with ribs (unit: mm)

Grahic Jump Location
Fig. 1

Various cooling methods for a turbine blade

Grahic Jump Location
Fig. 8

Heat transfer and pressure drop

Grahic Jump Location
Fig. 9

Normalized Nusselt number and friction factor

Grahic Jump Location
Fig. 10

Centerline normalized Nusselt number

Grahic Jump Location
Fig. 11

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

Grahic Jump Location
Fig. 5

Grid of numerical model

Grahic Jump Location
Fig. 6

Velocity contours at different planes, Re = 20,000

Grahic Jump Location
Fig. 7

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

Grahic Jump Location
Fig. 12

Thermal performance of both rib configurations

Grahic Jump Location
Fig. 13

Heat transfer coefficient versus pumping power

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In