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Computational analysis of the influences of guide ribs/vanes on enhanced heat transfer of a turbine blade tip-wall

Xie, Gongnan; Zhang, Weihong and Sundén, Bengt LU (2012) In International Journal of Thermal Sciences 51. p.184-194
Abstract
Gas turbine blade tips encounter large heat load as they are exposed to the high temperature gas. A common way to cool the blade and its tip is to design a serpentine passage with 180-deg turns under the blade tip-cap inside the turbine blade. Improved internal convective cooling is therefore required to increase the blade tip lifetime. In this paper, turbulent fluid flow and heat transfer through seven two-pass channels with and without guide ribs or vanes have been investigated numerically using Computational Fluid Dynamics technique. The influences of placing six kinds of guide ribs/vanes in the turn regions on the tip-wall heat transfer enhancement and the overall pressure loss of the channels are analyzed. The guide ribs have a height... (More)
Gas turbine blade tips encounter large heat load as they are exposed to the high temperature gas. A common way to cool the blade and its tip is to design a serpentine passage with 180-deg turns under the blade tip-cap inside the turbine blade. Improved internal convective cooling is therefore required to increase the blade tip lifetime. In this paper, turbulent fluid flow and heat transfer through seven two-pass channels with and without guide ribs or vanes have been investigated numerically using Computational Fluid Dynamics technique. The influences of placing six kinds of guide ribs/vanes in the turn regions on the tip-wall heat transfer enhancement and the overall pressure loss of the channels are analyzed. The guide ribs have a height of 9% height of the channel while the guide vanes have a height identical to that of the channel. The inlet Reynolds numbers are ranging from 100,000 to 600,000. The detailed three-dimensional fluid flow and heat transfer over the tip-walls are presented. The overall performances of several two-pass channels are also evaluated and compared. It is found that the tip heat transfer coefficients of the channels with guide ribs/vanes are up to 65% higher than those of a channel without guide ribs/vanes, while the pressure loss might be reduced if the guide ribs/vanes are properly designed and located, otherwise the pressure loss is expected to be increased severely. It is suggested that the usage of proper guide ribs/vanes is a suitable way to augment the blade tip heat transfer and improve the flow structure, but is not the most effective way compared to the augmentation by surface modifications imposed on the tip-wall directly. (C) 2011 Elsevier Masson SAS. All rights reserved. (Less)
Please use this url to cite or link to this publication:
author
organization
publishing date
type
Contribution to journal
publication status
published
subject
keywords
Tip-wall, Guide ribs, Guide vanes, Heat transfer, Computation
in
International Journal of Thermal Sciences
volume
51
pages
184 - 194
publisher
Elsevier
external identifiers
  • wos:000297431100020
  • scopus:80054714206
ISSN
1290-0729
DOI
10.1016/j.ijthermalsci.2011.08.004
language
English
LU publication?
yes
id
2f63b3db-53b1-4e94-9329-16cba89abc68 (old id 2278928)
date added to LUP
2012-01-11 13:31:10
date last changed
2017-01-01 06:13:16
@article{2f63b3db-53b1-4e94-9329-16cba89abc68,
  abstract     = {Gas turbine blade tips encounter large heat load as they are exposed to the high temperature gas. A common way to cool the blade and its tip is to design a serpentine passage with 180-deg turns under the blade tip-cap inside the turbine blade. Improved internal convective cooling is therefore required to increase the blade tip lifetime. In this paper, turbulent fluid flow and heat transfer through seven two-pass channels with and without guide ribs or vanes have been investigated numerically using Computational Fluid Dynamics technique. The influences of placing six kinds of guide ribs/vanes in the turn regions on the tip-wall heat transfer enhancement and the overall pressure loss of the channels are analyzed. The guide ribs have a height of 9% height of the channel while the guide vanes have a height identical to that of the channel. The inlet Reynolds numbers are ranging from 100,000 to 600,000. The detailed three-dimensional fluid flow and heat transfer over the tip-walls are presented. The overall performances of several two-pass channels are also evaluated and compared. It is found that the tip heat transfer coefficients of the channels with guide ribs/vanes are up to 65% higher than those of a channel without guide ribs/vanes, while the pressure loss might be reduced if the guide ribs/vanes are properly designed and located, otherwise the pressure loss is expected to be increased severely. It is suggested that the usage of proper guide ribs/vanes is a suitable way to augment the blade tip heat transfer and improve the flow structure, but is not the most effective way compared to the augmentation by surface modifications imposed on the tip-wall directly. (C) 2011 Elsevier Masson SAS. All rights reserved.},
  author       = {Xie, Gongnan and Zhang, Weihong and Sundén, Bengt},
  issn         = {1290-0729},
  keyword      = {Tip-wall,Guide ribs,Guide vanes,Heat transfer,Computation},
  language     = {eng},
  pages        = {184--194},
  publisher    = {Elsevier},
  series       = {International Journal of Thermal Sciences},
  title        = {Computational analysis of the influences of guide ribs/vanes on enhanced heat transfer of a turbine blade tip-wall},
  url          = {http://dx.doi.org/10.1016/j.ijthermalsci.2011.08.004},
  volume       = {51},
  year         = {2012},
}