0
TECHNICAL PAPERS

Capturing Sudden Increase in Heat Transfer on the Suction Side of a Turbine Blade Using a Navier–Stokes Solver

[+] Author and Article Information
Faisal Rahman, Jan A. Visser, Reuben M. Morris

Department of Mechanical and Aeronautical Engineering, University of Pretoria, Lynwood 0002, Pretoria, South Africa

J. Turbomach 127(3), 552-556 (Jan 04, 2005) (5 pages) doi:10.1115/1.1928287 History: Received March 14, 2004; Revised January 04, 2005

The numerical modeling of heat transfer on the suction side of a cooled gas turbine blade is one of the more difficult problems in engineering. The main reason is believed to be the transition from laminar to turbulent flow and the inability of standard Navier–Stokes solvers to predict the transition. This paper proves that sudden changes in heat transfer on the suction side of a turbine blade can indeed also be caused by localized shocks disrupting the boundary layer. In contrast to transition, the position of these shocks and the effect of the shocks on the pressure distribution and heat transfer rate can be predicted to within an acceptable degree of accuracy using standard Navier–Stokes solvers. Two well-documented case studies from the literature are used to prove that the pressure distribution around the profile can be predicted accurately when compared to experimental data. At the same time this method can be used to capture sudden changes in heat transfer rate caused by localized shocks. The conclusion from this study is that localized shock waves close to the suction side surface of a turbine blade can have the same effect on the heat transfer rate to the blade as transition.

FIGURES IN THIS ARTICLE
<>
Copyright © 2005 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Boundary conditions

Grahic Jump Location
Figure 2

Computational grid

Grahic Jump Location
Figure 3

Heat transfer coefficient on the blade surface

Grahic Jump Location
Figure 4

Mach number contours

Grahic Jump Location
Figure 5

General outline of MarkII blade

Grahic Jump Location
Figure 12

Temperature distribution as calculated by Bohn (5)

Grahic Jump Location
Figure 11

Simulated temperature distribution through the blade

Grahic Jump Location
Figure 10

Temperature distribution: Realizablek-ε model, enhanced wall treatment

Grahic Jump Location
Figure 9

Contours of Mach number

Grahic Jump Location
Figure 8

Pressure distribution: Realizablek-ε model, enhanced wall treatment

Grahic Jump Location
Figure 7

Computational grid in the vicinity of cooling hole 7

Grahic Jump Location
Figure 6

Computational grid

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