Unsteady Effects on Trailing Edge Cooling-Reference-Cited by-同舟云学术

Unsteady Effects on Trailing Edge Cooling

Published:2005-03-30 Issue:4 Volume:127 Page:388-392
ISSN:0022-1481
Container-title:Journal of Heat Transfer
language:en
Short-container-title:

Author:

Medic G.¹,Durbin P. A.¹

Affiliation:

1. Mechanical Engineering Department, Stanford University, Stanford, CA 94305-3030

Abstract

It is shown how natural and forced unsteadiness play a major role in turbine blade trailing edge cooling flows. Reynolds averaged simulations are presented for a surface jet in coflow, resembling the geometry of the pressure side breakout on a turbine blade. Steady computations show very effective cooling; however, when natural—or even moreso, forced—unsteadiness is allowed, the adiabatic effectiveness decreases substantially. Streamwise vortices in the mean flow are found to be the cause of the increased heat transfer.

Publisher

ASME International

Subject

Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics,General Materials Science

Link

http://asmedigitalcollection.asme.org/heattransfer/article-pdf/127/4/388/5641834/388_1.pdf

Reference6 articles.

1. Holloway, S. D., Leylek, J. H., and Buck, F. A., 2002, “Pressure-Side Bleed Film Cooling: Part I, Steady Framework for Experimental and Computational Results,” ASME Turbo Expo 2002; papers GT-2002-30471.

2. Iaccarino, G., Ooi, A., Durbin, P. A., and Behnia, M., 2003, “Reynolds Averaged Simulation of Unsteady Separated Flow,” Int. J. Heat Mass Transfer, 24, pp. 147–156.

3. Holloway, S. D., Leylek, J. H., and Buck, F. A., 2002, “Pressure-Side Bleed Film Cooling: Part 2, Unsteady Framework for Experimental and Computational Results,” ASME Turbo Expo 2002, papers GT-2002-30472.

4. Rigby, D. L., and Bunker, R. S., 2002, “Heat Transfer in a Complex Trailing Edge Passage for a High Pressure Turbine Blade,” NASA/CR 2002-211701.

5. Martini, P., and Shultz, A., 2004, “Experimental and Numerical Investigation of Trailing Edge Film Cooling by Circular Coolant Wall Jets Ejected From a Slot With Internal Rib Arrays,” ASME J. Turbomach., 126, pp. 229–236.

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