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Research Papers

Film Cooling From a Row of Holes Supplemented With Antivortex Holes

[+] Author and Article Information
Alok Dhungel, Yiping Lu, Wynn Phillips

Mechanical Engineering Department, Louisiana State University, Baton Rouge, LA 70803

Srinath V. Ekkad1

Mechanical Engineering, Virginia Tech, Blacksburg, VA 24060sekkad@vt.edu

James Heidmann

Turbomachinery and Heat Transfer Branch, NASA Glenn Research Center, Cleveland, OH 44135-3191

1

Corresponding author.

J. Turbomach 131(2), 021007 (Jan 22, 2009) (10 pages) doi:10.1115/1.2950059 History: Received June 11, 2007; Revised December 05, 2007; Published January 22, 2009

The primary focus of this paper is to study the film cooling performance for a row of cylindrical holes each supplemented with two symmetrical antivortex holes, which branch out from the main holes. The antivortex design was originally developed at NASA-Glenn Research Center by James Heidmann, coauthor of this paper. This “antivortex” design is unique in that it requires only easily machinable round holes, unlike shaped film cooling holes and other advanced concepts. The hole design is intended to counteract the detrimental vorticity associated with standard circular cross-section film cooling holes. The geometry and orientation of the antivortex holes greatly affect the cooling performance downstream, which is thoroughly investigated. By performing experiments at a single mainstream Reynolds number of 9683 based on the freestream velocity and film hole diameter at four different coolant-to-mainstream blowing ratios of 0.5, 1, 1.5, and 2 and using the transient IR thermography technique, detailed film cooling effectiveness and heat transfer coefficients are obtained simultaneously from a single test. When the antivortex holes are nearer the primary film cooling holes and are developing from the base of the primary holes, better film cooling is accomplished as compared to other antivortex hole orientations. When the antivortex holes are laid back in the upstream region, film cooling diminishes considerably. Although an enhancement in heat transfer coefficient is seen in cases with high film cooling effectiveness, the overall heat flux ratio as compared to standard cylindrical holes is much lower. Thus cases with antivortex holes placed near the main holes certainly show promising results.

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Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

Experimental set up

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Figure 2

Layout of mesh heater

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Figure 10

Effect of blowing ratio on overall heat flux ratio for different cases

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Figure 3

(a) Test plate geometry for base line case, (b) test plate geometry with shaped holes, and (c) test plate geometry with anti vortex holes

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Figure 4

(a) Generic orthographic views of the anti vortex configurations and (b) top view of the six cases

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Figure 5

Detailed film effectiveness distributions for all cases at different blowing ratios

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Figure 6

Detailed heat transfer coefficient distributions for all cases at different blowing ratios

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Figure 7

Effect of hole configuration on spanwise averaged film effectiveness distributions at each blowing ratio

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Figure 8

Effect of hole configuration on spanwise averaged heat transfer coefficient ratio distributions at each blowing ratio

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Figure 9

Effect of blowing ratio on (a) overall area-averaged film effectiveness and (b) heat transfer coefficient ratios for all cases

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