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Research Papers

Experimental and Numerical Investigation of Convective Heat Transfer in a Gas Turbine Can Combustor

[+] Author and Article Information
Sunil Patil, Santosh Abraham, Danesh Tafti, Srinath Ekkad

Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

Yong Kim, Partha Dutta, Hee-Koo Moon, Ram Srinivasan

 Solar Turbines, Incorporated, San Diego, CA 92101

www.minco.com.

J. Turbomach 133(1), 011028 (Sep 28, 2010) (7 pages) doi:10.1115/1.4001173 History: Received July 06, 2009; Revised November 08, 2009; Published September 28, 2010; Online September 28, 2010

Experiments and numerical computations are performed to investigate the convective heat transfer characteristics of a gas turbine can combustor under cold flow conditions in a Reynolds number range between 50,000 and 500,000 with a characteristic swirl number of 0.7. It is observed that the flow field in the combustor is characterized by an expanding swirling flow, which impinges on the liner wall close to the inlet of the combustor. The impinging shear layer is responsible for the peak location of heat transfer augmentation. It is observed that as Reynolds number increases from 50,000 to 500,000, the peak heat transfer augmentation ratio (compared with fully developed pipe flow) reduces from 10.5 to 2.75. This is attributed to the reduction in normalized turbulent kinetic energy in the impinging shear layer, which is strongly dependent on the swirl number that remains constant at 0.7 with Reynolds number. Additionally, the peak location does not change with Reynolds number since the flow structure in the combustor is also a function of the swirl number. The size of the corner recirculation zone near the combustor liner remains the same for all Reynolds numbers and hence the location of shear layer impingement and peak augmentation does not change.

Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Experimental setup (all dimensions are in centimeters)

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Figure 2

3D CAD model of swirler

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Figure 3

Viewports for an IR camera on combustor model wall

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Figure 4

Schematic of surface heater

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Figure 5

(a) Computational domain and (b) overall mesh view in flow nozzle (sector angle=18)

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Figure 6

(a) Boundary layer resolution near swirler vane and (b) near liner wall

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Figure 7

Detailed heat transfer distributions on the liner wall (left: swirler; right: exit)

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Figure 8

Comparison of numerical predictions using different turbulence models with experiments at Re=50,000

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Figure 9

Nusselt number augmentation for Re=50,000 and Re=80,000 along the liner wall

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Figure 10

Streamlines in combustor (Re=50,000)

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Figure 11

Contours of normalized axial velocity in meridional plane in combustor (Re=50,000)

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Figure 12

Contours of normalized turbulent kinetic energy in meridional plane in combustor (Re=50,000)

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Figure 13

Normalized axial velocity profiles for radial traverse

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Figure 14

Axial vorticity isocontour (value=1000) in combustor colored with axial velocity

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Figure 15

Effect of Reynolds number on liner wall heat transfer augmentation

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Figure 16

Variation in peak heat transfer augmentation ratio with Reynolds number

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Figure 17

Variation in normalized turbulent kinetic energy with Reynolds number near shear layer impingement on liner wall

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Figure 18

Streamlines in combustor for (a) Re=80,000 and (b) Re=500,000

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