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Research Papers

Study of Flow and Convective Heat Transfer in a Simulated Scaled Up Low Emission Annular Combustor

[+] Author and Article Information
Sunil Patil, Teddy Sedalor, Danesh Tafti, Srinath Ekkad

Mechanical Engineering Department,  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

J. Thermal Sci. Eng. Appl 3(3), 031010 (Aug 12, 2011) (8 pages) doi:10.1115/1.4004531 History: Received November 03, 2010; Revised April 26, 2011; Published August 12, 2011; Online August 12, 2011

Modern dry low emissions (DLE) combustors are characterized by highly swirling and expanding flows that makes the convective heat load on the gas side difficult to predict and estimate. A coupled experimental–numerical study of swirling flow inside a DLE annular combustor model is used to determine the distribution of heat transfer on the liner walls. Three different Reynolds numbers are investigated in the range of 210,000–840,000 with a characteristic swirl number of 0.98. The maximum heat transfer coefficient enhancement ratio decreased from 6 to 3.6 as the flow Reynolds number increased from 210,000 to 840,000. This is attributed to a reduction in the normalized turbulent kinetic energy in the impinging shear layer, which is strongly dependent on the swirl number that remains constant at 0.98 for the Reynolds number range investigated. The location of peak heat transfer did not change with the increase in Reynolds number since the flow structures in the combustors did not change with Reynolds number. Results also showed that the heat transfer distributions in the annulus have slightly different characteristics for the concave and convex walls. A modified swirl number accounting for the step expansion ratio is defined to facilitate comparison between the heat transfer characteristics in the annular combustor with previous work in a can combustor. A higher modified swirl number in the annular combustor resulted in higher heat transfer augmentation and a slower decay with Reynolds number.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematics and images of test setup showing swirler placement

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Figure 2

Test section configuration with position of three swirlers

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Figure 3

Computational domain consisting swirl nozzle and periodic segment of annular combustor

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Figure 4

Computational grid details: (a) mesh on the swirler vanes, (b) mesh in the passage between the two vanes, and (c) head on view of overall mesh in the swirler and combustor

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Figure 5

2D measured wall temperature and heat transfer coefficient (W/(m2 K)) on the convex liner wall at Re = 420,000

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Figure 6

2D measured wall temperature and heat transfer coefficient (W/(m2 K)) on the concave liner wall at Re = 420,000

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Figure 7

Comparison of convex and concave surface heat transfer coefficient (W/(m2 K)) along the combustor liner wall (experimental, Re = 420,000)

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Figure 8

Nusselt number augmentation on (a) concave liner wall and (b) convex liner wall

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Figure 9

Streamline patterns in the azimuthal plane in the computational domain (Re = 420,000)

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Figure 10

Contours of (a) normalized axial velocity and (b) normalized turbulent kinetic energy in the azimuthal plane in the computational domain (Re = 420,000)

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Figure 11

Change in normalized turbulent kinetic energy with increase in Reynolds number in the shear layer near the peak heat transfer location

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Figure 12

Corner recirculation region in the annular combustor section immediately downstream of the swirl nozzle for (a) Reynolds number 210,000 and (b) Reynolds number 420,000

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Figure 13

Generic representation of swirler–combustor configuration

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Figure 14

Variation of peak heat transfer augmentation with Reynolds number for can and annular combustor

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