Heat transfer measurements have been made in the stagnation region of a flat plate with a circular leading edge. Electrically heated aluminum strips placed symmetrically about the leading edge stagnation region were used to measure spanwise-averaged heat transfer coefficients. The maximum Reynolds number obtained, based on leading edge diameter, was about 100,000. The model was immersed in the flow field downstream of an approximately half-scale model of a can-type combustor from a low ground-based power-generating turbine. The tests were conducted with room temperature air; no fuel was added. Room air flowed into the combustor through six vane-type fuel/air swirlers. The combustor can contained no dilution holes. The fuel/air swirlers all swirled the incoming airflow in a counterclockwise direction (facing downstream). A five-hole probe flow field survey in the plane of the model stagnation point showed the flow was one big vortex with flow angles up to 36 deg at the outer edges of the rectangular test section. Hot-wire measurements showed test section flow had very high levels of turbulence, around 28.5 percent, and had a relatively large axial-length scale-to-leading edge diameter ratio of 0.5. X-wire measurements showed the turbulence to be nearly isotropic. Stagnation heat transfer augmentation over laminar levels was around 77 percent and was about 14 percent higher than predicted by a previously developed correlation for isotropic grid-generated turbulence.
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January 2001
Technical Papers
Augmentation of Stagnation Region Heat Transfer Due to Turbulence From a DLN Can Combustor
G. James Van Fossen,
G. James Van Fossen
NASA Glenn Research Center, Cleveland, OH 44135
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Ronald S. Bunker
Ronald S. Bunker
General Electric, Schenectady, NY 12309
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G. James Van Fossen
NASA Glenn Research Center, Cleveland, OH 44135
Ronald S. Bunker
General Electric, Schenectady, NY 12309
Contributed by the International Gas Turbine Institute and presented at the 45th International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8–11, 2000. Manuscript received by the International Gas Turbine Institute February 2000. Paper No. 2000-GT-215. Review Chair: D. Ballal.
J. Turbomach. Jan 2001, 123(1): 140-146 (7 pages)
Published Online: February 1, 2000
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Received:
February 1, 2000
Citation
Van Fossen, G. J., and Bunker, R. S. (February 1, 2000). "Augmentation of Stagnation Region Heat Transfer Due to Turbulence From a DLN Can Combustor ." ASME. J. Turbomach. January 2001; 123(1): 140–146. https://doi.org/10.1115/1.1330270
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