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Augmentation of Stagnation Region Heat Transfer Due to Turbulence from a DLN Can CombustorHeat 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 NO(x), 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%, 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% and was about 14% higher than predicted by a previously developed correlation for isotropic grid-generated turbulence.
Document ID
20010061448
Acquisition Source
Glenn Research Center
Document Type
Reprint (Version printed in journal)
Authors
VanFossen, G. James
(NASA Glenn Research Center Cleveland, OH United States)
Bunker, Ronald S.
(General Electric Co. Schenectady, NY United States)
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Publication Information
Publication: Transactions of the American Society of Mechanical Engineers
Publisher: American Society of Mechanical Engineers
Volume: 123
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
Paper-2000GT215
Meeting Information
Meeting: 45th International Gas Turbine and Aeroengine Congress and Exhibition
Location: Munich
Country: Germany
Start Date: May 8, 2000
End Date: May 11, 2000
Distribution Limits
Public
Copyright
Other

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