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First Thermal and Fluids Engineering Summer Conference

ISSN: 2379-1748
ISBN: 978-1-56700-430-4

EFFECTS OF CURVATURE RADII AND ASPECT RATIOS ON COOLING CHANNELS HEAT TRANSFER FOR LIQUID ROCKET ENGINES

DOI: 10.1615/TFESC1.hte.012762
pages 1245-1268

Guang Chen
Department of Mechanical Engineering, Columbia University, NY 10027, USA

Mohammad H. N. Naraghi
Mechanical Engineering Department, Manhattan College Riverdale, New York

Pejman Akbari
Columbia University, Mechanical Engineering Department, New York, NY, 10027


KEY WORDS: Heat Transfer, Cooling Channels, Liquid Rocket Engine

Abstract

Coolant flow heat transfer characteristics in curved rectangular cooling channels are numerically modeled and studied. It is determined that the heat transfer coefficient varies differently on three surfaces of cooling channel. In this study, we demonstrated that the heat transfer enhances significantly on the outer surface of cooling channel while it was reduced on the inner surface as coolant enters the curved section. This process reverses as coolant exits the curve section of cooling channel. The three variables that are incorporated in the heat transfer coefficient correlations include dimensionless distance from entrance or exit of the curved section, the normalized radius of curvature and cooling channel aspect ratio. Finally new correlations are developed for developing and diminishing coolant flow heat transfer coefficient as the coolant flow enters and leaves curved section of cooling channels.

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