Numerical Simulation of Film Cooling in Supersonic Flow

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Numerical Simulation of Film Cooling in Supersonic Flow

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Peter, Johannes M. F. / Kloker, Markus J.

High-order direct numerical simulations of film cooling by tangentially blowing cool helium at supersonic speeds into a hot turbulent boundary-layer flow of steam (gaseous H₂O) at a free stream Mach number of 3.3 are presented. The stagnation temperature of the hot gas is much larger than that of the coolant flow, which is injected from a vertical slot of height s in a backward-facing step. The influence of the coolant mass flow rate is investigated by varying the blowing ratio F or the injection height s at kept cooling-gas temperature and Mach number. A variation of the coolant Mach number shows no significant influence. In the canonical baseline cases all walls are treated as adiabatic, and the investigation of a strongly cooled wall up to the blowing position, resembling regenerative wall cooling present in a rocket engine, shows a strong influence on the flow field. No significant influence of the lip thickness on the cooling performance is found. Cooling correlations are examined, and a cooling-effectiveness comparison between tangential and wall-normal blowing is performed.

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Title :

Numerical Simulation of Film Cooling in Supersonic Flow

Additional title:

Notes Numerical Fluid Mech.

Contributors:

Adams, Nikolaus A. (editor) / Schröder, Wolfgang (editor) / Radespiel, Rolf (editor) / Haidn, Oskar J. (editor) / Sattelmayer, Thomas (editor) / Stemmer, Christian (editor) / Weigand, Bernhard (editor) / Peter, Johannes M. F. (author) / Kloker, Markus J. (author)

Published in:

Future Space-Transport-System Components under High Thermal and Mechanical Loads ; Chapter : 5 ; 79-95

Notes on Numerical Fluid Mechanics and Multidisciplinary Design ; 146

Publication date :

2020-10-27

Size :

17 pages

ISBN :

978-3-030-53847-7 , 978-3-030-53846-0

ISSN :

1860-0824 , 1612-2909

DOI :