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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    Titel :

    Numerical Simulation of Film Cooling in Supersonic Flow


    Weitere Titelangaben:

    Notes Numerical Fluid Mech.


    Beteiligte:
    Adams, Nikolaus A. (Herausgeber:in) / Schröder, Wolfgang (Herausgeber:in) / Radespiel, Rolf (Herausgeber:in) / Haidn, Oskar J. (Herausgeber:in) / Sattelmayer, Thomas (Herausgeber:in) / Stemmer, Christian (Herausgeber:in) / Weigand, Bernhard (Herausgeber:in) / Peter, Johannes M. F. (Autor:in) / Kloker, Markus J. (Autor:in)


    Erscheinungsdatum :

    2020-10-27


    Format / Umfang :

    17 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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