A hot air anti-icing system of a gas turbine engine inlet is analyzed numerically. A three-dimensional potential flow code, which accounts for compressibility effects, is used to determine the flowfield in and around the inlet. A particle trajectory code is developed using a local linearization technique. The trajectory code is used to calculate local water impingement rates. Energy balances are performed on both the surface runback water and the metallic skin to determine their temperature distributions. A variety of test cases are considered in order to validate the various numerical components of the process as well as to demonstrate the procedure.


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    Titel :

    Thermal analysis of engine inlet anti-icing systems


    Weitere Titelangaben:

    Thermische Analyse der Enteisungssysteme in den Turbineneinlaessen


    Beteiligte:
    Al-Khalil, K.M. (Autor:in) / Keith, T.G. jun. (Autor:in) / Witt, K.J. de (Autor:in) / Nathman, J.K. (Autor:in) / Dietrich, D.A. (Autor:in)

    Erschienen in:

    AIAA-Papers ; Jan ; 1-12


    Erscheinungsdatum :

    1988


    Format / Umfang :

    12 Seiten, 27 Bilder, 1 Tabelle, 11 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Thermal analysis of engine inlet anti-icing systems

    KEITH, THEO G. / DEWITT, KENNETH J. / NATHMAN, JAMES K. et al. | AIAA | 1990


    Thermal analysis of engine inlet anti-icing systems

    KEITH, JR., THEO / DE WITT, KENNETH / NATHMAN, JAMES et al. | AIAA | 1989


    COMPOUND ENGINE ASSEMBLY WITH INLET LIP ANTI-ICING

    LAMARRE SYLVAIN / FONTAINE MIKE / JULIEN ANDRE et al. | Europäisches Patentamt | 2023

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