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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    Title :

    Thermal analysis of engine inlet anti-icing systems


    Additional title:

    Thermische Analyse der Enteisungssysteme in den Turbineneinlaessen


    Contributors:

    Published in:

    AIAA-Papers ; Jan ; 1-12


    Publication date :

    1988


    Size :

    12 Seiten, 27 Bilder, 1 Tabelle, 11 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Thermal analysis of engine inlet anti-icing systems

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


    Thermal analysis of engine inlet anti-icing systems

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


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