Three-dimensional finite element models were generated and transferred into three-dimensional finite difference models to perform the transient thermal analyses on the first-stage nozzle and rotor blade of the Space Shuttle Main Engine high pressure fuel turbopump. STANCOOL was chosen to calculate heat transfer coefficients (HTCs) around airfoils, and endwall effects were included at the intersections of the airfoils and platforms for the steady-state boundary conditions. Free convection and forced convection due to rotation were also considered in hollow cores. Transient HTCs were calculated by taking ratios of the steady-state values based on the flow rates and the fluid properties calculated at each time slice. Results were presented in both transient plots and three-dimensional color contour isotherm plots. They were also converted into universal files to be used for finite element stress analyses.


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    Titel :

    3-D thermal analysis using finite difference technique with finite element model for improved design of components of rocket engine turbomachines for Space Shuttle Main Engine (SSME)


    Weitere Titelangaben:

    Dreidimensionale thermische Analyse mit Hilfe der Finite-Differenz-Technik in Verbindung mit einem Finite-Elemente-Modell zur Verbesserung der Konstruktion von Bauteilen der Raketen-Turbomotoren fuer den Hauptantrieb der Raumfaehre


    Beteiligte:
    Sohm, K.D. (Autor:in) / Ip, S.P. (Autor:in)

    Erschienen in:

    AIAA-Papers ; Jul ; 1-10


    Erscheinungsdatum :

    1988


    Format / Umfang :

    10 Seiten, 15 Bilder, 10 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch