Abstract The verification results are cited of 3D computational investigation of effectiveness of the film cooling for the vane leading edge of the C3X engine high pressure turbine with application of SST and S—A turbulence models, and calculation results are presented for used 1D empirical dependences and 2D calculation with modeling coolant injection within the bounds of two-dimensional boundary layer. The most satisfactory matching of calculation data with experimental ones is demonstrated in case of using S—A turbulence model in 3D calculations.


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    Title :

    Verification of the Film Cooling Calculations for Nozzle Vane Leading Edges in ANSYS CFX


    Contributors:

    Published in:

    Publication date :

    2019




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    Local classification TIB:    770/7040/8000
    BKL:    55.50 Luftfahrzeugtechnik



    Verification of the Film Cooling Calculations for Nozzle Vane Leading Edges in ANSYS CFX

    Gorelov, Yu. G. / Tyul’kov, K. V. / Anan’ev, V. V. et al. | Springer Verlag | 2019




    Design of a High Pressure Turbine Nozzle Guide Vane with Effective Film Cooling System on Leading Edge (AIAA 2016-0654)

    Kiyici, Firat / Aksu, Tekin / Uslu, Sitki | British Library Conference Proceedings | 2016