Three-dimensional Reynolds-averaged Navier-Stokes equations are applied to further explore steam vortex cooling mechanism in gas turbine blade leading edge. Grid independence analysis and turbulence model validation are carried out to determine the proper grid dimension and turbulence model for simulations. Influences of Reynolds number and temperature ratio on steam vortex cooling flow and heat transfer behavior for the blade leading edge are investigated. Heat transfer and friction correlations for steam vortex cooling are achieved on the basis of numerical data. Results show that radial convection is generated due to violent rotational motion and uneven density distribution, contributing to heat transfer enhancement. For the sake of increasing steam velocity, the obvious increase in heat transfer intensity and decrease in friction coefficient are observed with the increasing Reynolds number. When the temperature ratio increases, the heat transfer intensity decreases slightly and the friction coefficient decreases significantly. The thermal performance increases with the increasing Reynolds number and the decreasing temperature ratio. Compared with calculating results, the heat transfer and friction correlations can predict steam vortex cooling characteristics accurately.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge




    Publication date :

    2016



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    52.50 Energietechnik: Allgemeines / 52.30 Strömungskraftmaschinen, Turbomaschinen / 52.30 / 52.50
    Local classification TIB:    275/5345/5365/5500



    Stagnation Region Gas Film Cooling for Turbine Blade Leading-Edge Applications

    D.W. Luckey / D.K. Winstanley / G.J. Hanus et al. | AIAA | 1977


    Stagnation region gas film cooling for turbine blade leading edge applications

    LUCKEY, D. / WINSTANLEY, D. / HANUS, G. et al. | AIAA | 1976


    Numerical Study of Swirl Cooling in a Turbine Blade Leading-Edge Model

    Liu, Zhao / Li, Jun / Feng, Zhenping | AIAA | 2015



    Heat transfer enhancement in combined cooling of the turbine blade leading edge

    Shchukin, A. V. / Il’inkov, A. V. / Dezider’ev, S. G. et al. | Springer Verlag | 2013