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Start date: 2020Subject: search.filters.subject.Film cooling

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    Numerical Solutions of Heat Convection Problems in Film Cooling Flow Over Adiabatic and Diabatic Flat Plates
    (2026-03-06)
    Jeatrakul, Karn
    ;
    Prapamonthon, Prasert
    ;
    Wongsatanawarid, Atikorn
    ;
    Wang, Yeteng
    ;
    Hao, Zhanzhou
    This paper presents numerical solutions for film cooling flow over a flat plate subjected to heat convection problems, namely (1) adiabatic, and (2) diabatic plates with constant heat fluxes of 500 and 1000 W/m<sup>2</sup>. The governing equations and realizable k-ε turbulence model are solved to provide numerical solutions in terms of film effectiveness for the adiabatic case, and dimensionless temperature and Nusselt number for the diabatic case. Numerical solutions are carried out at two film hole angles i.e. α = 25° and 35° and two blowing ratios i.e. BR = 0.3 and 0.6. The numerical solutions indicate that the smaller angle and lower blowing ratio can provide better effective cooling on the flat plate for both problem conditions. In addition, the strong influence of the blowing ratio on the film cooling flow is observed. When the heat flux is included, the Nusselt number increases in spanwise and streamwise direction with the heat flux.
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    NUMERICAL PREDICTION OF THERMOMECHANICAL SENSITIVITY OF THE FIRST STAGE NOZZLE GUIDE VANE WITH FILM COOLING
    (2022-01-01)
    Khumhaeng, Siwanart
    ;
    Suksa, Thitapa
    ;
    Laohalertchai, Nutcha
    ;
    Chaiprasit, Benyapa
    ;
    Chotroongruang, Thanapat
    Practically, a gas-turbine engine's first-stage nozzle guide vane (NGV) must operate under extreme conditions induced by high temperatures from burned gases, causing severe damage to the vane, such as cracks or fatigue failures. As a result, the first stage NGV's lifespan is shortened. In other words, the first stage NGV's lifespan is determined by the vane material's durability. Therefore, effective cooling systems and thermal barrier coating (TBC) are provided. This paper presents a numerical prediction of the thermomechanical sensitivity of the first stage NGV with film cooling under aerothermal conditions and TBC using a 3D CFD/CHT approach with a static structure model for a steady temperature analysis. Turbine inlet temperature (TIT), coolant inlet temperature (CIT), blowing ratio (BR), and TBC thickness, which are key factors for gas turbines' performance improvement, are used as independent variables. An examination of vane cooling performance is presented in the first part, followed by a prediction of the thermomechanical sensitivity of the vane under the four variables in terms of von Mises equivalent stress and strain in the second part. The findings obtained from both parts show that the relationship between cooling performance and thermomechanical characteristics is sensitive to the influences of turbine inlet temperature (TIT), coolant inlet temperature, and TBC thickness. In addition, the findings indicate the role of the blowing ratio in thermal and mechanical sensitivity for the filmcooled vane.