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Author: search.filters.author.Chotroongruang, Thanapat

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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.
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    INFLUENCE of COOLANT on COOLING PERFORMANCE SENSITIVITY of INTERNALLY CONVECTIVE TURBINE VANE
    (2021-01-01)
    Chotroongruang, Thanapat
    ;
    Prapamonthon, Prasert
    ;
    Thongdee, Rungsimun
    ;
    Thongmuenwaiyathon, Thanapat
    ;
    Sun, Zhenxu
    Based on the Brayton cycle for gas-turbine engines, the high thermal efficiency and power output of a gas-turbine engine can be obtainable when the gas-turbine engine operates at high turbine inlet temperatures. However, turbine components e.g., inlet guide vane, rotor blade, and stator vane request high cooling performance. Typically, internal cooling and film cooling are two effective techniques that are widely used to protect high thermal loads for the turbine components in a stateof- the-art gas turbine. Consequently, the high thermal efficiency and power output can be obtained, and the turbine lifespan can be prolonged, also. On top of that, a comprehensive understanding of flow and heat transfer phenomena in the turbine components is very important. As a result, both experiments and simulations have been used to improve the cooling performance of the turbine components. In fact, the cooling air used in the internal cooling and film cooling is partially extracted from the compressor. Therefore, variations in the cooling air affect the cooling performance of the turbine components directly. This paper presents a numerical study on the influence of the cooling air on cooling-performance sensitivity of an internally convective turbine vane, MARK II using the computational fluid dynamics (CFD)/conjugate heat transfer (CHT) with the SST k- turbulence model. Result comparisons are conducted in terms of pressure, temperature, and cooling effectiveness under the effects of the inlet temperature, mass flow rate, turbulence intensity, and flow direction of the cooling air. The cooling-performance sensitivity to the coolant parameters is shown through variations of local cooling effectiveness, and area and volume-weighted average cooling effectiveness.