Numerical simulations are carried out to predict the phantom cooling on the blade tip and casing from blade-surface film coolant. The impacts of hole compound angles and shape for the pressure side (PS) film hole on the tip and casing phantom cooling are investigated under various mass flow ratios (MFR) of coolant to mainstream from 0.7% to 2.6%. The results indicate that the coolant derived from the leading edge and PS film holes could help cool the tip, especially for the tip forepart and near the PS where its heat transfer coefficient is the highest due to the leakage flow separation. The casing could also be cooled, but its cooling effectiveness level is much lower than that on the tip. Increasing MFR has a noticeable improvement both on the phantom cooling performance of the tip and the casing. Increasing the compound angle of PS film holes would enhance the phantom cooling performance on both the tip and the casing in that the coolant spanwise component toward the tip is increasing, particularly at higher MFR values. Applying shaped holes would increase the cooling effectiveness of the tip middle-to-aft part, but would decrease it on the tip forepart. In contrast, shaped holes always worsen the cooling effectiveness level of the casing.


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    Titel :

    Turbine Blade Tip and Casing Phantom Cooling from Blade-Surface Film Coolant


    Beteiligte:
    Li, Feng (Autor:in) / Liu, Zhao (Autor:in) / Feng, Zhenping (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2020-10-20


    Format / Umfang :

    15 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch