Nabeel Al-Zurfi, Adel Nasser, Ahmed Alhusseny

    Research output: Contribution to conferencePaperpeer-review


    Among the several film cooling enhancement techniques used in film holes design, the use of anti-vortex holes technique has been gaining popularity. In the current work, the film cooling effectiveness for flow over a 1-1/2 stage gas turbine blade has been analysed by varying the blowing ratio and the side hole
    position. A three dimensional, unsteady state numerical heat transfer simulation has been conducted on this blade using the finite-volume method. The simulation are performed to predict the turbulent flow using the large eddy simulation methods. The blowing ratio varied from 1.0 to 5.0 and the density ratio of coolant to mainstream was 2.0. Compared to the base hole, the film cooling performance of the all anti-vortex cases showed obvious improvement at all blowing ratios. The middle stream side holes and downstream side holes each demonstrated good film cooling performance at all blowing ratios, while the upstream side holes perform well only at a lower blowing ratio.

    The presence of side holes can restrain the CRVP intensity of the main hole and reduce the coolant lift-off, improving the film coverage and film cooling effectiveness. The downstream side holes can perform better in reducing the CRVP intensity.
    Original languageEnglish
    Number of pages9
    Publication statusPublished - 14 Mar 2019


    • Rotor blade
    • LES,
    • Film effectiveness
    • Ant-vortex holes design


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