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Investigation of Film Cooling Effectiveness Enhancement by Using Corrugated Spiral Holes

Ammar Fakhir Abdulwahid(1*), Tholudin Mat Lazim(2), Aminuddin Saat(3), Zaid Sattar Kareem(4)

(1) Faculty of Mechanical Engineering, Universiti Teknologi Malaysia (UTM), Malaysia
(2) Faculty of Mechanical Engineering, Universiti Teknologi Malaysia (UTM), Malaysia
(3) Faculty of Mechanical Engineering, Universiti Teknologi Malaysia (UTM), Malaysia
(4) Faculty of Mechanical Engineering, Universiti Teknologi Malaysia (UTM), Malaysia
(*) Corresponding author



Film cooling represents one of the important game-changing technologies that has allowed the achievement of today’s high inlet turbine temperature to get high-efficiency gas turbine engines. Shear Stress Transport (SST) K-ω was performed to investigate the flow structures and the development process of vortices in different sections (rectangular, hexagonal and circular) of a stationary gas turbine at blowing ratio equal to (0.5, 1.0, 1.5 and 2.0), while the jet film cooling hole angles equal to (90°, 60°, 45° and 30°). It was observed that higher freestream turbulence improves adiabatic effectiveness and heat transfer coefficient for the corrugation film cooling holes design and specially enhancement at holes angle equal to 30° with twisted angle equal to 360° and rectangular corrugation shape. Results show the effectiveness enhancement range of 20.1%-69.3%of the smooth film cooling hole. Numerical calculation of film cooling effectiveness is validated with reported numerical and experimental results.
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Film Cooling; Jet In Cross Flow; Twisted Holes; Turbulent Flow

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