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research-article

Improvement in Film Cooling Effectiveness using Single and Double Rows of Holes with Adverse Compound Angle Orientations

[+] Author and Article Information
Elumalai Kannan

Department of Mechanical Engineering, Hindustan Institute of Technology and Science, Chennai, Tamil Nadu, India
kannan2671@gmail.com

Seralathan Sivamani

Department of Mechanical Engineering, Hindustan Institute of Technology and Science, Chennai, Tamil Nadu, India
siva.seralathan@gmail.com

Dibyakanti Ghosh Roychowdhury

Department of Mechanical Engineering, Hindustan Institute of Technology and Science, Chennai, Tamil Nadu, India; Hindustan College of Science and Technology, Farah, Mathura, Uttar Pradesh, India
roychowdhury.dg@gmail.com

T. Micha Premkumar

Department of Mechanical Engineering, Hindustan Institute of Technology and Science, Chennai, Tamil Nadu, India
tmichamech@gmail.com

Venkatesan Hariram

Department of Mechanical Engineering, Hindustan Institute of Technology and Science, Chennai, Tamil Nadu, India
connect2hariram@gmail.com

1Corresponding author.

ASME doi:10.1115/1.4041937 History: Received March 12, 2018; Revised November 01, 2018

Abstract

Three dimensional Reynolds Averaged Navier Stokes equations with shear stress transport turbulence model is used to analyze the film cooling effectiveness on a flat plate having single row of film hole involving cylindrical and laidback holes. The cylindrical and laidback holes are inclined at 35° to the surface with a compound angle (ß) orientation ranging from favorable to adverse inclination (i.e., ß = 0° to 180°) and examined at high and low blowing ratios (M = 1.25 and 0.60). Cylindrical hole (CH) with a adverse compound angle of 135° gives the highest area averaged film cooling effectiveness in comparison with laidback hole (LBH) configuration. Also, CH ß =135° film hole shows a higher lateral coolant spread. Later, double jet film cooling concept is studied for this cylindrical hole. In all the cases, the first hole compound angle is fixed as 135° and the second hole angle is varied from 135° to 315°. At high blowing ratio, the dual jet cylindrical hole (DJCH) with ß =135°, 315° gives a higher area averaged film cooling effectiveness by around 66.50% compared to baseline CH ß = 0°. On comparing all CH, LBH and DJCH cases, the highest area averaged film cooling effectiveness is obtained by CH configuration with ß = 135°. Hence, the cylindrical hole with its adverse compound angle (ß = 135°) orientation could be an appropriate film cooling configuration for gas turbine blade cooling.

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