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ABSTRACT
The present study proposes a suitable injection configuration and operating parameters for the film cooling of an aero-engine afterburner, based on experimental and numerical studies. The experimental investigations are carried out for different injection locations for blowing ratios 0.5 and 1, fixed injection angle (45°), and density ratio (1.095). The numerical study is extended for various injection locations with a wide range of operating parameters such as blowing ratios from (0.25–3), density ratios (1.095, 2.5, and 4), and different pressure ratios from 1 to 15, representing the operating conditions of an actual aero-engine afterburner. The present study reveals that the film cooling on the corrugated surface is strongly influenced by the secondary stream injection locations and corrugation amplitude to wavelength ratio. This study also shows that the film cooling behavior on a corrugated surface is inherently different from that a flat surface; the centreline effectiveness plots show improvements even at a higher blowing ratio (i.e. 2). The density ratio also shows a significant impact on film cooling performance, and with an increase in density ratio from 1.095 to 2.5, the centreline effectiveness increases.
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Acknowledgments
The authors are thankful to the Department of Mechanical Engineering, NIT Manipur for the Wind Tunnel test facility (Under TEQIP-III) and the Department of Science and Technology (SERB), New Delhi under Early Career Research Award; Project Ref. No. ECR/2016/001364; for the Computational facility to carry out the numerical study in the Department of Mechanical Engineering at NIT Manipur, India.
Disclosure statement
No potential conflict of interest was reported by the author(s).