Numerical Study of Film Cooling Over Flat Plate | ||
| International Conference on Aerospace Sciences and Aviation Technology | ||
| Article 82, Volume 14, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 14 – May 24 - 26, 2011, May 2011, Pages 1-16 PDF (495.84 K) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/asat.2011.23396 | ||
| Authors | ||
| A. S. Baher-Eneel1; A. F. El-Sayed2; M. H. Khobeiz3 | ||
| 1Libyan postgraduate student. | ||
| 2Prof. of Aerospace and Mechanical Engineering, Zagazeeg University, Egypt. | ||
| 3Egyptian Armed Forces, Egypt. | ||
| Abstract | ||
| The effect of film cooling over flat plate was investigated using Fluent 6.32. The computational domain included the coolant supply tube as well as the main mixing region. A tube L/D of 4 and injection angles of (30o, 60o, and 90o) were employed for blowing ratio of (0.33, 0.5, and 1.67), and a density ratio of 1.14. Adiabatic film cooling effectiveness distributions were also determined for inline and stagger arrangements. The main observation from this study that the 30o hole gave larger effectiveness values than 60o and 90o at the blowing ratio of 0.33 with the same length-to-diameter ratio. The maximum effectiveness was achieved with a blowing ratio of 0.5. The results show that the increase of blowing ratio negatively affects film cooling, such that for the blowing ratio of 1.67 the injected coolant tends to lift off from the wall due to the increase of the wall normal momentum. The comparisons for numerical results with experimental data are presented. | ||
| Keywords | ||
| Film cooling; Adiabatic effectiveness; Injection angle; Blowing ratio | ||
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