Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor
This research was done to analyze the effects of two different blowing ratios of BR=1.25 and BR=3.18 on the film cooling effectiveness at the combustor outlet, whereas the cylindrical and row trench holes with alignment angle of +60 degrees were considered. In the current research, a three-dimension...
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my.utm.590102017-01-30T02:21:43Z http://eprints.utm.my/id/eprint/59010/ Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor Kianpour, Ehsan C. S., Nor Azwadi Mohammad Hussein, Razavi M., Akbari Masoud, Afrand Golshokouh, Iman TJ Mechanical engineering and machinery This research was done to analyze the effects of two different blowing ratios of BR=1.25 and BR=3.18 on the film cooling effectiveness at the combustor outlet, whereas the cylindrical and row trench holes with alignment angle of +60 degrees were considered. In the current research, a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2.26. This study has been carried out with Reynolds-averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. The combustor combines the interaction of two rows of dilution jets, which are staggered in the stream-wise direction and aligned in the span-wise direction, with that of film cooling along the combustor liner walls. The entire findings of the study showed that trenched holes performed much more efficiently at both blowing ratios, especially at BR=3.18. North Atlantic University Union 2015 Article PeerReviewed Kianpour, Ehsan and C. S., Nor Azwadi and Mohammad Hussein, Razavi and M., Akbari and Masoud, Afrand and Golshokouh, Iman (2015) Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor. International Journal of Mechanics, 9 . pp. 11-15. ISSN 1996-3599 |
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TJ Mechanical engineering and machinery Kianpour, Ehsan C. S., Nor Azwadi Mohammad Hussein, Razavi M., Akbari Masoud, Afrand Golshokouh, Iman Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor |
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This research was done to analyze the effects of two different blowing ratios of BR=1.25 and BR=3.18 on the film cooling effectiveness at the combustor outlet, whereas the cylindrical and row trench holes with alignment angle of +60 degrees were considered. In the current research, a three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2.26. This study has been carried out with Reynolds-averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. The combustor combines the interaction of two rows of dilution jets, which are staggered in the stream-wise direction and aligned in the span-wise direction, with that of film cooling along the combustor liner walls. The entire findings of the study showed that trenched holes performed much more efficiently at both blowing ratios, especially at BR=3.18. |
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Article |
author |
Kianpour, Ehsan C. S., Nor Azwadi Mohammad Hussein, Razavi M., Akbari Masoud, Afrand Golshokouh, Iman |
author_facet |
Kianpour, Ehsan C. S., Nor Azwadi Mohammad Hussein, Razavi M., Akbari Masoud, Afrand Golshokouh, Iman |
author_sort |
Kianpour, Ehsan |
title |
Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor |
title_short |
Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor |
title_full |
Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor |
title_fullStr |
Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor |
title_full_unstemmed |
Thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor |
title_sort |
thermodynamic analyzes of film cooling for a restructured cooling holes at the end of gas turbine engine combustor |
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North Atlantic University Union |
publishDate |
2015 |
url |
http://eprints.utm.my/id/eprint/59010/ |
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1643654448172498944 |
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13.160551 |