Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor
By using the well-known Bryton cycle, great turbine industries strive to extend the turbine inlet temperature and increase engine performance. However the turbine inlet temperature increment creates harsh environment for the downstream components of the combustor and so it is needed to design a cool...
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| 主要作者: | |
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| 格式: | Thesis |
| 語言: | English |
| 出版: |
2014
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| 主題: | |
| 在線閱讀: | http://eprints.utm.my/id/eprint/78023/1/ShahihSalimiMFKM20141.pdf |
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