Numerical analysis of film cooling effectiveness using compound cooling holes at the end of gas turbine engine combustor

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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书目详细资料
主要作者:	Salimi, Shahin
格式:	Thesis
语言:	English
出版:	2014
主题:	TJ Mechanical engineering and machinery
在线阅读:	http://eprints.utm.my/id/eprint/78023/1/ShahihSalimiMFKM20141.pdf
标签:	添加标签没有标签, 成为第一个标记此记录!

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