Effects of an Entrance Step on the Performance of Film-Cooling Holes with Compound Angles at the Endwall of a Gas Turbine Vane
碩士 === 大葉大學 === 機械工程研究所碩士班 === 93 === In the existing literature for such a problem, all researchers used smooth walls for hot gas passage. Thus, boundary layer developed along the endwalls before reaching the leading edge of the first stage guide vanes. After that, the flow of hot gas is affected b...
| Main Authors: | , |
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| Format: | Others |
| Language: | zh-TW |
| Published: |
2005
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| Online Access: | http://ndltd.ncl.edu.tw/handle/10122263076370395591 |