Effects Of Compressibility On The Pressure Distribution Of Turbomachinery Airfoils
碩士 === 國立成功大學 === 工程科學研究所 === 85 === Vortical distubance and potential effect generate unsteady aerodynamic loading of the axial compressor blade. These unsteady loading may cause high - cycle blade fatigue. With smaller gap between cascade, the potential effect is getting more serious. Thus an un...
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| Format: | Others |
| Language: | zh-TW |
| Published: |
1997
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| Online Access: | http://ndltd.ncl.edu.tw/handle/04264642990409381206 |
| Summary: | 碩士 === 國立成功大學 === 工程科學研究所 === 85 === Vortical distubance and potential effect generate unsteady aerodynamic loading of the axial compressor blade. These unsteady loading may cause high - cycle blade fatigue. With smaller gap between cascade, the potential effect is getting more serious. Thus an understanding of the potential effect is important for designing a modern turbomachine. In this study, an implicit upwind code has been used to solve Euler equation for simulating the potential flow within a single stage compressor. By varying different inlet Mach number, the effect of compressibilty on the pressure distribution of a stator airfoil is investigated. The pressure decay rate along the up - and down - stream of the mean flow are computed. It is found the decay rate along the upstream is faster than that along the downstream.
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