EXPERIMENTAL STUDY ON AERODYNAMIC PERFORMANCE OF ULTRA-HIGHLY LOADED AXIAL TURBINE BY USING SMALL SIZED ANNULAR CASCADE : EFFECTS OF TIP CLEARANCE SIZE AND BLADE PROFILE
Bibliographic Information
- Other Title
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- 小型円環翼列による超高負荷軸流タービンの空力性能に関する実験的研究 : 翼端間隙高さと翼形状の影響
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Description
Raising the turbine blade loading by the increase of the blade turning angle can improve the aerodynamic performance of axial turbine which is the main part of the gas turbines. However, the increase of the blade turning angle intensifies the passage vortex and leakage vortex, and deteriorates the aerodynamic performance of axial turbine. Therefore, in order to develop a highly loaded axial turbine cascade, it is necessary to clarify the influences of the intensifications of the passage vortex and the tip leakage flow on the aerodynamic performance of turbine cascade. In this study, the aerodynamic performances of two types of UHLTC, Up and Down, with the turning angle of 160 degree were measured by using the small-sized turbine cascade test rig. Furthermore, the tip clearance size was set to 2% and 3% of the passage height. The experimental results showed that the Up-blade possessed the higher efficiency than the Down-blade because of the higher torque performance in spite of the higher loss generation. The reduction of the tip clearance size was more effective to enhance the efficiency because it could reduce the loss generation in addition to the increase of the torque performance.
Journal
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- 法政大学大学院紀要. 理工学・工学研究科編
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法政大学大学院紀要. 理工学・工学研究科編 62 1-7, 2021-03-24
法政大学大学院理工学・工学研究科
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Details 詳細情報について
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- CRID
- 1390853650462609792
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- NII Article ID
- 120007119684
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- NII Book ID
- AA12677220
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- HANDLE
- 10114/00023891
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- ISSN
- 21879923
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- Text Lang
- ja
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- Data Source
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- JaLC
- IRDB
- CiNii Articles
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- Abstract License Flag
- Allowed