2020 Fiscal Year Final Research Report
Study of supersonic turbine with pseudo-shock model
| Project/Area Number |
18K03957
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Multi-year Fund |
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| Section | 一般 |
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| Review Section |
Basic Section 19010:Fluid engineering-related
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| Research Institution | Chubu University |
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Principal Investigator |
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| Project Period (FY) |
2018-04-01 – 2021-03-31
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| Keywords | タービン / 超音速 / 遠心力 / 擬似衝撃波 |
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| Outline of Final Research Achievements |
Study of the supersonic turbines with the pseudo-shock model was conducted.
A pseudo-shock model was created.(1 peer-reviewed paper) Experiments and numerical simulation were conducted, and they showed the effect of increased pressure caused by the pseudo-shock on the turbine performance was.(2 conference papers)
It was found out the centrifugal force affected flow condition in the turbines and it greatly degraded the turbine performance. Calculation model was constructed which included the effect of the centrifugal force on the turbine performance. The model results were verified by comparison with the experimental and numerical results. It was made clear the centrifugal force had to be included in estimation of the supersonic turbine performance. The result is now in submission to a journal.
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| Free Research Field |
推進工学、流体力学、熱力学
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| Academic Significance and Societal Importance of the Research Achievements |
ロケットエンジンのタービン設計では従来、種々の損失を上げてその影響を検討してきた。実験および数値シミュレーションにおける大きな損失のメカニズムが不明であり、タービン性能向上を行うことが困難であった。従来の擬似衝撃波モデルを適用するだけでは、損失を説明できなかった。
今回の研究により、高速で急激に流れの向きをかえるタービン内の流れに働く遠心力が、タービン内の流れに大きく影響し、性能を下げていることが明らかとなった。損失を抑制するための方法についても提案を行った。
今後の超音速タービン設計において本研究の知見や計算方法を活用することで、高性能なタービンを設計することが可能となった。
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