Comparison between Hot and Cold Flow Conditions of Turbine Cascade
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概要
- 論文の詳細を見る
Flow quantities in the hot and cold flow conditions of a turbine cascade were compared at the same exit isentropic Mach and Reynolds numbers by three-dimensional flow simulations. In the hot flow condition, the total temperature at the inlet was 772 K, and the isothermal temperature of the blade was 540 K. In the cold flow condition, the total temperature at the inlet was 280 K, and the blade was adiabatic. As a result, the cold and hot flow conditions were similar in total and static density in the wake, total and static pressure, velocity, the thicknesses of the viscous and thermal boundary layers, and the amplitude and frequency of the vortex shedding. On the other hand, they were different in static density in the boundary layer, and total and static temperatures. Moreover, the Eckert-Weise effect was observed in the cold flow condition, while energy separation in the wake was observed in the hot flow condition.
- 社団法人 日本航空宇宙学会の論文
- 2010-11-04
著者
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EL-GENDI Mahmoud
Department of Aerospace Engineering, Nagoya University
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MORI Koichi
Department of Aerospace Engineering, Nagoya University
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NAKAMURA Yoshiaki
Aerospace Engineering Department, Graduate School of Engineering, Nagoya University
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Ibrahim Mohammed
Department Of Aerospace Engineering Nagoya University
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Nakamura Yoshiaki
Department Of Aerospace Engineering Nagoya University
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El-ghandour Mohamed
Department Of Aerospace Engineering Nagoya University
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Ibrahim Mohammed
Aerospace Engineering Department Faculty Of Engineering University Of Cairo
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DOI Katsunori
Department of Aerospace Engineering, Nagoya University
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Nakamura Yoshiaki
Aerospace Engineering Department Graduate School Of Engineering Nagoya University
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Mori Koichi
Aerospace Engineering Department Graduate School Of Engineering Nagoya University
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Nakamura Yoshiaki
Department Of Aerospace Eng. Nagoya University
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Doi Katsunori
Department Of Aerospace Engineering Nagoya University
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Nakamura Yoshiaki
Department Of Aeronautical Engineering Nagoya University
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IBRAHIM Mohammed
Department of Aerospace Engineering ,Nagoya University
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