Novel Flow Control Method for Vortex Shedding of Turbine Blade
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- EL-GENDI Mahmoud M.
- Department of Aerospace Engineering, Nagoya University
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- IBRAHIM Mohammed K.
- Department of Aerospace Engineering, Nagoya University Aerospace Engineering Department, Faculty of Engineering, University of Cairo
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- MORI Koichi
- Department of Aerospace Engineering, Nagoya University
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- NAKAMURA Yoshiaki
- Department of Aerospace Engineering, Nagoya University
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Three-dimensional flow simulations through a turbine cascade were carried out for an exit isentropic Mach number of 0.79 and a Reynolds number of 2.8×106. The main objective is to increase the base pressure. Calculations were carried out using an in-house numerical code, where a 2nd order Roe’s flux-difference splitting for inviscid numerical fluxes, a 2nd order implicit dual time method for time integration, and Delayed Detached Eddy Simulation for turbulence were employed. The present idea to increase the base pressure is to connect the pressure and suction sides of the blade using microtubes distributed uniformly along the span on the trailing edge. Simulated results show that this modification does not affect the blade load, increases the base pressure by 0.7%, and decreases the overall loss by 3%.
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 53 (180), 122-129, 2010
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390282679057086208
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- NII論文ID
- 10026613028
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- NII書誌ID
- AA0086707X
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- ISSN
- 21894205
- 05493811
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- NDL書誌ID
- 10782792
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- NDL
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- 使用不可