IGTC-13 Development of Casing Wall Boundary Layer through an Axial Compressor Rotor(Session A-4 AERODYNAMICS IV (Turbomachinery))
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概要
- 論文の詳細を見る
An experimental study has been carried out to clarify development of a casing wall boundary-layer through an isolated axial compressor rotor with various tip clearances. The detailed flow measurements have been made before and behind two rotors under the design and the off-design conditions, and by changing an inlet boundary. layer thickness. The exit flow distribution at tip region are determined mainly by the inlet main-stream condition rather than the inlet flow angle near the tip. The variation of the exit boundary-layer integral properties is closely related to a behavior of a tip leakage vortex. The blade force-defect has been examined on the basis of the end-wall boundary-layer equations and the empirical formulae have been presented in conformity with the actual flow phenomena.
- 公益社団法人日本ガスタービン学会の論文
著者
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INOUE M.
Department of Hematology/Oncology, Osaka Medical Center and Research Institute for Maternal and Chil
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Fukuhara M.
Department Of Mechanical Engineering Kyushu University
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Kuroumaru M.
Department of Mechanical Engineering, Kyushu University
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Kuroumaru M.
Department Of Energy And Mechanical Engineering Kyushu University
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Kuroumaru M.
Department Of Mechanical Engineering Kyushu University
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