Departmental Bulletin Paper 超高負荷タービン翼列内の二次元圧縮性流れの数値解析:翼形状に対する出口マッハ数の影響

小暮, 啓太

57pp.1 - 7 , 2016-03-24 , 法政大学大学院 理工学・工学研究科
ISSN:2187-9923
Description
The objective of this study is to obtain the knowledge to apply an ultra-highly loaded turbine cascade (UHLTC) with the turning angle of around 160 degrees to a practical gas turbine. In the present study, the two-dimensional flows in three types of UHLTC, which are different in the maximum blade thickness, were analyzed numerically for the subsonic and the supersonic exit Mach number conditions in order to clarify the influence of the blade profile itself on the shock formation and the associated loss eneration. The computed results clarified that the increase of the exit Mach number ntensified the shock wave on the suction surface around the blade trailing edge and consequently strengthened its interaction with the boundary layer on the suction surface and reduced the outlet flow angle. The interaction of shock wave with the boundary layer increased the profile loss by generating the boundary layer separation according to the decrease of maximum blade thickness. Key Words : Ultra-Highly Loaded Turbine Cascade, Two-Dimensional Flow, Exit Mach Number, Blade Profile
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http://repo.lib.hosei.ac.jp/bitstream/10114/12281/1/14R1115%e5%b0%8f%e6%9a%ae%e5%95%93%e5%a4%aa.pdf

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