日本航空宇宙学会誌
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
2次元遷音速タービン翼列の性能に関する研究
永山 猛彦倉元 靖夫今泉 全通
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1982 年 30 巻 341 号 p. 338-346

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The effect of the aerofoil suction side curvatures on the 2-D transonic turbine cascade performances is investigated by the numerical and the experimental methods. The Modified FLIC method is used to predict the cascade flows. The experiments are conducted in the wide range of the exit Mach number M2th=0.5 to 2.0 by the optical and the wake traverse methods using the suction-type shock tunnel and the blow-down type wind tunnel.
The characteristics of the flow patterns around these four kinds of aerofoil sections are clarified and it is shown that the relation between energy loss and its exit Mach number clearly depends on their suction side curvatures.

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© The Japan Society for Aeronautical and Space Sciences
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