A-16 高反動度型超音速タービン翼列のための数値流体解析手法(蒸気タービン,一般講演)

概要

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A quasi-3D computational technique for turbulent flows of supersonic turbine cascade was developed, in particular grid generation method and inflow and outflow boundary conditions. The grid generation technique uses multi-block structured grids and the orthogonality of the grid is good even for highly staggered blades. The nonreflecting boundary conditions based on two-dimensional characteristic theory can prevent non-physical reflection of a shock wave at the inlet and outlet boundaries. Computational pressure distributions on transonic compressor agree well with the experimental results. The computational method was applied to the supersonic turbine cascade of the last stage blade in a steam turbine. Shock waves can be captured accurately and stably and spurious reflections of shock waves at the boundaries can be avoided.
公益社団法人日本ガスタービン学会の論文
2010-10-20