Numerical investigation of heat transfer in film layer under supersonic consition of convergent-divergent transition
2019
The distribution of film cooling effectiveness in supersonic mainstream of
circle-rectangular Convergent-Divergent transition has been numerically
investigated under different pressure ratios. The shock wave exerted
superior influence on film cooling. In supersonic main flow, extra
compression waves formed in upstream of the film holes, resulted by the
obstruction of the multiple cooling jets. This exerted extra pressure to the
boundary layer, induced adverse pressure gradient, and led to weakening of
the film flow attachment ability and decreasing of local cooling
effectiveness. Bow oblique shock wave occurred in front of holes, the two
oblique bow shaped low pressure zones formed on both sides of the hole, and
low cooling effectiveness zones appeared accordingly. The inefficient region
at the leading edge of the hole destroyed the film developing between holes,
decreased the cooling effectiveness accumulation in the rear part. The
decrease of hole incline angle caused an increase of cooling effectiveness,
which reduced reverse velocity gradient caused by shock wave in the boundary
layer and improved film attachment. The influence of main flow pressure
ratio to film cooling was also investigated, and found with increasing of
the ratio, the influence will became even significant.
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