Interference Characteristics of Shock Wave and Film Cooling in Supersonic Flow
Shock waves can influence the characteristics of the film cooling flow field,resulting in changes to the flow field structure and cooling efficiency.In order to investigate the impact of shock interference,film cooling on supersonic flat plate varying jet angles and blowing ratios was analyzed by numerical simulation method.The results demonstrate that the film cooling efficiency exhibits an initial increase and subsequent decline with an increase in the blowing ratio.Additionally,the spreading coverage of the film near the holes gradually improves with the increase of jet angle,while the cooling efficiency is accelerated along the decay of the flow direction.To analyze the effect of shock interference on the film cooling flow,a dimensionless coordinate system is employed.It can be concluded that the shock will cause a significant reduction in the cooling efficiency.Furthermore,the coolant is prone to producing a three-dimensional flow separation under the shock interference.As the jet angle increases,the limiting streamlines topology in the separation zone becomes increasingly complex.In order to quantitatively analyze the effect of the shock interference on the film cooling efficiency,the uniformity index parameter is introduced.The uniformity of the cooling distribution in the shock interference region shows a tendency of increasing and then decreasing with the increase of the blowing ratio under different jet angles.
SupersonicPlate Film CoolingShock Wave InterferenceFilm Cooling Effectiveness
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