Film Cooling Experimental Study on Sinusoidal Corrugated Liner for Afterburner

摘要

The need of improved cooling effectiveness for hot components in jet engines has led to new designs of afterburner liners. In the present paper, experiments were performed to reveal the cooling characteristics and flow loss of various sinusoidal corrugated liners for an advanced afterburner. It is found that there are alternate high temperature and low temperature zones corresponding to the wave crests and troughs of the corrugated liner, respectively. Compared to the flat liner, the corrugated liner increases cooling effectiveness by 10% at the blowing ratio of 0.5, by 4.5% at the blowing ratio of 3.2. However, the difference in discharge coefficients for these two kinds of liners is only 4.3%. The increased opening ratio of film holes from 1.42% to 3.72% for corrugated liners is able to improve the cooling effectiveness by 9.8%. However, the discharge coefficient is decreased by 34.1%. The augment of amplitude of liners can enhance the ram effect of cooling air, which has an advantage to increase the local blowing ratio, and to form good cooling film at the windward of wave troughs. The flow loss is bigger while the cooling effectiveness is enhanced due to the change of amplitude of the liner.