Experimental Studies of Film Cooling in Supersonic Combustors

Abstract

The current work is an experimental investigation of the dependence of film-cooling effectiveness on the injection angle, mass flux and injection temperature in supersonic combustors. The mainstream Mach number is 2.5, and the coolant was injected with sonic speed. The total temperature of the mainstream is 1500K, and for the injection it ranges from 300K to 1060K. Three injection angle is respectively , , . The coolant mass flux ranges from 1% to 6% of the mainstream mass flux, and the mainstream mass flux is 2.5kg/s. The results show that a smaller injection angle has a better performance in film cooling effectiveness and indicate that an increase in film-cooling effectiveness with the increase of the coolant mass flux. The influence of coolant temperature is more complex. The rising of coolant temperature reduces the film-cooling effectiveness without kerosene combustion, while has not significant difference with kerosene combustion.

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

“…However, as the temperature sensor of the calculation model is very sensitive to signal delay, which will probably lead to errors, the experimental model should be amended in later studies to improve the temperature measurement accuracy. Fan et al [43] studied the relationship between air film cooling effect and the film spray angle, and between mass flux of the coolant and the spray temperature in the combustion chamber of propulsion systems. The conclusions show that a relatively small spray angle can achieve a comparatively good air film cooling effect.…”