Design method of supercritical hydrocarbon fuel injection for a scramjet

Abstract

Abstract Both the fuel transfer control scheme and the knowledge of fuel temperature and pressure values before injection are important to a scramjet engine. A measurement method of the fluid temperature suitable for small channel is presented, and a fluid transfer control scheme of the area of injecting holes is designed using the balance equations of fluid mass, energy and entropy. A convective heat transfer experiment is conducted to evaluate the temperature measurement and the fluid transfer control design method of the heat absorbing supercritical hydrocarbon fuel. The results show that during the heating process the injecting pressure meets the requirement, and the fluid transfer control system works well. Such results suggest that the design method in the present work would be useful in the design of regenerative cooling for scramjet engines.

Keywords

• Supercritical hydrocarbon fluid
• Temperature measurement
• Transfer control
• Scramjet engine