막냉각이 적용된 수소추력기의 설계 및 연소시험

초록

Hydrogen is expected as a future green energy source because of its high energy density, and can be used as rocket propellant. Using hydrogen propellant will produce high specific thrust, but it can cause structure failure by high flame temperature. Therefore, cooling system is essential hydrogen thruster. In this paper, hydrogen thruster with coaxial injector and was designed, and film cooling system with nitrogen gas as a coolant is adopted for combustion chamber cooling. Combustion test was conducted in combustion test chamber with water sprinkler system. Effect of film cooling on wall temperature was measured, and effect of coolant by chamber pressure was found.