One-dimensional steady method was used to calculate the high temperature rise combustor engine and two-combustor engine's overall performance in consideration of the component efficiency. The overall performance was compared at total pressure ratio 32 and turbine inlet temperature 1900K for two-combustor engine and turbine inlet temperature 2400K for high temperature rise combustor engine. The way of temperature rise distribution between combustors of two-combustor engine was also analyzed. Results show that the specific thrust of high temperature rise combustor engine is 2.7 percent higher than that of two-combustor engine

while the specific thrust fuel consumption is 3.8 percent lower. The two-combustor engine is helpful to decrease the total pressure loss under supersonic condition

and its specific thrust increase ratio is higher than high temperature rise combustor engine when Mach number is more than 1.5.