Research on separate exhaust turbine based continuous detonation engine performance
A separate exhaust turbine-based continuous detonation combined engine configuration was proposed,and a general performance analysis model was built for the combined engine based on the GSP computing platform,and an aerothermodynamic equivalent calculation model was built for the detonation combustion module.The results showed that the combined engine could operate in the speed range of 0～3 Mach and meet the thrust demand when the equivalent folded speed control law was adopted;the thrust of the combined engine increased and then decreased with the increase of the ratio of the turbine-based bleed gas to the detonation combustion chamber(defined as the split fraction in the paper),and the corresponding split fraction was 0.49 at the maximum thrust.
gas turbine engineoverall performancerotating detonationengine characteristic
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