Part load performance analysis of TurboJet with rotating detonation combustor

This work presents an analysis of a turbojet engine integrated with a hydrogen-fueled rotating detonation combustor (RDC). The cycle layout consists of NASA Energy Efficient Engine ( E 3 ) 10-stage high-pressure compressor, RDC, mixer, NASA ( E 3 ) two-stage high-pressure turbine and convergent nozzle. The turbine inlet temperature (TIT) is fixed at 1800 K for the take-off condition. In this study, the mixer determines the TIT using the entrainment ratio. The performance metrics of RDC-turbojet with hydrogen fuel and conventional turbojet with Jet A1 fuel were compared for the take off condition. Results shows that the RDC-turbojet showed higher thrust, lower thrust-to-specific fuel, lower exergy destruction and higher exergy efficiency. Flow parameters and performance metrics were evaluated and compared for different part load conditions such as 75% corrected speed, 85% corrected speed, maximum climb and maximum cruise. The turbojet operating map are generated for different altitudes ranging from sea level to 11 km. • Cycle model integrates NASA E3 compressor, RDC, mixer, turbine, and nozzle. • Hydrogen RDC outperformed Jet A1 conventional turbojets under take-off conditions. • RDC cycle has lower overall exergy destruction than conventional turbojet. • Part-load conditions 75% speed, 85% speed, take-off, climb, and cruise are analyzed.