in a forward direction 16 and an aft direction 18 engine 10 includes a core engine 30 which includes a high pressure compressor 34 a combustor 36 a high pressure turbine 38 and a power turbine or a low pressure turbine 39 all arranged in a serial axial flow relationship in an alternative embodiment core engine 30 includes a compressor a detonation chamber and a turbine arranged in a serial axial flow relationship engine 10 also includes a bypass duct 44 that surrounds core engine 30 and enables fluid flow to be routed downstream from core engine 30 rather than through core engine 30 in an alternative embodiment engine 10 includes a core fan assembly not shown an annular centerbody 50 extends downstream from core engine 30 toward a variable geometry exhaust nozzle 54 during operation airflow enters engine 10 and fuel is introduced to core engine 30 the air and fuel are mixed and ignited within core engine 30 to generate hot combustion gases specifically pressurized air from high pressure compressor 34 is mixed with fuel in combustor 36 and ignited thereby generating combustion gases such combustion gases drive high pressure turbine 38 which drives high pressure compressor 34 the combustion gases are discharged from high pressure turbine 38 into low pressure turbine 39 the core airflow is discharged from low pressure turbine.