| abstract |
A gas turbine engine includes an air intake and propulsive fan that generates two airflows A and B. Gas turbine engine includes, in axial flow A, core including a compressor, first combustor, high pressure turbine including first turbine stage, second combustor, second turbine stage of the high pressure turbine, low pressure turbine and core exhaust nozzle including and divergent portions. Fan housing surrounds the core and fan and defines, in axial flow B, a bypass arrangement including the fan, a duct, a third combustor in the form of a duct burner and a bypass nozzle including a converging portion and a diverging portion. The bypass and core are arranged coaxially, such that the core flow A is exhausted annularly within the bypass flow. When the duct burner is in operation, the exhaust velocity of the bypass flow is greater than the exhaust velocity of the core flow. |