method of application of the present invention engine 10 includes in serial flow relation proceeding in a direction from an inlet 16 to exhaust nozzle 30 through a low pressure compressor 18 a high pressure compressor 20 a combustor 22 a high pressure turbine 24 a low pressure turbine 26 an afterburner 28 and terminating in exhaust nozzle 30 afterburners 28 are optional items used in military applications air entering inlet 16 is compressed by compressors 18 20 before reaching combustor 22 where the highly compressed air is mixed with fuel and ignited this air fuel exhaust mixture is then propelled through turbines 24 26 which are urged into rotation by the passing mixture of hot gases to likewise rotatably drive respective compressors 18 20 since these components are connected to a common drive shaft upon reaching optional afterburner 28 fuel is introduced into the mixture stream to augment thrust utilizing the unburned oxygen in the exhaust gas to support combustion afterburners are typically used in military aircraft they increase the speed of the aircraft for short periods of time by injecting fuel into the hot exhaust gas stream where it is combusted thereby providing additional thrust the temperature of the afterburner flame can exceed about 1 700 u00b0 c about 3.