Patent ID: 7509797
Filing Date: 2009-03-31
Classification: B64C,F02C,F02K

Abstract:
1. A supersonic turbojet engine comprising: a core engine including a multistage axial compressor joined by a rotor to a high pressure turbine, with an annular combustor disposed therebetween; an afterburner disposed coaxially with an aft end of said core engine for receiving combustion gases therefrom; an exhaust nozzle including an inlet duct converging aft to a throat of minimum flow area, and an outlet duct diverging aft therefrom for diffusing said combustion gases discharged therefrom; a thrust vectoring system operatively joined to said compressor for receiving pressurized air therefrom, and operatively joined to said nozzle inlet and outlet ducts for selectively discharging said pressurized air therein; and a controller operatively joined to said thrust vectoring system for varying distribution of said pressurized air around said nozzle and thereby vector thrust from said combustion gases discharged through said nozzle.