GAS TURBINE PROPULSION SYSTEM

摘要

AIRCRAFT PROPULSION SYSTEM WITH FLIGHT MANEUVERABLE EXHAUST NOZZLE An aircraft propulsion system is provided which incorporates a flight maneuverable exhaust nozzle. In one embodiment, gas turbine engines are mounted on both sides of an aircraft fuselage, each engine having an exhaust duct partially defining an exhaust stream flow path. The duct transits from a substantially cylindrical diffuser section aft of the engine to a relatively high aspect ratio section proximate the trailing edge of the wing. Exhaust gases are expelled through a thrust vectorable nozzle which is conto?? within the wing and which is adapted to increase wing lift through the concept of supercirculation. Maximum aerodynamic advantage is achieved by distributing the exhaust flow over a significant portion of the wing span at the trailing edge. Thrust augmentation is provided by means of a long, flat duct burner disposed within the high aspect ratio section proximate the exhaust nozzle thereby minimizing turning losses and cooling air requirements. The exhaust nozzle includes an articulated deflector partially defining both the exhaust stream flow path and the wing upper surface. Synchronous movement of the two flaps comprising the deflector ensures proper internal area control prior to exhaust gas vectoring. The nozzle throat area is varied by a lower flap disposed in general opposition to the articulated deflector. Actuation means are provided to vary the throat area and produce the proper thrust vector angle by positioning the lower flap and articulated deflector, respectively.