Systems, devices, and methods are presented for detecting a misaligned or otherwise skewed variable area fan nozzle (VAFN) (150) that is mounted on a thrust reverser sleeve (182, 184) of an aircraft engine (110). Rods (212, 222) project from different part...

An integrated thrust reverser and variable area fan nozzle actuator (100) includes a ballscrew shaft (120) having a first ballnut (122) and a second ballnut (130). The second ballnut (130) is fastened to a first translatable object. A bearing (134) is affi...

A variable area nozzle (200) for a gas turbine engine is provided that has a circumferential outer boundary (100), which may be formed at least in part by the nacelle of a turbofan engine, that has a fixed portion (110) and a movable portion (120). The mov...

The exit area of a nozzle assembly is varied by translating a ring assembly (254,256) located at a rear of the engine nacelle (18). The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring def...

A multi axis slide carriage system (10) includes a channeled track (16), a slider (18), a shaft (20) and a slide carriage bracket (22). The channeled track (16) extends along a first axis (38). The slider (18) slides along the first axis (38) within the ch...

A ducted fan gas turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes (37) for channelling airflow from the duct in a rearward direction and a second set of turning vanes (38) for channelling airf...

The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable...

A bypass gas turbine engine includes a variable area fan nozzle (40) with a first and second nacelle sections (52,54). The second nacelle section (54) is movable relative to the first nacelle section (52) to define an auxiliary port (60) which varies the f...

A variable geometry convergent-divergent nozzle (30) for a gas turbine engine includes a centerbody (32) extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud (34) surrounds the centerb...