A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a pivot between the first end and the second end. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage to in turn move the nozzle door about the pivot between a plurality of positions, such as a stowed position, an intermediate position, and a thrust reverse position, to influence a bypass airflow through a fan bypass passage.

Variable area fan nozzle and thrust reverser

A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering.

Thrust vectorable fan variable area nozzle for a gas turbine engine fan nacelle

A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well as provide a relatively lower temperature operating environment.

Gas turbine engine with pylon mounted accessory drive

gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. A second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area. A ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5.

Geared turbofan with three turbines with high speed fan drive turbine

The device (20) has a rotating door (24) comprising inner and outer flaps (26, 28) secured and articulated around a pivot axle (58) that is remote from the inner flap in a direction from the outer flap to the inner flap when the door is in closing position so that upstream and downstream ends of the inner and outer flaps protrude from inner and outer sides relative to inner and outer surfaces (12, 14) of a fixed structure (22) in opening position. The inner flap is spaced from the structure to provide an air passage between the inner flap and the structure in downstream of the inner flap.

Air-discharge device for an airplane turbofan engine

A turbofan engine includes a fan variable area nozzle, which includes a louver system having a multiple of slats generally transverse to the engine axis. Each of the louver slats are pivotally mounted to the fan nacelle to vary the effective area of the fan nozzle exit area and permit efficient engine operation at predefined pressure ratios.

Jr. Edward F. Migliaro

Papers

Gas turbine engine with fan variable area nozzle, nacelle assembly and method of varying area of a fan nozzle

Nacelle assembly for a high-bypass gas turbine engine, corresponding high-bypass gas turbine engine and method of varying a fan nozzle exit area