A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. The flap assembly generally includes a multiple of flaps, flap linkages and an actuator system. The actuator system radially and axially translates a drive ring relative an engine centerline axis. A slot within the drive ring receives the flap linkages to asymmetrically and symmetrically vary the fan nozzle exit area in response to movement of the drive ring.

Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

Actuation system for a translating variable area fan nozzle

A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine The buffer system can include a first circuit and a second circuit The first circuit selects between a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to render a first buffer supply air having an intermediate pressure The second circuit selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer supply air

Gas turbine engine buffer system

A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device is positioned near the inlet internal diffuser section and is actuable to introduce a second airflow at the inlet internal diffuser section. The sensor produces a signal that represents an operability condition. The controller receives the signal and simultaneously moves the variable area fan nozzle and actuates the first boundary layer control device and the second boundary layer control device in response to receiving the signal to achieve a slim-line nacelle.

Gas turbine engine having slim-line nacelle

A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system

Fundamental gear system architecture

A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller. The bleed passage includes an inlet for receiving a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The controller identifies an operability condition and selectively introduces the bleed airflow near a boundary layer of the inlet lip section in response to the operability condition.

Gas turbine engine providing simulated boundary layer thickness increase

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 turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan (20) to a generator (52). The turbofan emergency power system includes a controller (50) that communicates with the flow control device (41). Upon sensing an emergency condition, the controller manipulates the flow control device to reduce the effective nozzle exit area (40) of the bypass flow path, which chokes the flow through the bypass flow path thereby increasing the rotational speed of the fan. In this manner, the generator is driven at a higher rotational speed than if the flow through the bypass flow path was not choked, which enables a smaller generator to be utilized.

Turbofan engine with variable area fan nozzle and low spool generator for emergency power generation and method for providing emergency power.

PROBLEM TO BE SOLVED: To provide an area variable nozzle for a gas turbine engine fan nacelle effective and of relatively low cost. SOLUTION: A thrust vectorable fan variable area nozzle (FVAN) 28 includes a synchronizing ring, a static ring 42, and a flap assembly mounted within a fan nacelle 32. An actuator assembly 48 selectively rotates synchronizing ring segments relative to the static ring 42 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 28 segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN 28 in which all segments are moved simultaneously to maximize engine thrust and fuel economy. By separately adjusting the segments of the thrust vectorable FVAN 28, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering. COPYRIGHT: (C)2008,JPO&INPIT

Fan nacelle for gas turbine engine, fan nacelle assembly, and method for changing annular fan outlet area of gas turbine engine

A laser hole drilling system includes a laser source that generates a laser beam along an optical axis; a spherical lens along the optical axis downstream of the laser source; and a control system in communication with the spherical lens and the laser source, the control system operable to locate the spherical lens with respect to the laser source to produce a light distribution in polar coordinates of a real portion of the Fourier Transform to generate an asymmetric teardrop shaped energy distribution at a focal plane.

Michael Winter

Papers

Gas turbine engine providing simulated boundary layer thickness increase

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

Turbofan engine with variable area fan nozzle and low spool generator for emergency power generation and method for providing emergency power.

Fan nacelle for gas turbine engine, fan nacelle assembly, and method for changing annular fan outlet area of gas turbine engine

System and method for laser drilling of shaped cooling holes