An aircraft with an integrated boundary layer ingesting propulsion having a mechanically-distributed propulsion system. The mechanically-distributed propulsion system may include an engine to generate a mechanical drive power, a drive shaft, a direction-reversing transmission, and a propulsor fan. The drive shaft may be operatively coupled to the engine to receive the mechanical drive power. The direction-reversing transmission may have a first rotating shaft and a second rotating shaft, the first rotating shaft operatively coupled to the drive shaft to receive the mechanical drive power, which is configured to redirect the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft. The propulsor fan may be coupled to the second rotating shaft to convert the mechanical drive power into thrust.

A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots

A turbofan engine nacelle includes a thrust reverser system provided with at least one movable cowl retracting towards a rear reverse-jet position, tilting pivoting flaps which at least partially close an annular flow duct, and opening lateral openings of this annular flow duct equipped with reverser grids. Each movable cowl includes a control sector that slides in a transverse plane, a deflection device linking a fixed part of the nacelle to this control sector in order to make it slide towards a reversal position when the movable cowl retracts, and flap connecting rods linking this control sector to the pivoting flaps, which tilt these flaps, closing the annular flow duct, when the control sector slides towards its reversal position.

A power extraction and amplification system for a gas turbine engine is disclosed. In various embodiments, the power extraction and amplification system includes a low spool tower shaft configured for engagement with a low speed spool, a high spool tower shaft configured for engagement with a high speed spool, a first motor, a generator, a differential gear box operably coupled to the low spool tower shaft, to the first motor and to the generator, and a second motor operably coupled to the generator and the high spool tower shaft.

A variable vane system including an actuator; a harmonic drive driven by the actuator, a multi-planar drive gear driven by the harmonic drive, a first actuator gear mounted to a first variable vane of a first variable vane stage, the first actuator gear driven by the multi-planar drive gear, the first actuator gear comprises a drive arm, and a second actuator gear mounted to a second variable vane of a second variable vane stage, the second actuator gear driven by the multi-planar drive gear.

A mechanism for driving a first member for adjusting the orientation of the blades of a first stage of a turbine engine diffuser and a second member for adjusting the orientation of the blades of a second stage of the turbine engine diffuser, including a single drive wheel which simultaneously drives the first adjustment member and the second adjustment member and a set of gears which is arranged between the drive wheel and the two adjustment members, wherein the set of gears includes a first gearwheel which is directly coupled with the drive wheel and with the first adjustment member and which is coupled with the second adjustment member with a secondary gearwheel which is directly coupled with the second adjustment member.

A baffle includes a disk, a rim, a peripheral portion, and an outlet. The rim is connected to and circumferentially surrounds a portion of the disk. The peripheral portion is connected to and circumferentially surrounds the rim. The peripheral portion forms a channel. The outlet is fluidly connected to the channel of the peripheral portion. The outlet includes a cover and a series of openings. The cover caps a distal end of the outlet. The series of openings is disposed on a portion of the outlet and is fluidly connected to the channel via the outlet.

A gas turbine engine accessory gearbox assembly comprising an accessory gearbox and a plurality of accessories arranged to be driven by the accessory gearbox. The accessory gearbox comprises a gear train and an accessory gearbox casing enclosing the gears of the gear train. Each accessory is driven by a shaft and the shaft of each accessory has a spur gear. The gear train comprises the spur gears of the accessories. The shaft of at least one of the accessories has a bevel gear and the bevel gear is arranged to mesh with a further bevel gear and the further bevel gear is arranged to drive the accessory gearbox assembly. The accessories may be arranged in V-shape on the core engine casing within an aerodynamic core nacelle.

The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.

A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.