Systems, methods, and devices are provided for an engine driven pump gearbox. A engine, such as a gas turbine engine, may drive a primary shaft having a gear. The gear may selectably engage with a gear of a secondary shaft that drives a machine (e.g., pump). By changing whether the gear of the primary shaft is engaged with the gear of the secondary shaft, the gearbox may be switched between an engaged and a neutral (or disengaged) configuration. A power takeoff device (e.g., a generator) may be connected to the primary shaft and may be operated in reverse as a motor to rotate, slow, stop, and/or reverse rotation of the primary shaft. Brakes may be associated with one or more of the primary and secondary shafts. The power takeoff device and one or more of the brakes may be controlled to shift the shafts between engaged and disengaged positions relative to each other.

Disclosed is a drone having at least one rotor. The at least one rotor comprises a mast and at least two blades having a proximal end and a distal end. The at least two blades are arranged in connection with the mast by their proximal ends. The at least one of the blades comprises an electrically conductive element extending a distance D between its distal end and its proximal end. The electrically conductive element is electrically coupled with means for stopping the blades, thus forming an electrical circuit. The means for stopping the blades is arranged to be actioned when at least one electrical property of the electrical circuit change.

A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K.sub.1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K.sub.2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.

An assembly is provided for an aircraft. This assembly includes a geartrain, a first propulsor rotor and a rotating structure. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The ring gear circumscribes the sun gear and is rotatable about an axis. Each of the intermediate gears is between and meshed with the sun gear and the ring gear. Each of the intermediate gears is rotatably mounted to the carrier. The carrier is rotatable about the axis. The first propulsor rotor is coupled to the carrier. The rotating structure is coupled to the ring gear. The rotating structure includes a turbine rotor. The rotating structure is configured to drive rotation of the first propulsor rotor through the geartrain.

A variable cross-section nozzle of an aircraft has at least two movable parts enabling modification of the cross-section of the nozzle. A control device for the nozzle includes a system for regulating the engine, the system being connected to a control element which drives at least one electric motor which creates the movement of the movable parts, including an electric motor for each movable part and two mechanical transmission systems for each movable part connected only to the same electric motor.

An electrical power generation system for a vehicle includes a prime mover, an electrical generator to generate electrical power and a gear box operably connected to the prime mover and the electrical generator to transfer rotational energy from the prime mover to the electrical generator. A braking mechanism is located at the gear box to selectably transfer rotational energy from the prime mover to the electrical generator for selective generation of electrical power. A method of electrical power generation for a vehicle includes generating rotational energy at a prime mover, transferring the rotational energy to an electrical power generator, generating electrical power via the rotational energy transfer to the electrical power generator, and periodically stopping and/or starting the transfer of rotational energy from the prime mover to the electrical power generator via a braking mechanism in operable communication with the electrical power generator.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.

The invention relates to a device (3) for driving actuators (7-10) for a thrust reverser, comprising a motorized drive unit (15), a brake (16) and a manual drive unit (17) for rotatably driving a drive shaft, and a control part (44) which can be actuated by an operator, the control part (44) being mobile between a motorized drive position and a manual drive position, the movement of the control part (44) from the motorized drive position into the manual drive position causing the movement of a clutch part (40) into an engaged position in order to connect the manual drive unit (17) to the drive shaft (14), and the movement of the brake (16) into the loosened configuration in order to authorize the driving of the drive shaft (14) in rotation by the manual drive unit (17).

An assembly is provided for an aircraft. This aircraft assembly includes a first propulsor rotor, a geartrain, a rotating assembly and an auxiliary turbine. The rotating assembly is rotatable about an axis and includes a turbine rotor. The rotating assembly is coupled to and is configured to drive rotation of the first propulsor rotor through the geartrain. The auxiliary turbine is coupled to the first propulsor rotor independent of the geartrain.

An engine assembly is provided that includes a geartrain, a device and a fluid damper. The geartrain is configured as or otherwise includes an epicyclic gear system. A first component of the geartrain is rotatable about an axis. The device is configured to brake and/or lock rotation of the first component of the geartrain about the axis. The device is configured as or otherwise includes a device structure. The fluid damper engages the device structure. The fluid damper is configured to damp vibrations in the device.