A fan brake system for controlling an industrial fan system, the fan brake system including a fan brake having a brake pad movable on the fan brake to selectively engage the fan system. An actuator including a motor can be operable to cause the fan brake to perform a braking procedure on the fan system to resist rotational movement of the fan system. A controller can be communicated with the actuator, the controller operable to selectively cause the actuator and the fan brake to perform the braking procedure, wherein the controller is operable to monitor and control power being supplied to the motor of the actuator during the braking procedure to maintain a torque output of the motor according to a predetermined torque profile during the braking procedure.

The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.

An assembly is provided for an aircraft propulsion system. This assembly includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first brake and a second brake. The sun gear is rotatable about a centerline axis. The ring gear circumscribes the sun gear and is rotatable about the centerline axis. The intermediate gears are arranged circumferentially about the centerline axis. Each of the intermediate gears is meshed between the sun gear and the ring gear. The carrier is rotatable about the centerline axis. Each of the intermediate gears is rotatably mounted to the carrier. The first brake is configured to slow and/or stop rotation of the ring gear about the centerline axis. The second brake is configured to slow and/or stop rotation of the carrier about the centerline axis.

A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

A steam turbine includes a turbine body; a steam flow passage; a regulating valve which regulates opening and closing of the steam flow passage with a linear motion; a switching drive mechanism which drives the regulating valve; an electronic governor which controls at least the switching drive mechanism; and a controller unit. The switching drive mechanism has an electric motor which rotates when supplied with power, a conversion mechanism which converts a rotary motion of the electric motor into a linear motion of the regulating valve, and a brake which brakes the rotary motion of the electric motor. At least one of the controller unit and the electronic governor performs control such that the brake is actuated and the position of the regulating valve is maintained when at least one of the electric motor and the controller unit breaks down.

An assembly for a gas turbine engine of an aircraft includes a rotational assembly, a starter generator, and a control relay. The starter generator is coupled with the rotational assembly. The starter generator is configured to selectively drive rotation of the rotational assembly. The starter generator includes a motor winding including a first electrical terminal and a second electrical terminal. The control relay includes a switch electrically connected to the first electrical terminal. The switch is positionable in a first contact position and a second contact position, in the first contact position, the first electrical terminal is electrically isolated from the second electrical terminal through the switch. In the second contact position, the first electrical terminal is electrically connected to the second electrical terminal through the switch such that a closed electrical circuit is formed through the motor winding, the first electrical terminal, the second electrical terminal, and the switch.

A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

Systems and methods are provided that lock thrust reversers and also drive fan nozzles of an aircraft. One system includes a coupling configured to selectively engage and disengage. While engaged, the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), at least a portion of which is on a translating portion of a thrust reverser of an aircraft. Furthermore, while engaged the coupling is configured to prevent displacement of the translating portion.

A vacuum pump includes a rotating body including a rotor blade; a rotor shaft disposed in a center of the rotating body; a magnetic bearing configured to levitate and support the rotor shaft; a touchdown bearing that is separated, by a gap, from the rotor shaft and configured to support the rotor shaft when the magnetic bearing is uncontrollable; and a bearing protection structure configured to protect the touchdown bearing. The bearing protection structure includes a protrusion disposed on at least one of the rotating body and a component around the rotating body. Upon a touchdown of the rotor shaft on the touchdown bearing, the rotating body comes into contact with the component around the rotating body through the protrusion so that kinetic energy of the rotating body acting on the touchdown bearing is reduced.

An assembly is provided for an aircraft. This aircraft assembly includes a geartrain, a first bladed rotor, a second bladed 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 bladed rotor is coupled to the ring gear. The second bladed rotor is coupled to the carrier. The rotating structure is coupled to the sun gear. The rotating structure includes a turbine rotor. The rotating structure is configured to drive rotation of the first bladed rotor and the second bladed rotor through the geartrain.