A lubricating fluid damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation and a radial aperture, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a lubricating fluid jet configured to propel a lubricating fluid through the radial aperture toward the contact portion.

A fan and a motor are provided. The fan or the motor includes a shaft seat disposed on a frame, a rotor, and a stopping assembly. The rotor is disposed on the shaft seat and includes a hub and a rotation shaft. The hub has a first locking mechanism adjacent to its peripheral surface, and the rotor is connected to the shaft seat via the rotation shaft. The stopping assembly corresponds to the rotor, and includes a second locking mechanism facing the first mechanism. When the rotor smoothly rotates, the first locking mechanism is separated from the second locking mechanism. When the rotor rotates in reverse, the stopping assembly moves along a first direction, and the first and second locking mechanisms contact each other. When the first locking mechanism is affixed to the second locking mechanism, the rotor stops rotating.

In one aspect, a fan array fault response control system is provided for a cooling tower. The fan array fault response control system includes a fan interface configured to be in communication with a plurality of fans of the cooling tower and a processor operably coupled to the fan interface. The processor is configured to detect at least one non-operational fan of the plurality of fans. The processor configured to effect, in response to detecting the at least one non-operational fan, a reduced fan speed of at least one operational fan of the plurality of fans.

A lubricating fluid damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation and a radial aperture, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a lubricating fluid jet configured to propel a lubricating fluid through the radial aperture toward the contact portion.

The mechanical shaft lock can include one or more shear pins. When an end of the shear pin, e.g., shear pin head, lines up with one or more shearing slots on the MSL or pump shaft, the shear pin engages and stops the rotation of the pump shaft and motor attached to the pump. The shaft lock can be engaged for installing an ESP, disengaged for production after installing by breaking the shear pin upon start-up, and re-engaged for removing the ESP from the wellbore. In some embodiments, the MSL may be configured to be disengaged and re-engaged to deal with well kicks.

A lubricating fluid damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation and a radial aperture, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a lubricating fluid jet configured to propel a lubricating fluid through the radial aperture toward the contact portion.

A fan and a motor are provided. The fan or the motor includes a shaft seat disposed on a frame, a rotor, and a stopping assembly. The rotor is disposed on the shaft seat and includes a hub and a rotation shaft. The hub has a first locking mechanism adjacent to its peripheral surface, and the rotor is connected to the shaft seat via the rotation shaft. The stopping assembly corresponds to the rotor, and includes a second locking mechanism facing the first mechanism. When the rotor smoothly rotates, the first locking mechanism is separated from the second locking mechanism. When the rotor rotates in reverse, the stopping assembly moves along a first direction, and the first and second locking mechanisms contact each other. When the first locking mechanism is affixed to the second locking mechanism, the rotor stops rotating.

A gas turbine engine includes a fan and a first drive shaft connected to the fan. A fan drive gear box connects the first drive shaft to a second drive shaft and is configured to allow the first drive shaft to rotate at a different speed than the second drive shaft. The gas turbine engine also includes a sprag clutch disposed circumferentially around the first shaft and connected to the first drive shaft. The sprag clutch is configured to allow rotation of the first drive shaft and the fan in a first direction while prohibiting rotation of the fan and the first drive shaft in a second direction.

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.

A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive train driven by a turbine, a driving side of the gearbox being driveably connected with a propulsive fan, with at least one torque transmission device positioned in the drive train, the torque transmission device having an asymmetric torque transmission characteristic, so that torque is transmittable by the torque transmission device under a nominal rotational direction and no torque is transmittable by the torque transmission device in a non-nominal rotational direction.