A system includes one or more sensors to detect unintended forward and reverse rotation of rotating machinery. The system also includes a monitoring system consisting of a processor, memory, display and communication interface. The processor receives signals from the sensors. The processor determines unintended rotation when the pattern of received signals match with the conditions defined in the processor. The processor generates a notification signal of “Unintended Rotation” on the display. The notification signal is also sent to the operator workstation to alert the operating personnel. The notification history is also stored in the system memory. The system is also configured to initiate automatic action to stop the unintended rotation and protect the machinery components from unintended rotation. The action may include closing the suction and discharge valve and starting the lubrication system to lube the bearings of the rotating machinery and the motor.

A turbine fracturing system and a controlling method thereof, a controlling apparatus and a storage medium are provided. The turbine fracturing system includes: N turbine fracturing apparatuses, wherein each of the N turbine fracturing apparatuses comprises a turbine engine, and N is an integer greater than or equal to 2; a fuel gas supply apparatus connected to the N turbine engines, wherein the fuel gas supply apparatus is configured to supply fuel gas and distribute the fuel gas to the N turbine engines as gaseous fuel; and a fuel liquid supply apparatus connected to at least one of the N turbine engines and configured to supply liquid fuel to at least one of the N turbine engines in a case that at least one of a flow rate and a pressure of the fuel gas decreases.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

An operation control device for a single shaft gas turbine selects an operation mode based on a load state of a power generator, and controls the turbine based on the operation mode. In a first operation mode, a rotational speed of the turbine is maintained within a first rotational speed range, and in a second operation mode, the rotational speed is maintained within a second rotational speed range set on a lower rotational speed side than the first rotational speed range. The second rotational speed range is set on the lower rotational speed side than the first rotational speed range with a first non-selection rotational speed range set therebetween.

Methods, systems, and devices for dynamic wind turbine rotational speed control are described. The method may include attaching a vane shaft to a support arm of the wind turbine, the vane shaft partially inserted into a cylindrical aperture of an airfoil of the wind turbine, rotating an airfoil around a vertical axis of the wind turbine, and controlling, via a torsion spring of the wind turbine, when a rear stop of the speed control assembly exerts a force on the airfoil to reduce the rotational speed of the wind turbine, where the torsion spring is configured to facilitate the rear stop to exert the force on the airfoil when a rotational speed of the wind turbine around the vertical axis exceeds a set rotational speed, where a portion of the vane shaft is inserted into a helical portion of the torsion spring.

Systems and method for synchrophasing aircraft engines are disclosed. One method comprises receiving data indicative of a sensed vibration level associated with a first aircraft engine and a second aircraft engine operating at a substantially same operating speed and commanding one or more momentary changes in operating speed of the second aircraft engine until the sensed vibration level substantially reaches a target vibration level. The momentary changes in operating speed of the second aircraft engine is commanded irrespective of phase information associated with imbalances of the first and second aircraft engines.

A system and method for adaptively controlling a cooldown cycle of an auxiliary power unit (APU) that is operating and rotating at a rotational speed includes reducing the rotational speed of the APU to a predetermined cooldown speed magnitude that ensures combustor inlet temperature has reached a predetermined temperature value, determining, based on one or more of operational parameters of the APU, when a lean blowout of the APU is either imminent or has occurred, and when a lean blowout is imminent or has occurred, varying one or more parameters associated with the shutdown/cooldown cycle.

Systems and methods to pump fracturing fluid into a wellhead may include a gas turbine engine including a compressor turbine shaft connected to a compressor, and a power turbine output shaft connected to a power turbine. The compressor turbine shaft and the power turbine output shaft may be rotatable at different rotational speeds. The systems may also include a transmission including a transmission input shaft connected to the power turbine output shaft and a transmission output shaft connected to a hydraulic fracturing pump. The systems may also include a fracturing unit controller configured to control one or more of the rotational speeds of the compressor turbine shaft, the power turbine output shaft, or the transmission output shaft based at least in part on target signals and fluid flow signals indicative of one or more of pressure or flow rate associated with fracturing fluid pumped into the wellhead.

A method for controlling a speed of a turbocharger that is in operative connection with a compressor, the steps including: provision of a setpoint for the speed of the turbocharger on the basis of a model-based precontrol for a calculation of a desired boost pressure ahead of the turbocharger; determination of an actual value for the speed of the turbocharger; control of an actuator of the turbocharger in order to compensate for the difference between the desired value and the actual value for the speed of the turbocharger. A main signal and a subsidiary signal are provided during the determination of the actual value for the speed of the turbocharger, wherein the main signal and the subsidiary signal are combined in order to validate the actual value for the speed of the turbocharger.

There is provided a dynamic motoring system and method for an aircraft engine. Motoring of the engine is initiated for an initial motoring duration and at an initial motoring interval. At least one engine parameter is measured in real-time during the motoring, the at least one engine parameter comprising a temperature of the engine. The initial motoring duration and the initial motoring interval are modified in real-time, based on a value of the at least one engine parameter during the motoring, to obtain a modified motoring duration and a modified motoring interval. The motoring continues for the modified motoring duration and at the modified motoring interval, with a speed of rotation of the engine being controlled using the modified motoring interval.