A steam turbine valve abnormality monitoring system according to an embodiment includes a detection unit detecting the state of a steam turbine valve or a steam turbine valve drive device, a determination unit, and an abnormality processing unit. Based on the detected result of the detection unit, the determination unit determines whether or not an abnormality has occurred in the opening degree control of the steam turbine valve. The abnormality processing unit issues an alarm or issues a turbine stop command when the determination unit determines that an abnormality has occurred in the opening degree control of the steam turbine valve.

An actuation system is provided for varying the pitch of the blades of a variable pitch fan or propeller. The actuation system includes a first actuator and a second actuator. The actuation system further includes a first linkage which operably connects the first actuator to the blades such that operation of the first actuator varies the pitch of the blades via the first linkage. The actuation system further includes a second linkage which operably connects the second actuator to the first actuator such that operation of the second actuator varies the pitch of the blades by series connection of the second linkage to the first linkage.

An engine control system includes an electronic hardware engine controller and an actuator that operates at different positions to control operation of an engine. An actuator sensor measures an actuator position, and the engine controller generates a synthesized actuator position. In response to detecting a faulty actuator, a faulty actuator sensor, or both, the engine controller adjusts the position of the actuator based on the synthesized actuator position.

An engine control system includes an electronic hardware engine controller in signal communication with an actuator and an engine sensor. The actuator operates at a plurality of different positions to control operation of an engine. The engine sensor measures an engine operating parameter. The engine controller generates a synthesized engine operating parameter, and adjusts the position of the actuator based on the synthesized engine operating parameter in response to detecting a faulty engine sensor.

An engine control system includes an electronic hardware engine controller in signal communication with at least one engine sensor, which measures an engine operating parameter (Ycrtr_t). The engine controller generates a synthesized engine operating parameter (Ycrtr) calculates an error (ERRcrtr) between the engine operating parameter (Ycrtr_t) and the synthesized engine operating parameter (Ycrtr). The engine controller further determines a corrector error parameter (Xcrtr) and determines a faulty sensor among the at least one engine sensor based on a comparison between the error value (ERRcrtr) and the corrector error parameter (Xcrtr).

An apparatus and method for controlling a cooling fan of a battery of a vehicle are provided. The apparatus includes a motor controller that drives a cooling fan motor of the battery based on information regarding control conditions of the cooling fan motor, and requests a backup process of a control of the cooling fan motor when an error in CAN communication by a CAN communicator or an error of the vehicle occurs. A backup processor then compensates for an output signal of the cooling fan based on at least one of an air conditioner pressure transducer (APT) output value, a vehicle speed, and a cooled water temperature and transmits the compensated output signal of the cooling fan to the motor controller.

A system and method for monitoring a thrust reverser system are provided. The embodiments described herein utilize sensors located proximate locks comprising a thrust reverser locking system. The provided system and method detect deflection and displacement proximate the locks to determine when individual locks have failed.

A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.

A blocking device for preventing an inappropriate shut-off of an engine of an aircraft. The blocking device enables by default the actuation of the shut-off unit and receives information representative of an activated or inactivated state of a fuel shut-off lever, of a reduced or non-reduced speed state of a throttle lever, and a correct or incorrect operating state of the engine. The blocking device blocks the actuation of the shut-off unit when the throttle lever is in an inactivated state, when the engine is in a correct operating state, and when, in addition, the throttle lever is in a non-reduced speed state or the throttle lever is in a reduced speed state and, in addition, the opposite propulsion engine is in a failed state or in an incorrect operating state.

A turbo machine, such as a gas turbine, includes a rotor, which rotates about a horizontal machine axis, and which is enclosed by a coaxial enclosure. The turbo machine includes a metal casing, whereby an electrical heating system is provided on the lower half of the metal casing. A safe operation is achieved by having the heating system configured as a redundant system.