There is proposed a method for controlling a bistable shutoff vale for an aircraft engine, involving the steps of: emitting a closure signal on one of the control channelsemitting an open signal on the other control channel, the method being characterized in thatthe amplitude of the close signal is designed to cause the vane to move into a first position constantly in a given period of time,in the same period, the amplitude of the open signal fluctuates between a value designed to urge the valve toward a second position and a rest value, the actuating values of the two signals being adapted to one another in order to keep the vane immobile when the two signals received by the valve simultaneously adopt said actuation values.

There is proposed a method for controlling a bistable shutoff vale for an aircraft engine, involving the steps of: emitting a closure signal on one of the control channelsemitting an open signal on the other control channel, the method being characterized in thatthe amplitude of the close signal is designed to cause the vane to move into a first position constantly in a given period of time,in the same period, the amplitude of the open signal fluctuates between a value designed to urge the valve toward a second position and a rest value, the actuating values of the two signals being adapted to one another in order to keep the vane immobile when the two signals received by the valve simultaneously adopt said actuation values.

A method for testing an overspeed protection mechanism of a single-shaft combined-cycle plant that includes, during testing, an electrical load is first connected to the generator and the load is disconnected and a trigger threshold value can be achieved at a test moment in time, thereby triggering the overspeed protection mechanism.

A method for testing an overspeed protection mechanism of a single-shaft combined-cycle plant that includes, during testing, an electrical load is first connected to the generator and the load is disconnected and a trigger threshold value can be achieved at a test moment in time, thereby triggering the overspeed protection mechanism.

The present application provides a method of evaluating valve spindle vibration in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors, wherein the operating parameters may include valve spindle vibration, comparing the valve spindle vibration to a predetermined value, and altering one or more of the operating parameters if the valve spindle vibration exceeds the predetermined value.

The present application provides a method of evaluating valve tightness in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors, wherein the operating parameters may include rotor acceleration and rotor speed, comparing the rotor acceleration and the rotor speed to predetermined values, and altering one or more of the operating parameters and/or initiating repair procedures if the rotor acceleration and/or the rotor speed is increasing and/or exceeds predetermined values.

A system includes a trip manifold assembly (TMA). The TMA includes a plurality of block valves configured to receive a flow of fluid from a hydraulic power unit (HPU), and a plurality of solenoid valves configured to admit the flow of fluid to actuate the plurality of block valves, a plurality of dump valves, and a plurality of relay valves of the TMA. The plurality of solenoid valves is configured to admit a respective portion of the flow of fluid. The plurality of dump valves is configured to depressurize a trip header of the TMA as an output to operate a plurality of stop valves coupled to a turbine system. The TMA is configured to regulate the flow of fluid to control the operation of the plurality of stop valves as a mechanism to interrupt an operation of the turbine system.

Disclosed herein are systems and methods method of verifying the configuration of an overspeed system for a shaft. The method comprises determining a first rotational speed of a shaft using an overspeed system. The overspeed system comprises a toothed wheel that rotates in relation to the rotational speed of the shaft. The method further comprises determining a second rotational speed of the shaft using a vibration sensing system for monitoring vibration of the shaft. The method further comprises comparing the first rotational speed of the shaft and the second rotational speed of the shaft to verify a configuration of the overspeed system.

A method and machine for validating an investigated sensor within a sensor group includes receiving sensor data from sensors of the sensor group measuring the same physical property, calculating a deviation of the sensor data received from the investigated sensor within the sensor group from sensor data reconstructed based on the sensor data received from all other sensors of the sensor group, and signaling a sensor fault of the investigated sensor if the calculated deviation is outside of a trusted range.

An aircraft engine reservoir system includes a reservoir inner chamber containing a flammable fluid. A chamber inlet is fluidly connectable to a flammable fluid source pressurizing the fluid. The chamber includes an outlet. An air source operates at a pressure that is lower that a flammable fluid pressure during an engine operational condition. A valve selectively fluidly connecting the chamber to the air source is movable between a closed position, in which the chamber flammable fluid pressure acting on the valve exceeds the air source pressure acting on the valve such that the valve blocks the air from entering the chamber, and an open position, in which the chamber flammable fluid pressure acting on the valve is lower than the air source pressure acting on the valve such that the valve allows the air to flow into the chamber and evacuate the flammable fluid from the chamber through the outlet.