An electronic controller for an engine and a propeller, a control system and related methods are described herein. The control system comprises the controller having a first channel and a second channel independent from and redundant to the first channel. Each channel comprises a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command and at least one propeller control command. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output, based on the second engine and propeller parameters, at least one engine protection command and at least one propeller protection command. The control system comprises sensors for measuring the parameters of the engine and/or the propeller and effectors configured to control the engine and the propeller.

An engine control system includes a first user control lever configured for rotational movement between a first control position and a second control position and a second user control lever configured for rotational movement between a third control position and a fourth control position. The first user control lever is configured for operational control of an engine in a first control mode and the second user control lever is configured for operational control of the engine in a second control mode, such as a backup mode. A mechanical link couples the first user control lever to the second user control lever with at least one angular offset. As a result of the angular offset, the second user control lever can be maintained in a safe operating position relative to the first user control lever position.

A system and method for detecting a shaft break in a turbofan gas turbine engine includes sensing fan rotational speed and sensing turbine engine rotational speed. A rate of change of rotational speed difference between the sensed fan rotational speed and the sensed turbine engine rotational speed is determined in a processor, and a determination that a shaft break has occurred is made in the processor based at least in part on the rate of change of the rotational speed difference.

A power converting apparatus includes a diode bridge that converts first AC power supplied from a power supply into DC power, a main circuit capacitor (capacitors) that smooths the DC power, an inverter that converts the smoothed DC power into second AC power and supplies the second AC power to a load, a capacitor that reduces a noise component included in the first AC power, and a path switching unit (relays), and a control unit that switches a charging path for the main circuit capacitor so that current output from the power supply flows into the main circuit capacitor via the capacitors from when supply of the first AC power starts until a voltage of the main circuit capacitor reaches a predetermined voltage, and that the current output from the power supply flows into the main circuit capacitor without passing through the capacitors after the voltage of the main circuit capacitor reaches the predetermined voltage.

A motor device includes a motor, an input unit, a processing unit, and an electrical energy storage unit. The input unit accepts power supplied from a controller during a first period and receives at least a communication signal transmitted from the controller during a second period after the first period. The processing unit updates data for the motor in accordance with the communication signal received by the input unit. The electrical energy storage unit stores, based on the power supplied to the input unit, electrical energy for driving the processing unit.

Methods and systems for operating a gas turbine engine in a multi-engine aircraft are described. The method comprises operating the gas turbine engine in a standby mode to provide substantially no motive power to the aircraft when another engine of the multi-engine aircraft is operated in an active mode to provide motive power to the aircraft, transitioning the gas turbine engine from the standby mode to the non-standby mode, and applying pulse width modulation to an air switching system of the gas turbine engine while transitioning the gas turbine engine from the standby mode to the non-standby mode.

A gas turbine engine includes a generator that is configured to be driven by a turbine section, an electric motor that is configured to receive at least a portion of electric power from the generator, a gearbox that is mechanically coupled to both the electric motor and the generator, and a control system that has an operational amplifier that is configured to synchronize operation of the electric motor and the generator. The operational amplifier electrically couples the electric motor to the generator and is configured to define an electrical gain that matches a mechanical gain that is defined by the gearbox.

An electronic controller for an engine and a propeller, a control system and related methods are described herein. The control system comprises the controller having a first channel and a second channel independent from and redundant to the first channel. Each channel comprises a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command and at least one propeller control command. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output, based on the second engine and propeller parameters, at least one engine protection command and at least one propeller protection command. The control system comprises sensors for measuring the parameters of the engine and/or the propeller and effectors configured to control the engine and the propeller.

A fuel supply control device is provided in which a parallel flow path of an orifice and a pressurizing valve is used as a complex pressurizing valve for a fuel supply amount, and which controls a fuel supply pump on the basis of a pressure difference before and after the complex pressurizing valve that has been detected by a pressure difference meter. When the rotational speed of the fuel supply pump is below a predetermined threshold value, the fuel supply pump is controlled on the basis of a first fuel measurement amount, and the fuel supply pump is controlled on the basis of a second fuel measurement amount.

A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes a full authority digital engine control (FADEC) that controls operation of the gas turbine engine in a full-power mode and controls operation of the core turning motor to drive rotation of the engine core using a reduced power draw when the FADEC is partially depowered in a low-power bowed rotor prevention mode.