An electrical assembly for an aeronautical turbomachine, including an electric machine configured to be disposed in a turbomachine and comprising a stator and a rotor comprising magnets, the assembly including a short-circuit detecting means, a hot air injecting means configured to draw hot air off the turbomachine at a temperature greater than the temperature of demagnetization of the magnets of the rotor, and to inject the drawn hot air onto the magnets of said rotor when the short-circuit detecting means detects the presence of a short-circuit in the electric machine, and a cool air injecting means, configured to draw cool air off the turbomachine and to inject it into an inner chamber of the turbomachine, the temperature of the cool air drawn by the cool air injecting means being less than the temperature of the hot air drawn by the hot air injecting means.

A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine an estimate of hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a model predictive control state and a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the model predictive control state and the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.

The present application relates to an abnormality determination device for a variable geometry turbocharger having a nozzle mechanism capable of changing a flow path area of exhaust gas with an actuator. The abnormality determination device includes: a first detection part configured to be capable of detecting at least one of a load of the actuator or supply energy to the actuator; and a determination part configured to determine that an abnormality is present, if a detection result by the first detection part is out of an allowable range corresponding to an operational state of the variable geometry turbocharger.

A method may include monitoring, by a controller, operation of a pump of at least one hydraulic fracturing rig during ramp-up of the pump. Each of the at least one hydraulic fracturing rig may further include an engine and a transmission. The method may further include detecting, by the controller, an issue in the operation of the pump based on the monitoring of the operation and performing an action based on the detecting of the issue.

A system includes a first AC bus configured to supply power from a first AC power source. A second AC bus is configured to supply power from a second AC power source. A first transformer rectifier unit (TRU) connects a first DC bus to the first AC bus through a first TRU contactor (TRUC). A second TRU connects a second DC bus to the second AC bus through a second TRUC. A ram air turbine (RAT) automatic deployment controller is operatively connected to the first TRUC and to the second TRUC to automatically deploy a RAT based on the combined status of the first TRUC and the second TRUC.

An assembly is provided for an engine. This engine assembly includes a fuel system, a sensor and a processing system. The fuel system includes a fuel source, an engine component and a fuel circuit configured to direct fuel from the fuel source to the engine component. The sensor is configured to provide sensor data indicative of a measured parameter of the fuel directed through the fuel circuit from the fuel source to the engine component. The processing system is configured to identify a fuel leak in the fuel system based on the sensor data. The fuel leak is identified when a measured value corresponding to the measured parameter of the fuel is less than an expected value corresponding to an expected parameter for the fuel directed through the fuel circuit from the fuel source to the engine component.

Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

An oil supply system and a method for operating the same to provide oil to a gas turbine engine in a variety of harsh operating conditions is provided. The oil supply system includes a main oil tank and an auxiliary oil tank which share oil through a tank sharing valve that may be closed if a depressurization event occurs in the main oil tank. The oil supply system further includes an auxiliary supply conduit and an auxiliary oil pump for providing oil to the gas turbine engine in the event of main oil tank depressurization or in negative gravity conditions where the oil within the auxiliary oil tank rises to the top of the tank and uncovers the oil pump supply.

A method is provided involving a turbine engine. During this method, data is received indicative of twist of a shaft of the turbine engine. The data is monitored over time to identity one or more reversal events while the turbine engine is operating, where each of the reversal events corresponds to a reversal in a value sign of the data. Shaft shear is identified in the shaft based on occurrence of N number of the reversal events.

A gas turbine engine, includes: an engine core including a turbine, compressor, and shaft system connecting the turbine to the compressor, and forming a torque path therebetween. The shaft system is axially located by a thrust bearing located forward of the turbine, and the engine is configured, in the event of a shaft break which divides the shaft system into a front portion located by the thrust bearing and a rear portion unlocated by the thrust bearing, the rear portion is free to move axially rearwardly under a gas load. The engine further includes a shaft break detector having a forward speed sensor configured to measure a rotational speed of the front portion of the shaft system, and a rear microwave sensor configured to measure a rotational speed of the rear portion of the shaft system, wherein a shaft break can be detected based on differences in the measured speeds.