A method and system for bleed flow power generation is provided. The engine includes a core flowpath formed by a compressor section, a heat addition system, and an expansion section in serial flow arrangement. A bleed circuit is extended from the core flowpath to extract a portion of compressed fluid from the core flowpath. The method and system include bleeding compressed fluid through a bleed circuit extended in fluid communication from the core flowpath of the engine; flowing the compressed fluid through the bleed circuit to a turbine rotor positioned at the bleed circuit; extracting, via the turbine rotor, energy from the flow of compressed fluid across the turbine rotor; and receiving energy at an electric machine operably coupled to the turbine rotor.

A method and system for detecting a functional failure in a power gearbox, includes engine a) measuring operational data in a gas turbine engine of operational parameters dependent on power generation and power consumption of the engine or the gearbox, b) obtaining analyzed operational data including time data, angular data of rotation, frequency data and/or phase data, c) using the analyzed operational data in a comparison with stored baseline operational data to determine deviation data, d) determining time dependent trend data from the deviation data or determining a first state measured dependent on the power generation, power consumption or power regulation of the engine and measuring a second state dependent on vibrational data of the engine, e) generating a signal and/or a protocol for controlling the gearbox, and/or the engine based on the time dependent trend data, if a threshold is exceeded or based on the first or second states.

The invention relates to a method for determining a fluid conveying parameter, a fluid conveying device, particularly for determining a volumetric flow, comprising the steps of Determining excitation information for mechanical excitation of at least one fluid conveying element of the fluid conveying device in at least one spatial direction by at least one first sensor means, Providing operating information, comprising at least a value of an operating variable of the fluid conveying device by means of a providing means, Analyzing the information provided and determined, Determining a fluid conveying parameter, particularly a volumetric flow, of the fluid conveying device based on the analyzed information.

To control an engine shutdown in an aircraft, a control system includes a fuel supply shut-off member, a control member with a set of switches, a first switch on an electrical power supply link of the fuel supply shut-off member and second switches connected to avionics of the aircraft, the set of switches switching position on an engine shutdown command. An engine shutdown confirmation unit includes a third switch on the electrical power supply link, the third switch in open position by default. The engine shutdown confirmation unit includes electronic circuitry configured to switch the third switch over to closed position when a predefined quantity Q of switches of the control member switches position within a sliding window of predefined duration and, otherwise, keeps the third switch in open position. Thus, it is ensured that the engine shutdown is intentional.

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative $\left(\frac{dN2i}{dt}\right)”,$
and automatically stopping the engine when the current derivative $\left(\frac{dN2i}{dt}\right)$
changes sign.

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.

A single drive, dual clutch accessory drive system for an aircraft including an input shaft connected to a low pressure spool of a turbine engine. The input shaft is rotatable at a first input speed and at a second input speed that is distinct from the first input speed. An output shaft is operatively connected to an aircraft accessory. A first drive path operatively connects the input shaft and the output shaft. The first drive path includes a first clutch and a gear system. The first drive path is operable to adjust the first input speed to a selected output shaft speed. A second drive path operatively connects the input shaft and the output shaft. The second drive path includes a second clutch. The second drive path is operable to rotate the output shaft at the second input speed.

An engine system includes a turbine engine having a high pressure spool and a low pressure spool. A transmission includes an input shaft connected to one of the high pressure spool and the low pressure spool, and an output shaft. A clutch is arranged between the input shaft and the output shaft. A generator is connected to the output shaft. A clutch controller activates the clutch when one of the high pressure spool and the low pressure spool, and the generator are operating at a selected speed range.

The method of assembling the rotor assembly can include obtaining geometrical reference values about the individual rotor components, based on the geometrical reference values, determining a combination of relative circumferential positions of the individual rotor components associated to a bow shape configuration of the centers of mass along the axially-extending sequence; and assembling the rotor components to one another in said determined combination of relative circumferential positions, into the rotor assembly.

A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA) is disclosed. An example fuel supply system includes a fuel supply line to supply fuel to a combustion engine, a fuel metering valve coupled to the fuel supply line, the fuel metering valve to control a flow of fuel through the fuel supply line to the combustion engine, a throttle valve coupled to the fuel supply line downstream of the fuel metering valve, the throttle valve to bleed off fuel supplied to the combustion engine based on a pressure difference across the fuel metering valve, and a controllable servo coupled to the throttle valve, the controllable servo to control the throttle valve based on a sensor output indicative of the pressure difference.