Abstract: A method and system for measuring a flow profile in a portion of a flow path in a turbine engine is provided. The system includes a mass flow sensor assembly having a plurality of hot wire mass flow sensors, the mass flow sensor assembly disposed in the portion of the flow path at a location where the flow profile is to be measured. The system also includes a controller that converts signals from the temperature sensor, the pressure sensor and the plurality of hot wire mass flow sensors to flow profile measurements.

Abstract: Described herein are methods of operating a gas turbine engine (12) for reduced ammonia slip. An exemplary method (100) includes operating (102) the engine over a range of power output levels; controlling (104) a mass flow of NOx produced in exhaust (19) of the engine to be within 10% over the range of power output levels; and treating (106) the exhaust of the engine in a selective catalytic reduction process (22). In this way, the production of NOx and a corresponding flow of reducing agent (33) utilized in the SCR process remain relatively constant in terms of mass (molar) flow throughout the range of power output levels and ammonia slip is controlled.

Abstract: A method for operating a firing plant with at least one combustion chamber and at least one burner, especially a gas turbine, includes an operating characteristic for operating the combustion chamber close to the lean extinction limit defined as a burner group staging ratio (BGVRich). Pressure pulsations (PulsActual) measured in the combustion chamber are processed by a filter device (2) and converted into corresponding signals (PulsActual,Filter(t)). An exceeding/falling short of at least one pulsation limiting value (PulsLimit) is monitored by a monitoring device (3) and adapts a pulsation reference value (PulsRef) in dependence upon the monitoring. The processed pressure pulsations (PulsActual,Filter(t)) are then compared with the adapted pulsation reference value (PulsRef,adapt), and, from this, a correction value ?BGV is determined, by which the burner group staging ratio (BGVRich) is corrected, and as a result operation of the firing plant close to the lean extinction limit is realized.

Abstract: A gas turbine including a compressor and a combustor, an SOFC including an air electrode (cathode) and a fuel electrode (anode), a first compressed air supply line adapted to supply a compressed air compressed by the compressor to the combustor, a second compressed air gas supply line adapted to supply a part of a compressed air compressed by the compressor to the air electrode (cathode), a first fuel gas supply line adapted to supply a fuel gas to the combustor, a second fuel gas supply line adapted to supply a fuel gas to the fuel electrode (anode), a fuel gas recirculation line adapted to return an exhausted fuel gas discharged from the fuel electrode (anode) to the fuel electrode (anode), a cooler provided in the fuel gas recirculation line are provided.

Abstract: A gas turbine includes a compressor section, a combustion section downstream from the compressor section, a turbine section downstream from the combustion section, and a controller. The controller controls the operation of the gas turbine at a reduced load, and is capable of querying a database including multiple sets of operational parameters for the gas turbine correlated with at least one measured output response at each set of operational parameters. One of the sets of operational parameters provides a desired gas turbine load that meets a target level for the output response. Related methods are also disclosed.

Abstract: In one embodiment, a system includes at least one sensor configured to communicate a signal representative of a gas turbine operations. The system further includes a controller communicatively coupled to the sensor. The system additionally includes a stoichiometric model configured to receive one or more inputs representative of the gas turbine operations and a measured equivalence ratio, wherein the controller is configured to transform the signal into the one or more inputs and to use the stoichiometric model to derive an actuation signal based on a target equivalence ratio.

Abstract: Embodiments of the present invention have the technical effect of automatically testing an overspeed protection system of a powerplant machine comprising at least one shaft. An embodiment of the present invention may automatically test the overspeed protection system while the powerplant machine is decelerating from full-speed-no-load (FSNL). Another embodiment of the present invention may automatically test the overspeed protection system of the powerplant machine while the powerplant machine is accelerating to FSNL.

Abstract: A method for controlling a gas turbine including a compressor assembly including at least one variable geometry portion, a combustion chamber, and a turbine assembly. The method generates a flow rate setpoint value for fuel to be fed to the combustion chamber as a function of a desired speed of the gas turbine, computes threshold values for maintaining the fuel flow setpoint value in a given range, the threshold values depending on a thermodynamic state of the gas turbine, and controls the position of the variable geometry portion by controlling an actuator as a function of the difference between position information representative of the instantaneous position and setpoint position information. The threshold values are automatically adjusted by computation in real time as a function of the instantaneous position information of the variable geometry portion or of the difference between this position information and the setpoint position information.

Abstract: In a method for operating a gas compressor which compresses gas whose supply conditions change and which is equipped with an intake-flow regulating mechanism, a limit pressure ratio that defines the operational upper limit of the pressure ratio relative to the intake flow rate of the gas compressor or the degree of opening of the intake-flow regulating mechanism to prevent surging in the gas compressor is corrected by multiplying a reference limit pressure ratio calculated from the design conditions of the gas compressor by a first correction factor calculated depending on a detected operating-state value of the gas compressor.

Abstract: An embodiment of the present invention is a gas turbine engine including a compressor, a turbine, an annular combustor, an exhaust duct, a first engine shaft bearing, and a second engine shaft bearing. The turbine has an axial flow direction toward the compressor. The combustor has an axial flow direction away from the compressor. The exhaust duct is disposed between the compressor and the combustor. The first engine shaft bearing is disposed on an axial side of the compressor opposite the turbine. The second engine shaft bearing is disposed on an axial side of the turbine opposite the compressor.

Abstract: Fuel control arrangements for gas turbine engines generally comprise an injector and a fuel control valve. Typically the fuel control valve is controlled in terms of fuel demand through fuel pressure presented to the valve. Fuel demand may vary and in such circumstances stagnation of fuel adjacent to the valve may cause degradation of the fuel and therefore spurious operational performance. By providing a dedicated working fluid, and typically hydraulic, pressure to the valve a variable aperture port can be displaced to alter the fuel flow configuration within the valve. In such circumstances different fuel valve conditions can be generated by altering the available area of aperture in the port to divert or present fuel to the injector between and across first or primary fuel paths and second or pilot fuel paths as required. Thus more flexibility with regard to fuel presentation to the injector is achieved as well as consistency with respect to avoiding fuel degradation as fuel demand varies.

Abstract: A gas turbine system includes a gas turbine including a combustor for combusting a fuel and a control assembly configured to control at least one of a fuel system and the combusting of the combustor based on providing values corresponding to at least one of fuel characteristics and combustor characteristics to a fuel induction time transfer function.

Abstract: Provided is a gas turbine control device that is used in a generating facility including a gas turbine and a generator for generating power when at least rotational power of the gas turbine is transmitted, the gas turbine control device including a first control section for obtaining a first fuel control command for causing generator output to follow a generator output set value decided based on a demand load, where the first control section has a feedback control section (60), and the feedback control section (60) includes a subtraction section (62) for calculating a deviation of the generator output with respect to the generator output set value, a PI control section (64) provided in a later stage of control than the subtraction section (62), and a peak suppression section (66) for suppressing a peak in amplitude characteristics of the generator or a utility grid including the generator.

Abstract: A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.

Abstract: Various methods for controlling a wastegate with an actuator having a temperature-dependent magnetic field are provided. In one example, the magnetic field is estimated based on operating conditions and other parameters, and used to apply a magnetic correction to a voltage supplied to the actuator. The methods may provide accurate wastegate control in the presence of varying magnetic fields, ensuring the proper supply of boost to an engine.

Abstract: A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side.

Abstract: Systems and methods for generating a predictable load upon a completion of a start sequence of a gas turbine are provided. According to one embodiment, a system may include a controller to control the gas turbine and a processor communicatively coupled to the controller. The processor may be configured to receive a start duration and a desired final load, and to calculate a target load rate to substantially reach the desired final load within the start duration based on the start duration and the desired final load. Measurements of a present load may be periodically received from a measuring device and used to periodically recalculate the target load rate. A present load rate may be periodically adjusted by the controller based on the recalculation.

Abstract: The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value.

Abstract: A speed control system for an engine comprising at least one rotary load is provided. The speed control system may include a rotor speed controller configured to regulate speed in the rotary load based on a sensed rotor speed, exclusive of resonant mode speed oscillations, in closed loop feedback with a commanded rotor speed. To provide active damping of resonant mode speed oscillations, a resonance disturbance rejection controller may be configured to compensate a speed control signal by observing a component of the sensed rotor speed that is due to resonant mode oscillations. Based on the observed resonance component, the resonance disturbance rejection controller may compute an adjustment value for the speed control signal. In the particular case of gas turbine engines, the resonance disturbance rejection controller may effect active damping by compensation of a fuel flow request for a gas generator.

Abstract: A gas turbine control device having a gas turbine control unit for the gas turbine operation control that computes adjustment increments regarding at least one of the airflow rate into the combustor and the pilot ratio, and makes revisions to the actuating variables comprising the airflow rate and the pilot ratio so that the actuating variables are contrasted with the status signals and the variables are modified toward initial design conditions. The gas turbine control unit resets the revisions made to the actuating variables in a case where the level of the combustion vibration is restrained below the predetermined control criterion for a predetermined time span, and the gas turbine is operated under the control settings of the initial design stage.

Abstract: Systems and methods for distributing torque contribution are provided. According to one embodiment, a system may include a controller and a processor communicatively coupled to the controller. The processor may be configured to receive initial and final transition speeds of the drivetrain, receive a torque reference for accelerating the drivetrain, provide the starting device with primary control of the acceleration of the drivetrain according to the torque reference, and determine that the initial transition speed is reached. Based on the determination, the processor may capture initial transitional conditions of the starting device, define a torque trajectory of the starting device based on the initial and final transition speeds of the drivetrain, and transfer the primary control of the acceleration of the drivetrain from the starting device to the gas turbine.

Abstract: A control apparatus for controlling a compressor driven by a driving unit generating driving power by a gas turbine and an electric motor includes: a temperature detection section for detecting an exhaust gas temperature of the gas turbine; and a control section for generating a motor torque instruction value for the electric motor based on the detected exhaust gas temperature. Such a control apparatus can realize a control so as not to distribute a load on the electric motor when the exhaust gas temperature of the gas turbine is low and a driving power is low. As a result, the operation efficiency can be enhanced.

Abstract: A combined cycle power generation plant can include at least one gas turbine and at least one steam turbine. A method for providing Asymmetric Joint Control for Primary Frequency Regulation (PFR) in the combined cycle power generation plant can include the use of the spinning energy existing in the high pressure steam to rapidly supply additional power to the steam turbine for PFR service within the time frame established as a requirement to participate in the PFR service. The PFR control method can be carried out by controlling flow of high pressure steam to a medium pressure steam circuit through a bypass.

Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to estimate combustor fuel-air ratio based on a realtime model-based estimate of combustor airflow, and commands engine actuators to correct for a difference between the estimated combustor fuel-air ratio and a limit fuel-air ratio selected to avoid lean blowout.

Abstract: A method and a system for identifying failures in an aeroengine. The system includes: a mechanism defining a set of standardized indicators representative of operation of the aeroengine; a mechanism constructing an anomaly vector representative of a behavior of the engine as a function of the set of standardized indicators; a mechanism selecting in an event of an anomaly being revealed by the anomaly vector a subset of reference vectors having directions belonging to a determined neighborhood of a direction of the anomaly vector, the subset of reference vectors being selected from a set of reference vectors associated with failures of the aeroengine and determined using criteria established by experts; and a mechanism identifying failures associated with the subset of reference vectors.

Abstract: The invention relates to a method for operating a thermal power plant, which includes a gas turbine and a generator driven directly by the gas turbine by means of a shaft and being connected to an electrical grid having a grid frequency (FG) via an electronic decoupling apparatus and a step-up transformer. A synthetic inertia response is achieved by said method includes the steps of: sensing said grid frequency (FG); detecting if in case of an excursion of said grid frequency (FG) additional inertial power is required or not; if inertial power is required, calculating the magnitude and duration of the additional inertial power; and releasing additional inertial power to said electrical grid in accordance with said calculations via said electronic decoupling apparatus.

Abstract: Systems and methods for accelerating droop response in a combined cycle power plant are provided. According to one embodiment if the disclosure, a system may include a controller and a processor communicatively coupled to the controller. The processor may be configured to receive frequency variation data associated with a frequency variation of an electrical grid, determine, based at least in part on the frequency variation data, a target operational level of the combined cycle power plant and the droop response associated with the target operational level, calculate a variable compensation value, and apply the variable compensation value to the droop response until the target operational level is reached.

Abstract: A method is provided for operating a gas turbine in the event of load shedding and/or rapid shutdown. The method includes operating the gas turbine by the combustion of fuel in a combustion chamber of the gas turbine with the addition of combustion air via an air passage, and driving a load. Upon or directly after the load shedding or rapid shutdown, an additional gas volume is supplied to the combustion chamber via the air passage in order to slow the drop in pressure level in the combustion chamber.

Abstract: A bleed valve module for mounting to a support structure within an aircraft includes a pipe, a plurality of bleed valves connected to the pipe, a plurality of pneumatic actuators connected to the plurality of bleed valves, and a vibration isolating element. The pipe contains a flow of bleed air and includes a plurality of inlets and an outlet. The plurality of bleed valves controls the flow of bleed air in the pipe. The plurality of pneumatic actuators actuate the plurality of bleed valves. The vibration isolating element connects the bleed valve module to the support structure within the aircraft and isolates the bleed valve module from vibration.

Abstract: A method for controlling a turbine engine generator set is disclosed. The method comprises: sensing an operating parameter indicative of a load increase on the turbine engine generator set; operating the turbine engine generator set in a first mode when the sensed operating parameter is within a predetermined range; and operating the turbine engine generator set in a second mode when the sensed operating parameter is outside the predetermined range. The second mode provides a rate of adjustment of operation of the turbine engine generator set that is greater than a rate of adjustment during the first mode.

Abstract: An on-line optical inspection and monitoring system is externally mounted to existing man way service access within the combustor housing. A replacement man way cover having an optical window is mounted to the combustor housing. One or more optical cameras are oriented so that the camera field of view (FOV) is directed through the man way cover optical window. The camera FOV is moved to plural positions within the combustion section, such as under control of an automated motion control system, and images are captured. Multiple images are combined to form a composite image, which may include an image of an entire transition within the combustion section. Visual images and/or infrared (IR) thermal images may be captured. Thermal image information is correlated with component temperature. Image information is utilized to determine vibration characteristics of the imaged components.

Abstract: A system for operating a gas turbine includes a compressor, a combustor, and a turbine. The combustor and turbine define a hot gas path. A sensor disposed outside the hot gas path measures internal thermal emissions from the combustor or turbine and generates a first signal reflective of the internal thermal emissions. The internal thermal emissions are infrared or ultraviolet emissions. A controller connected to the sensor receives the first signal and adjusts the compressor, combustor, or turbine in response to the first signal from the sensor. A method for operating a gas turbine includes measuring internal thermal emissions from inside a combustor or turbine using a sensor disposed outside the hot gas path. The method further includes generating a first signal reflective of the internal thermal emissions and adjusting the operation of the compressor, combustor, or turbine in response to the first signal from the sensor.

Abstract: The fluid pressure regulating valve is for use in an aircraft engine. The valve has at least a first fluid inlet, a first fluid outlet and a second fluid outlet. The valve comprises: a valve housing having a first valve spool interior cavity; a first fluid path within the valve housing from the fluid inlet to the first fluid outlet; a second fluid path within the valve housing from the fluid inlet to the second fluid outlet; a first valve spool mounted for reciprocal motion within the first valve spool cavity between a first position and a second position, the first valve spool having a second valve spool interior cavity and being spring-biased to its first position; and a second valve spool mounted for reciprocal motion within the second valve spool cavity between a first position and a second position, the second valve spool being spring-biased to its first position, the second valve spool closing the first fluid path at its second position when the first valve spool is substantially at its first position.

Abstract: Disclosed is a gas turbine for a thermal power plant, especially a gas turbine, comprising a rotatable rotor and a duct which can be penetrated by a gas and in which turbine blades for driving the rotor are disposed. The inventive gas turbine is characterized by a blocking device which at least partially prevents the gas from penetrating the duct in a closed position.

Abstract: A Controller, a gas turbine, and a method for auto-tuning a combustion system of a gas turbine are provided. The method includes selecting a first tuning curve from a set of tuning curves for the gas turbine; unbalancing a stable operating point of the gas turbine by modifying one or more operational parameters based on a predefined recipe; determining tuning parameters and storing them while a current operating point of the gas turbine is brought back on the first tuning curve; and generating a backup of tuning parameters to recover the stable operating point.

Abstract: The gas turbine engine comprises at least one electrical generator and an electrical heater associated with a gas path of the engine. The heater is powered by the generator to selectively add heat to the gas turbine cycle.

Abstract: A control device of a gas turbine electric energy production plant (1), which delivers a power (P) at a frequency (fl); the control device (8) comprising power control means (15), for controlling the power (P) delivered by the plant (1) according to a reference power value (PSETNEW), and frequency control means (16), for determining correction values (PFSETPR; PFSETINT) of the reference power value (PSETNEW) according to a frequency error (eF), given by the difference between the plant frequency (f1) and a nominal frequency (fN); the device (8) being characterized in that the frequency control means (16) comprise integral control means (22) configured to calculate the correction values (PFSETINT) if the frequency error (eF) is beyond a first frequency range (B1), and proportional control means (20), which are deactivated when the frequency error (eF) is beyond a first frequency range (B1).

Abstract: A method and system for controlling a two-shaft turbine engine, the two-shaft turbine engine including a gas producer having a compressor with adjustable inlet guide vanes. The method includes monitoring a rotational speed of the gas producer, maintaining an inlet guide vane angle constant when a rotational speed of the gas producer is below a threshold value, and adjusting an inlet guide vane angle of the compressor at a predetermined rate when the rotational speed of the gas producer is above the threshold value.

Abstract: Systems, methods, and apparatus are provided for controlling the oxidant feed in low emission turbine systems to maintain stoichiometric or substantially stoichiometric combustion conditions. In one or more embodiments, such control is achieved through methods or systems that ensure delivery of a consistent mass flow rate of oxidant to the combustion chamber.

Abstract: A system includes a gas turbine system model configured to model a turbine system operational behavior of a gas turbine system, and a shaft contribution model (SCM) including a bottoming cycle performance (BCP) model configured to model a bottoming cycle behavior of a bottoming cycle system. The gas turbine system model is configured to receive a SCM output from the SCM and to use the SCM output to control an actuator. The actuator is operatively coupled to the gas turbine system.

Abstract: A method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor.

Abstract: A regulator device (10) for regulating a turbine engine (3). The regulator device (10) includes mechanical power take-off means (100) for taking off power mechanically from a gas generator (4), and an engine computer (20) controlling said engine (3) to comply with at least a first limitation (LimTET, LimT45) of a temperature (TET, T45) of the gas within the engine, and with a second limitation (LimNg) of a speed of rotation (Ng) of the gas generator (4). The engine computer (20) determines whether the speed of rotation (Ng) of the gas generator has reached said second limitation (LimNg), and whether said temperature (TET, T45) has reached said first limitation (LimTET, LimT45). An avionics computer (30) causes the mechanical power take-off means (100) to operate if the speed of rotation (Ng) of the gas generator (4) has reached said second limitation (LimNg), and if said temperature (TET, T45) has not reached said first limitation (LimTET, LimT45).

Abstract: A combustion turbine engine that includes: a compressor; a combustor that receives fuel from a fuel line; a turbine; a heat exchange portion comprising a portion of the fuel line in heat transfer relationship with a heat source for heating the fuel; a rapid heating value meter disposed to test the heating value of the fuel that is configured to provide heating value test results within approximately 1 minute; a cold leg bypass comprising a fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction; and valves for controlling the fuel being directed through the heat exchange portion and the fuel being direct through the cold leg bypass; wherein the length of fuel line between the fuel mixing junction and the combustor is less than 20 meters.

Abstract: A method of controlling a power plant that comprises a working fluid and a recirculation loop, wherein the power plant includes a combustor operably connected to a turbine, the method including the steps of: recirculating at least a portion of the working fluid through the recirculation loop; controlling the power plant such that the combustor at least periodically operates at a preferred stoichiometric ratio; and extracting the working fluid from at least one of a first extraction point and a second extraction point positioned on the recirculation loop during the periods when the combustor operates at the preferred stoichiometric ratio.

Abstract: A method of controlling a power plant that includes a working fluid, wherein the power plant includes a combustion system having an upstream combustor operably connected to a high-pressure turbine and a downstream combustor operably connected to a low-pressure turbine. The method may include the steps of: supplying compressed oxidant to at least one of the upstream and the downstream combustor; supplying a fuel to at least one of the upstream and the downstream combustor; combusting the fuel with the compressed; recirculating the working fluid; controlling the power plant such that one of the upstream and the downstream combustors operates at a preferred stoichiometric ratio; and extracting the working fluid from an extraction point positioned relative to the whichever of the upstream combustor and the downstream combustor operates at the preferred stoichiometric ratio.

Abstract: The present invention provides a system and method of operating a combined-cycle powerplant at part-load without shutting down an HRSG and steam turbine. The present invention may apply to a powerplant operating in an open-cycle mode. The present invention may also apply to a powerplant operating in a closed-cycle mode.

Abstract: Simple, robust and systematic solutions are provided for controlling counter-rotating open-rotor (CROR) gas turbine engines. The solutions mathematically decouple the two counter rotating rotors of a CROR engine by model-based dynamic inversion, which allows application of single-input-single-output (SISO) control concepts. The current solutions allow fuel flow to be treated as a known disturbance and rejected from the rotor speeds control. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.

Abstract: Embodiments of the present invention employ a closed loop controls philosophy, which actively controls the starting means of a powerplant machine, throughout the start-up process. Here, the present invention may provide a method for adjusting a nominal operating schedule of the starting means, which may have the form of a Load Commutated Inverter (LCI). Embodiments of the method may adjust the nominal operating schedule based, in part, on an operating parameter, which is associated with the gas turbine 100. The operating parameter may include, but is not limited to: a rotor speed, a desired start-up time, or the like. Here, the control system may receive data on the operating parameter associated with the gas turbine.

Abstract: Systems and methods are provided that include a gas turbine, a generator coupled to the gas turbine and configured to generate a first electrical power output, and a variable frequency transformer coupled to the generator and configured to be coupled to an electrical grid such that the variable frequency transformer is configured to transform the first electrical power output into a second electrical power output having one or more power characteristics that correspond to the electrical grid.

Abstract: A control method for controlling an overspeed safety system (5) of an aircraft (1) having at least a first engine (10) and a second engine (20), during which method an engine is shut down when a monitoring parameter of that engine exceeds a first threshold, and another engine distinct from this engine is shut down when the monitoring parameter for said other engine exceeds a second threshold, said second threshold being greater than said first threshold.