Abstract: A system for regulating a thermal parameter associated with a heat exchange assembly of a turbomachine includes at least one device for measuring or estimating the thermal parameter, a controlled valve acting on the flow rate of a fluid in the assembly, and a regulator including a comparator determining the sign of an error signal relating to the difference between the thermal parameter and a setpoint. The regulator further includes a switch configured to deliver, based on the sign, to a valve control system, a maximum control current switching the valve in a closed state or a minimum control current switching the valve in an open state, and a phase-shifter configured to apply on the error signal a phase advance determined from an estimate of a time constant of the control system.

Abstract: A control system for controlling a controlled parameter of an aeronautical equipment device, the controlled parameter being governed by an operating law linking the controlled parameter to a command and to a plurality of input parameters, the control system including a control loop controlling the controlled parameter to a setpoint with the control of the device by the command, the system including an operating law compensation module and a determination module determining a local gain configured to determine the local gain of a static part of a model of the operating law representative of the gain of the controlled parameter in response to a variation in the command in a stabilised operating regime of the operating law, the operating law compensation module using the inverse of the local gain.

Abstract: Resetting a basic digital model includes a step of detecting a stable state of at least one first parameter of the model, the first parameter being representative of a signal delivered by a sensor; a step of obtaining a resetting parameter for the model, during the stable state of the first parameter as a function of the first parameter, of a second parameter of the model, and of the basic digital model; and a step of obtaining a reset model from the basic digital model and the resetting parameter.

Abstract: A method of adjusting a fuel flow rate in a turbine engine propelling an aircraft, including: obtaining a first estimate of a flow rate of fuel injected into a combustion chamber of the turbine engine propelling an aircraft and as delivered by a fuel metering device of the turbine engine; obtaining a second estimate of the fuel flow rate, which second estimate is more accurate than the first estimate for at least one range of fuel flow rate values and being delivered by an estimator device having a flow meter; and adjusting the fuel flow rate threshold value with help of a difference evaluated between the first estimate and the second estimate, the threshold value being for use in an open loop for regulating the turbine engine.

Abstract: The invention relates to a method for controlling the speed and the power of a turbine engine propeller, wherein at least two operating modes are implemented: —one operating mode, called “speed mode”, in which the pitch (?) of the propeller is controlled as a function of the desired propeller speed, while the fuel flow is controlled as a function of the desired torque; the other operating mode, called “? mode”, in which the fuel flow is controlled as a function of the desired propeller speed, the pitch (?) of the propeller being set to a limit angle (?min) that limits the pitch of the propeller in the two operating modes, the pitch angle (?min(t)) being continuously computed and updated during a flight on the basis of parameters relating to the flight conditions estimated in real time.

Abstract: During a stage (E0) of starting the turbine engine, the method of the invention comprises: an open-loop generating step (E10) of generating a fuel flow rate command (WF_OL) from at least one pre-established relationship; and a closed-loop monitoring step (E20-E30) of monitoring at least one operating parameter of the turbine engine selected from: a rate of acceleration (dN2/dt) of a compressor of the turbine engine; and a temperature (EGT) at the outlet from a turbine of the turbine engine; this monitoring step comprising maintaining (E30) the operating parameter in a determined range of values by using at least one corrector network (R1, R2, R3) associated with the parameter and suitable for delivering a signal for correcting the open-loop generated fuel flow rate command so as to maintain the operating parameter in the determined range of values.

Abstract: A method for monitoring an LVDT sensor including two secondary circuits, the method including: calculating the difference between voltages at terminals of one of the secondary circuits at a given instant and at a previous instant; calculating the difference between voltages at terminals of the other one of the secondary circuits at the given instant and at the previous instant; calculating the sum of the two differences calculated; modifying an indicator according to a distance to zero of the previously calculated sum; and comparing the indicator with at least one predetermined threshold.

Abstract: A method of regulating a temperature (TM) associated with a heat exchanger assembly (10) of a turbine engine (1), the method comprising, in a single cycle: measuring (500) the temperature (TM) of an air stream at the outlet from a heat exchanger (14); receiving a setpoint temperature (TC) for the air stream at the outlet from the heat exchanger (14); estimating (510) a theoretical temperature (TT) for the air stream at the outlet from the heat exchanger (14) as a function of an estimate of the position of a shutter of a controlled valve (15) bleeding off a cooling air stream for the heat exchanger (14); determining a correction current (ICO) from the difference (?T1) between the measured temperature (TM) and the theoretical temperature (TT); and determining (530) a control current (IC) for the shutter from the difference (?T2) between the measured temperature (TM) and the setpoint temperature (TC) and while taking account of the correction current (ICO) determined during the preceding cycle, the position of t

Abstract: A control system for controlling a controlled parameter of an aeronautical equipment device, the controlled parameter being governed by an operating law linking the controlled parameter to a command and to a plurality of input parameters, the control system including a control loop controlling the controlled parameter to a setpoint with the control of the device by the command, the system including an operating law compensation module and a determination module determining a local gain configured to determine the local gain of a static part of a model of the operating law representative of the gain of the controlled parameter in response to a variation in the command in a stabilised operating regime of the operating law, the operating law compensation module using the inverse of the local gain.

Abstract: A processing method of an alternating signal produced by a variable reluctance sensor, including steps consisting of a raw window signal switching toward a low voltage level, respectively toward a high voltage level, calculation of a processed window signal using a value of the switching continuation duration calculated as a function of a value of shaft rotation speed, and based on the raw window signal, measurement of the shaft rotation speed, each switching of the processed window signal triggering the locking of the processed window signal, for a duration exactly equal to the switching continuation duration, so that the switches of the raw window signal are not translated into switches of the processed window signal during the locking, the processed window signal no longer being locked once the switching continuation duration has expired.

Abstract: This module (5) serves to filter a raw setpoint (N1_CMD_OP) for a corrector network (6) in a system (20) for regulating an engine. It comprises: a module (54) for detecting a filtering condition for filtering said raw setpoint; and means for supplying said corrector network with a filtered setpoint (N1_CMD_LIM) instead of said raw setpoint when the filtering condition is detected.

Abstract: A method of monitoring a valve in a turboshaft engine, said valve switching, by closing and/or opening, in response to a control instruction sent at a determined instant, said method comprising calculating a first form of a time signal from the change in a status variable of said turboshaft engine reacting to a switching of said valve, applying a signature test of the switching of the valve to a form of said signal, wherein the method further comprises defining a time interval after sending said control instruction to perform said signature test; acquiring one or more parameters other than the switching of the valve; modelling a signal of said time signal in response to a change in said other parameter(s) to calculate its change; and calculating said second form of the signal is calculated from the first form of the signal by subtracting therefrom the change in the signal calculated from the change in said other parameter(s), over said time interval following a control instruction.

Abstract: A method of monitoring a valve in a turboshaft engine, said valve switching, by closing and/or opening, in response to a control instruction sent at a determined instant, said method comprising calculating a first form of a time signal from the change in a status variable of said turboshaft engine reacting to a switching of said valve, applying a signature test of the switching of the valve to a form of said signal, wherein the method further comprises defining a time interval after sending said control instruction to perform said signature test; acquiring one or more parameters other than the switching of the valve; modelling a signal of said time signal in response to a change in said other parameter(s) to calculate its change; and calculating said second form of the signal is calculated from the first form of the signal by subtracting therefrom the change in the signal calculated from the change in said other parameter(s), over said time interval following a control instruction.

Abstract: A method for monitoring a thrust fault of a turbofan during a modification of the thrust setting of the turbofan, the method including a step of processing the thrust setting via a filtering function and a transient-phase model such as to obtain a modelled thrust, a step of comparing the modelled thrust to the actual thrust such as to determine a thrust difference, a step of comparing the thrust difference to an alarm threshold; and a step of emitting an alarm in the event of exceeding the alarm threshold, wherein at a given iteration, in which the prior modelled thrust is known, the transient-phase model provides a time constant in accordance with the prior modelled thrust, and the filtering function provides a modelled thrust in accordance with the time constant obtained, the prior modelled thrust and the thrust setting.

Abstract: An aircraft turbine engine including at least one spool rotating at speed N1 and a monitoring system including: a regulating module including at least one regulation measurement channel to obtain a measurement of the speed N1 and a mechanism to compare the obtained speed measurement with a thrust setpoint to provide a thrust status; and a module for engaging a protection function of UHT or ATTCS type of the turbine engine. The turbine engine further includes a system for protection against overspeed to prevent ejection of high-energy debris outside the turbine engine, the protection system including at least one overspeed measurement channel to obtain an overspeed of the rotating spool of the turbine engine. The engagement module compares at least one overspeed obtained with at least one reference speed defined according to the protection function to be engaged, to engage the protection function according to results of the comparison.

Abstract: A method for eliminating rotational stall in a compressor of a turbine engine, includes automatically detecting surge in the turbine engine; automatically shutting-down the turbine engine; in the event surge is detected, automatically restoring a surge margin; and automatically re-igniting the turbine machine.

Abstract: Resetting a basic digital model includes a step of detecting a stable state of at least one first parameter of the model, the first parameter being representative of a signal delivered by a sensor; a step of obtaining a resetting parameter for the model, during the stable state of the first parameter as a function of the first parameter, of a second parameter of the model, and of the basic digital model; and a step of obtaining a reset model from the basic digital model and the resetting parameter.

Abstract: A method of testing an engine fuel supply cutoff valve includes: detecting a fuel supply cutoff command; commanding to close the fuel supply cutoff valve; commanding to hold the fuel metering valve in the open position for a predetermined time; commanding to close the fuel metering valve after the predetermined time; measuring an engine operating parameter during performance of the previous steps; and comparing the measured parameter with a predetermined threshold, so as to determine whether or not the engine operating parameter corresponds to an engine fuel supply cutoff by normal operation of the fuel supply cutoff valve.

Abstract: A method of controlling a turbine engine, including: measuring a first temperature by a first temperature sensor; measuring a second temperature by a second temperature sensor; estimating a third temperature modeling the first temperature; and determining at least one control setpoint for at least one piece of variable-geometry equipment of the engine, as a function of the measured first temperature. The first sensor presents a time constant longer than a time constant of the second sensor. The method further detects ingestion of water or hail as a function of a drop in the measured second temperature; and when water or hail ingestion is detected, determines the control setpoint as a function of the estimated third temperature.

Abstract: A method of synchronizing engines of an airplane in accordance with at least one activation logic (10, 10?) defining a deactivated state (20), a primed state (22), and at least one activated state (16, 18), and comprising: passing (32) synchronization from the deactivated state to the primed state when a pilot of the airplane issues an activation order; passing (36) synchronization from the primed state to the activated state when at least certain safety and/or activation conditions are satisfied; and passing (24, 34) synchronization from the activated or primed state to the deactivated state when the pilot issues a deactivation order or whenever at least some of the safety conditions are not satisfied.