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: 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 and device producing a setpoint signal representing a flow rate of fuel that a metering unit having a slide valve is to supply to a fuel injection system of a combustion chamber in a turbine engine, the position of the valve depending on the setpoint signal. The method: obtains a first signal representing a measurement as delivered by a flow meter of a flow rate of fuel injected into the chamber; evaluates a second signal representing the flow rate of fuel injected into the chamber based on a measurement of the position of the valve; estimates a third signal representative of the measurement delivered by the flow meter by applying a digital model of the flow meter to the second signal; and produces the setpoint signal by adding a compensation signal to the first signal, the compensation signal obtained by subtracting the third signal from the second signal.

Abstract: A method of controlling an engine in which a fuel flow setpoint is determined is provided. The method includes implementing a steady speed regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a setpoint parameter that depends on the position of a control lever and an operating parameter of the engine; detecting an intended speed transient; and implementing a speed transient regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a speed of the engine and a speed setpoint varying over time with the speed trajectory as generated in predetermined manner, if a speed transient is detected.

Abstract: A method and device detecting a rotating stall affecting a turbine engine compressor. The detection method includes: detecting an abnormal acceleration of the engine or an operating line of the compressor that is characteristic of a failure of the engine; storing a reference temperature measured at an outlet from a turbine of the engine at an instant of detection; comparing a determined temperature threshold with the difference between a current temperature at the outlet of the turbine as measured after detection and the reference temperature; and identifying that a rotating stall is present in event of the threshold being exceeded.

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: 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: A detection method for detecting ingestion of water or hail in a gas turbine engine, the engine including at least a compressor, a combustion chamber, and a turbine, the method including: estimating a value of a first indicator representative of water or hail being ingested; estimating a value of a second indicator representative of water or hail being ingested, the second indicator being different from the first indicator; and calculating a value of a global indicator by summing at least the first indicator and the second indicator.

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: An aircraft turbine engine comprising at least one spool rotating at speed N1 and a monitoring system (1) comprising: a regulating module (REG) comprising at least one regulation measurement channel (A, B) suitable for obtaining a measurement (N1A, N1B) of the speed N1 and means for comparing the obtained speed measurement (N1A, N1B) with a thrust setpoint (N1cons) to provide a thrust status (EREG); and a module (ENG) for engaging a protection function of the UHT or ATTCS type of the turbine engine, the turbine engine also comprising a system for protection against overspeed in order to prevent the ejection of high-energy debris outside said turbine engine, the protection system comprising at least one overspeed measurement channel (AS, BS) suitable for obtaining an overspeed (N1AS, N1Bs) of the rotating spool of the turbine engine, the turbine engine being characterised in that the engagement module (ENG) comprises means for comparison of at least one overspeed obtained (N1AS, N1BS) with at least one ref

Abstract: A method and system for controlling clearance between the tips of blades of a turbine rotor in a gas turbine airplane engine and a turbine ring of a casing surrounding the blades. A valve is controlled to act on a flow rate and/or a temperature of air directed against the casing. The valve is of the on/off type for switching between an open state and a closed state in a determined reaction time, the valve control module including a corrector for determining a first binary control signal that can take a first value corresponding to an open state and a second value corresponding to a closed state of the valve. The corrector includes a time-delay module for determining a binary control signal, with the duration between two successive changes of state in the control signal being not less than the reaction time of the valve.

Abstract: A method including digitally modelling a temperature measured by a sensor by using a modeled signal and estimating a lag error signal for the sensor from the modeled signal and a signal obtained by filtering the modeled signal, the filter having as a parameter an estimate of a time constant of the sensor, and correcting the measurement signal delivered by the sensor by the estimated lag error signal. The time constant of the sensor is estimated as a function of time from the measurement signal and the modeled signal.

Abstract: Method of testing an engine fuel supply cutoff valve, characterised in that it comprises steps to: detect (E1) a fuel supply cutoff command, command (E3) to close the fuel supply cutoff valve, command (E4) to hold the fuel metering valve in the open position for a predetermined time, command (E5) to close the fuel metering valve after the predetermined time, measure (E6) an engine operating parameter during performance of the previous steps, compare (E7) 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 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.

Abstract: An estimation method that can estimate a stream temperature in a turbojet including: digitally modeling the stream temperature with help of a modeled signal; and correcting the modeled signal with help of an error signal, a signal obtained after correction representing an estimate of the stream temperature. When predetermined conditions relating to at least one operating stage of a turbojet and to temperature stability are satisfied, the error signal is updated from the modeled signal and from a measurement signal of the stream temperature as delivered by a temperature sensor.

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: A system for controlling angular position of stator blades including: a mechanism for calculating a set angular position of the blades according to one of speeds; and a module for correcting the set position including: a mechanism for determining the angular position of the blades; a mechanism for measuring fuel flow rate of the turbine engine; a memory unit in which consecutive angular positions of the blades are combined with the fuel flow rates of the turbine engine measured at the angular positions; and a mechanism for determining a correcting angle according to the difference between the fuel flow rates measured between two consecutive angular position of the blades. A method for optimizing the common angular position can utilize the system.

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 and device detecting a rotating stall affecting a turbine engine compressor. The detection method includes: detecting an abnormal acceleration of the engine or an operating line of the compressor that is characteristic of a failure of the engine; storing a reference temperature measured at an outlet from a turbine of the engine at an instant of detection; comparing a determined temperature threshold with the difference between a current temperature at the outlet of the turbine as measured after detection and the reference temperature; and identifying that a rotating stall is present in event of the threshold being exceeded.

Abstract: A detection method for detecting ingestion of water or hail in a gas turbine engine, the engine including at least a compressor, a combustion chamber, and a turbine, the method including: estimating a value of a first indicator representative of water or hail being ingested; estimating a value of a second indicator representative of water or hail being ingested, the second indicator being different from the first indicator; and calculating a value of a global indicator by summing at least the first indicator and the second indicator.