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, the method comprising: a step of 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; wherein the method comprises: a detection step of detecting an intended speed transient; and in response to said detection step, a step of 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.

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 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: Detecting a state of icing in a turbomachine fuel circuit includes reading information representative of a first temperature T1 of the fuel downstream from the metering unit, and of comparing the first temperature T1 with a first reference temperature T01. The method also includes detecting clogging of the filter unit. In the event of the temperature reading T1 being less than the first reference temperature T01 and of clogging being detected, a signal indicative of an icing state in the fuel circuit is issued. Information representative of a second fuel temperature T2 in the tank may be read and compared with a reference temperature T02 in order to confirm or contradict the icing state. A signal indicating a need for maintenance of the fuel circuit is issued when the temperature readings T1 and T2 are not less than the reference temperatures T01 and T02 and clogging has been detected.

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 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.