Safran Aircraft Engines

Snecma

Cedrik Djelassi

Bruno Robert Gaully

Pierre Cabrera

Christophe Javelot

Vincent Cabret

Alexandra Riou

Gilles Alain Marie Charier

Tewfik Boudebiza

Jean-Michel Roux

Julien Alexis Louis Ricordeau

Jacques Paul Michel Gauvrit

Florent Nobelen

Julien Michel Patrick Christian Austruy

Jean-François Jean-Paul Clément Schielin

Adel Cédric Abir Widemann

Cecile Marot

Darragh McGrath

Laurent Perotin

Julie Touya

Cecile Valerie Marie Cointe

Michael Dinsart

Mohamed Boutaleb

Victor Henry

Ismail Sylla

David Julien Boyer

Nicolas Raillard

Soufiane Herda

Darragh Mcgrath

Cecile Valerie Cointe

Bruno Gaully

Mohamed Amer

A system REG for regulating a physical parameter of a real turbomachine system F(p) from a physical setpoint parameter, the regulation system REG comprising a system OPTK for optimising the parameterisation gain K during the regulation, the optimisation system OPTK comprising a stability correction module determining a first gain component K1, a response time correction module determining a second gain component K2, the stability correction module being designed to inhibit the response time correction module when an instability is detected during the regulation of the physical parameter, and a determination module configured to determine the parameterisation gain K as a function of the previously determined first gain component K1 and second gain component K2.

System and method for regulating a physical parameter of a real turbomachine system from a physical parameter set point

A method for detecting a rotating stall includes: determining a level of variation of a static pressure in a combustion chamber of the turbojet engine around an average value of this static pressure; comparing the level of variation of the static pressure relative to a first threshold; comparing a temperature measured at the outlet of a turbine of the turbojet engine relative to a second threshold; and if the level of variation of the static pressure is greater than the first threshold and the temperature at the outlet of the turbine is greater than the second threshold, detecting a presence of a rotating stall.

Method and device for detecting a rotating stall adversely affecting a turbojet engine compressor

The invention relates to a method for filtering an input signal () relative to a physical variable of a turbine engine (), the input signal being digitised, the method implementing frequency filtering of said signal in a computer () of a control system () of said turbine engine (), said signal being provided at the input of the computer, a digital derivative of said signal being intended for being used by the control system (), characterised in that it involves: —detecting an amplitude variation of said variable on said input signal, by a step of generating a second derivative signal (S) of the input signal and a step of comparing a value of the second derivative value of the input signal with at least one predetermined threshold (S. . . S); and —adapting the frequency filtering of said input signal as a function of the detected amplitude variation of said variable, by a step of controlling a controlled filter (PB) capable of applying frequency filtering to the input signal, so that the controlled filter applies or does not apply the frequency filtering as a function of a result of the comparison step.

Adaptive filtering method

The invention describes a system for controlling the cyclic setting of blades () of a turbine engine propeller, the blades () being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: &#x2014;a plate assembly () that can be tilted relative to the normal plane (P), &#x2014;an articulation system () articulating the plate assembly () relative to the blades () such that tilting the plate assembly () modifies the setting of the blades (), &#x2014;a force sensor () designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (), &#x2014;a cylinder () suitable for tilting the plate assembly () in response to a force measured by the force sensor ().

System for controlling the cyclic setting of blades

A method of regulating a temperature associated with a heat exchanger assembly of a turbine engine, the method includes, in a single cycle: measuring the temperature of an air stream at the outlet from a heat exchanger; receiving a setpoint temperature for the air stream at the outlet from the heat exchanger; estimating a theoretical temperature for the air stream at the outlet from the heat exchanger as a function of an estimate of the shutter position of a controlled valve bleeding off a cooling air stream for the heat exchanger; determining a correction current from the difference between the measured temperature and the theoretical temperature; and determining a control current for the shutter from the difference between the measured temperature and the setpoint temperature and the correction current determined during the preceding cycle, the shutter position being determined from the control and correction currents determined during the preceding cycle.

Method and a system for regulating a temperature associated with a heat exchanger assembly of a turbine engine

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: &#x2014;one operating mode, called 'speed mode', in which the pitch (&#x3b2;) 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 '&#x3b2; mode', in which the fuel flow is controlled as a function of the desired propeller speed, the pitch (&#x3b2;) of the propeller being set to a limit angle (&#x3b2;min) that limits the pitch of the propeller in the two operating modes, the pitch angle (&#x3b2;min(t)) being continuously computed and updated during a flight on the basis of parameters relating to the flight conditions estimated in real time.

Method for controlling the speed and the power of a turbine engine propeller

A method for controlling a turbomachine comprising an electric motor forming a torque injection device on a high-pressure rotation shaft, in which method a fuel flow setpoint Qand a torque setpoint TRQprovided at the electric motor are determined, the control method comprising: &#x2022; a step of implementing a first fuel control loop in order to determine the fuel flow set point QCMD, &#x2022; a step of implementing a second, torque control loop in order to determine the torque setpoint TRQcomprising i. a step of determining a torque correction variable &#x394;TRQas a function of a transitory speed setpoint NHTrajAccelCons, NHTrajDecelCons and ii. a step of determining the torque setpoint TRQas a function of the torque correction variable &#x394;TRQ.

Method for controlling a turbomachine comprising an electric motor

A method for measuring rotation speed of an aircraft engine shaft includes: acquisition of an alternating rotation speed detection signal across terminals of a phonic wheel sensor, conversion of the alternating signal into a square signal; comparison of a plurality of previously-stored square signal period samples to lower and upper period limits, to determine valid samples of a value included between the terminals; if the number of valid samples is greater than a first threshold, determination on the basis of the valid samples of a desired period of the square signal; and at least on the condition that the number of valid samples is less than the first threshold, computation of a plurality of sums of samples, and computation of the average of a set comprising a number of valid period samples and a number of sums from among the plurality of sums of at least two samples.

Method for measuring the speed of rotation of an aircraft engine shaft, taking into account the measurement noise

The invention relates to a method (E) for detecting the ignition of a turbine engine combustion chamber, the method (E) comprising the steps of: receiving (E) a first measurement of the exhaust gas temperature downstream from the combustion chamber, before an attempt to ignite said combustion chamber; receiving (E) a temperature threshold; receiving (E) a secondary detection criterion; updating (E) the received temperature threshold as a function of the secondary detection criterion received; receiving (E) a second measurement of the exhaust gas temperature, after the attempt to ignite the combustion chamber; comparing (E) the updated temperature threshold with the difference between the first and second exhaust gas temperature measurements; and determining (E) the state of ignition of the combustion chamber.

Method for detecting the ignition of a turbine engine

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.

Unit for controlling a controlled valve for abstracting an airflow from a pressurized airflow of an aircraft

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.

Processing method for a rotation speed signal of an aircraft engine shaft affected by noise

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.

System for controlling a controlled parameter

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.

Method and device for adjusting a threshold value of a fuel flow rate

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.

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Marolles en Hurepoix, France

Cedrik Djelassi