Abstract: The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined, corresponding to the fact that the joint (J1) is compressed so as to not let the primary flow pass through the orifice (O1) in the secondary flow, by the fact that the dead zone is equal to a reference dead zone, which has been predetermined on a reference turbomachine operating on the ground, to which the measured static angle has been added and from which a reference static angle, which has been predetermined on the reference turbomachine operating in flight, has been subtracted.

Abstract: The invention relates to a method for controlling a pitch angle of the vanes or blades of a propellant body of a turbine engine, comprising generating a pitch command (ifinal) according to a rotational speed of the propeller (XNmes) and a speed setpoint (XNcons), the method comprises a nominal regulating chain (13), wherein the pitch command is further generated according to a value of a pitch angle (?mes) of the vanes or blades of the propellant body, and an off-nominal regulating chain (16), wherein the pitch command is generated independently of a value of a pitch angle of the vanes or blades of the propellant body.

Abstract: A method detects and localizes a failure of a measurement acquisition channel in an acquisition system including two redundant acquisition channels for the measurement of a physical quantity in an environment. The method uses a processor with a memory storing a model including modeled values of the physical quantity based on measurements of other physical quantities in the environment. The method includes detecting a symptomatic error of a defective acquisition channel when a deviation between the measured values of the two channels reaches a detection threshold, waiting to let the acquisition system evolve for a certain period, and localizing the defective channel among the two channels, when the deviation of the values measured between the channels reaches a localization threshold different from the detection threshold. The localization is made from the comparison of the measured value of each of the channels with a modeled value of the physical quantity.

Abstract: A lubricating oil circuit of a turbomachine includes a distribution valve that distributes an oil flow rate among a first heat exchanger and a bypass duct, connected to an oil duct, which is connected to an heat exchanger positioned against a turbomachine fuel passage duct, and includes a gearbox of a rotation speed reducer that lowers a rotational speed of a first rotary fan shaft of the turbomachine relative to a rotational speed of a second low-pressure compressor rotary shaft of the turbomachine or of a second low-pressure turbine rotary shaft of the turbomachine, and a regulation device. The regulation device includes a local regulation loop that generates an oil flow rate distribution control signal and regulates an oil temperature of the oil duct on a temperature setpoint, and a global regulation loop that generates the temperature setpoint as a function of the temperature and of the temperature setpoint.

Abstract: The invention relates to a method for controlling a pitch angle of the vanes or blades of a propellant body of a turbine engine, comprising generating a pitch command (ifinal) according to a rotational speed of the propeller (XNmes) and a speed setpoint (XNcons), the method comprises a nominal regulating chain (13), wherein the pitch command is further generated according to a value of a pitch angle (?mes) of the vanes or blades of the propellant body, and an off-nominal regulating chain (16), wherein the pitch command is generated independently of a value of a pitch angle of the vanes or blades of the propellant body.

Abstract: A system and method for controlling an aircraft turbine engine. The control system includes: a nominal-mode processing chain including a global corrector designed to control a speed of rotation of the turbine engine by delivering a position setpoint for a fuel metering device, and a local corrector designed to control a position of the fuel metering device by delivering a nominal-mode control current, a degraded-mode processing chain including a direct corrector designed to control the speed of rotation of the turbine engine by delivering a degraded-mode control current, and a mode management module designed to deliver, to the fuel metering device, the nominal-mode control current in the absence of failure of a position sensor measuring a position of the fuel metering device, and the degraded-mode control current in the case of failure of the position sensor.

Abstract: The invention relates to a method for estimating and using a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint signal for closing the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined from the static angle, corresponding to the fact that the joint (J1) remains compressed and seals the closing of the orifice (O1), the dead zone is recorded and the signal (SC1) for controlling the actuator (V1) is generated by the computer as a function of the dead zone.

Abstract: The invention relates to a method for estimating and using a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint signal for closing the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined from the static angle, corresponding to the fact that the joint (J1) remains compressed and seals the closing of the orifice (O1), the dead zone is recorded and the signal (SC1) for controlling the actuator (V1) is generated by the computer as a function of the dead zone.

Abstract: The invention relates to a method for the closed-loop control of a proportional integral-type controller (2) in an instrumentation and control device (1) of a closed-loop control system (3), in particular a servovalve-actuator system, said controller (2) including a setpoint-weighting coefficient (?), said closed-loop control method comprising the consecutive steps of assigning (11) a unit value to the set-point weighting coefficient (?), optimizing (12) a closed-loop control of the controller (2) satisfying at least one predefined performance criterion, defining a characteristic tracking error (?TC) making it possible to respond to the performance constraints of the system to be closed-loop controlled, and assigning (132) a setpoint weighting coefficient (?) value, depending on the characteristic tracking error (?TC) and the closed-loop control of the controller (2).

Abstract: The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined, corresponding to the fact that the joint (J1) is compressed so as to not let the primary flow pass through the orifice (01) in the secondary flow, by the fact that the dead zone is equal to a reference dead zone, which has been predetermined on a reference turbomachine operating on the ground, to which the measured static angle has been added and from which a reference static angle, which has been predetermined on the reference turbomachine operating in flight, has been subtracted.

Abstract: The invention relates to a method for detecting a possible fuel leak into an oil circuit of an aircraft engine, the aircraft including at least one pair of identical engines equipped with respective oil circuits, the pair of engines being associated with at least one quadruplet of measurements previously acquired in a measurement time during the operation of the engines of the pair and corresponding to a measurement of pressure and a measurement of temperature of the fluid contained in each of the oil circuits of the engines of the pair.

Abstract: The invention relates to a method for monitoring the operating state of an overpressure valve of a turbine engine, the turbine engine comprising a fluid circuit, at least one pressure sensor for the fluid in the fluid circuit, a temperature sensor for the fluid in the fluid circuit, said overpressure valve being configured to limit the maximum fluid pressures in the fluid circuit, and the method comprising the following steps: —(E2) determining an opening or closing indicator of the overpressure valve on the basis of the change in the fluid pressure over time; —(E3) determining an operating state of the valve as a function of a fluid threshold temperature and of the determined opening or closing indicator of the overpressure valve.

Abstract: A method detects and localizes a failure of a measurement acquisition channel in an acquisition system including two redundant acquisition channels for the measurement of a physical quantity in an environment. The method uses a processor with a memory storing a model including modeled values of the physical quantity based on measurements of other physical quantities in the environment. The method includes detecting a symptomatic error of a defective acquisition channel when a deviation between the measured values of the two channels reaches a detection threshold, waiting to let the acquisition system evolve for a certain period, and localizing the defective channel among the two channels, when the deviation of the values measured between the channels reaches a localization threshold different from the detection threshold. The localization is made from the comparison of the measured value of each of the channels with a modeled value of the physical quantity.

Abstract: A system and method for controlling an aircraft turbine engine. The control system includes: a nominal-mode processing chain including a global corrector designed to control a speed of rotation of the turbine engine by delivering a position setpoint for a fuel metering device, and a local corrector designed to control a position of the fuel metering device by delivering a nominal-mode control current, a degraded-mode processing chain including a direct corrector designed to control the speed of rotation of the turbine engine by delivering a degraded-mode control current, and a mode management module designed to deliver, to the fuel metering device, the nominal-mode control current in the absence of failure of a position sensor measuring a position of the fuel metering device, and the degraded-mode control current in the case of failure of the position sensor.

Abstract: The invention concerns a method for controlling a mechanism (10) displaying asymmetrical behaviour, the mechanism (10) comprising a first operating direction (F+) and a second operating direction (F?), the control method making it possible to generate, using a control module (24) of a computer (20), a control signal (x_com) from a setpoint signal (x_cons), in which—when the setpoint signal (x_cons) indicates that the mechanism (10) should be operated in the first direction (F+), the control module (24) applies a first corrector (100) to the setpoint signal (x_cons) in order to generate a control signal (x_com),—when the setpoint signal (x_cons) indicates that the mechanism (10) should be operated in the second direction (F?), the control module (24) applies a second corrector (100) to the setpoint signal (x_cons) in order to generate a control signal (x_com), and in which the first and second correctors (100, 200) have different parameters (Kp1, Kp2, Ti1, Ti2), in order to compensate for the asymmetrical beha

Abstract: The invention relates to a method for monitoring the operating state of an overpressure valve of a turbine engine, the turbine engine comprising a fluid circuit, at least one pressure sensor for the fluid in the fluid circuit, a temperature sensor for the fluid in the fluid circuit, said overpressure valve being configured to limit the maximum fluid pressures in the fluid circuit, and the method comprising the following steps:—(E2) determining an opening or closing indicator of the overpressure valve on the basis of the change in the fluid pressure over time;—(E3) determining an operating state of the valve as a function of a fluid threshold temperature and of the determined opening or closing indicator of the overpressure valve.

Abstract: The invention relates to a method for the closed-loop control of a proportional integral-type controller (2) in an instrumentation and control device (1) of a closed-loop control system (3), in particular a servovalve-actuator system, said controller (2) including a setpoint-weighting coefficient (?), said closed-loop control method comprising the consecutive steps of assigning (11) a unit value to the set-point weighting coefficient (?), optimizing (12) a closed-loop control of the controller (2) satisfying at least one predefined performance criterion, defining a characteristic tracking error (?TC) making it possible to respond to the performance constraints of the system to be closed-loop controlled, and assigning (132) a setpoint weighting coefficient (?) value, depending on the characteristic tracking error (?TC) and the closed-loop control of the controller (2).

Abstract: The invention relates to a lubricating oil circuit (CL) of a turbomachine, comprising a distribution valve (V) configured to distribute, as a function of an oil flow rate distribution control signal (COM), an oil flow rate among a first heat exchanger (ECH1) positioned in contact with a secondary gas flow (14) of the turbomachine (10) to cool the oil therein and a bypass duct (DER), connected to an oil duct (CEq), which is connected to an heat exchanger (ECH2) positioned against a turbomachine fuel passage duct to cool the oil therein.