Abstract: A device for ventilating and electrically powering a computer of an engine of an aircraft, the device including a feed mechanism feeding air to a proximity of the computer and a fan connected to a drive mechanism and configured to generate a stream of air for ventilating the computer. The fan is mounted in the air feed mechanism, and the drive mechanism includes an electrical machine configured to operate as a motor for driving the fan, and as a generator for powering the computer, a rotor of the machine when operating as a generator being driven by the fan, which is itself driven by a stream of air flowing in or leaving the air feed mechanism.

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 manual mechanical drive to a high pressure sub assembly of a turbojet during endoscopic inspection of the high pressure turbine is provided. A coupling element suitable for coupling with an external actuator such as a crank handle is fitted on the axis of an alternator that is normally driven mechanically via the high pressure sub assembly, thereby providing a coupling suitable for driving said high pressure sub assembly.

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: The present invention relates to anti-Axl antibodies and uses thereof in diagnostic and therapeutic methods. More particularly, the present invention relates to a monoclonal antibody having specificity for Axl comprising an heavy chain variable region comprising SEQ ID NO:2 in the H-CDR1 region, SEQ ID NO:3 in the H-CDR2 region and SEQ ID NO:4 in the H-CDR3 region; and a light chain variable region comprising SEQ ID NO: 6 in the L-CDR1 region, SEQ ID NO:7 in the L-CDR2 region and SEQ ID NO:8 in the L-CDR3 region. Said monoclonal antibody binds to the extracellular domain of Axl via, SEQ ID NO:9, SEQ ID NO: 10 and SEQ ID NO: 11.

Abstract: The present invention relates to anti-Axl antibodies and uses thereof in diagnostic and therapeutic methods. More particularly, the present invention relates to a monoclonal antibody having specificity for Axl comprising an heavy chain variable region comprising SEQ ID NO:2 in the H-CDR1 region, SEQ ID NO:3 in the H-CDR2 region and SEQ ID NO:4 in the H-CDR3 region; and a light chain variable region comprising SEQ ID NO: 6 in the L-CDR1 region, SEQ ID NO:7 in the L-CDR2 region and SEQ ID NO:8 in the L-CDR3 region. Said monoclonal antibody binds to the extracellular domain of Axl via, SEQ ID NO:9 and SEQ ID NO: 10.

Abstract: A device for changing a transmission ratio between a turbine shaft and a shaft of a starter-generator of an aeroengine, the device including: first and second fixed gear wheels carried by the shaft of the starter-generator; first and second idler gearwheels carried by the turbine shaft, and meshing respectively with the first and second fixed gearwheels to define different gear ratios; a changeover sleeve interposed between the idler gearwheels and mechanically coupled to the turbine shaft, the changeover sleeve being movable in translation on the turbine shaft between two coupling positions; and a mechanism causing the changeover sleeve to move in translation automatically from either one of its coupling positions to the other one when the sum of torques between the turbine shaft and the starter-generator shaft changes sign.

Abstract: A system for controlling at least two variable geometry apparatuses of a gas turbine engine that includes at least a first body and a second body, the first apparatus including a stator blade stage with a variable setting angle of a compressor of the first body capable of switching between a closed position in an idle mode and an open position in a high-speed mode, and the second apparatus including at least one discharge valve of a compressor of the second body capable of switching between an open position in an idle mode and a closed position in a high-speed mode. The system further includes an actuator for actuating the two apparatuses.

Abstract: A system for controlling at least two sets of variable geometry equipment of a gas turbine engine including at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. An actuator actuates the two sets of equipment.

Abstract: A system for controlling at least two sets of variable geometry equipment of a turbine engine. The turbine engine includes at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. The actuator drives the second set of equipment by an actuating part that is actuated over part of the course of the actuator and idle on an abutment over the rest of the course, and by a sliding joining element providing a backlash in the actuation of the second set of equipment.

Abstract: The device comprises first means for determining a pressure value relative to the pressure at the outlet of a precooler of an air bleed system and second means for calculating the air bleed level using this pressure value, said first means comprising means for calculating a first pressure value at the outlet of the precooler, using the pressure measured by a sensor, means for receiving a pressure measured by a second sensor, which represents a second pressure value at the outlet of the precooler and means for selecting one of said first and second pressure values, which is then transmitted to said second means for calculating said air bleed level.

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 controlling a clearance between tips of blades of a turbine rotor of a gas turbine aircraft engine and a ring-shaped turbine shroud of a housing surrounding the blades, the method including: controlling flow and/or temperature of air directed toward the housing according to an estimate of the clearance, the estimate of the clearance is determined upon start-up of the aircraft engine, according to a temperature measured by a temperature sensor including a sensitive element positioned in a free space of the aircraft engine.

Abstract: A control system for controlling at least two variable-geometry devices of a turbomachine, and a turbomachine including such a control system, the system including an actuator that actuates both devices; one of the devices including at least one stage of variable-pitch stator vanes, and the other device being an air-bleed valve for a turbomachine body. The system is configured to control progression opening of the vane stage and progressive closing of the air-bleed valve as an actuation parameter of the actuator increases. As a result, the control system serves advantageously to control two devices using a single control 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: An electrical connection system for an analysis system and a method for analysis of a liquid sample on an analytical test element using the described analysis system are disclosed. The analysis system provides an evaluation appliance for evaluation of electrical signals, a test element holder for holding and positioning of an analytical test element in a measurement position, and an electrical contact element which makes electrical contact with an electrical contact surface of an analytical test element to produce an electrical connection between the contact surface and the evaluation appliance. The contact element is moved by means such that contact with the electrical contact surface of the test element is made when the test element holder is in the measurement position.

Abstract: A control of a fuel metering device for a turbine engine as a function of a weight flow rate setpoint includes responding to at least one validity criterion to select a weight flow rate from among: a weight flow rate calculated as a function of a position signal; a weight flow rate calculated as a function of the position signal and of at least one temperature measurement signal; a weight flow rate calculated as a function of the position signal and of at least one permittivity measurement signal; a weight flow rate calculated as a function of the position signal, of at least one temperature measurement signal, and of at least one permittivity measurement signal; and a weight flow rate calculated as a function of a temperature measurement signal, of a permittivity measurement signal, and of a volume flow rate measurement signal.

Abstract: A system and method for controlling clearance between tips of moving blades of an aeroplane gas-turbine engine and a turbine shroud of an outer casing surrounding the blades. The method includes controlling, according to an operating speed of the engine, a valve positioned in an air duct opening at a stage of the compressor of the engine and leading into a control housing positioned around the outer surface of the turbine shroud and supplied with air coming only from the compressor stage. The valve is opened to cool the turbine shroud during a high-speed phase corresponding to takeoff and climb phases of an aeroplane propelled by the engine and during a nominal-speed phase following the high-speed phase and corresponding to a cruise phase of the aeroplane.

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.