Patent application number | Description | Published |
20100080684 | SYSTEM FOR CONTROLLING VARIABLE-GEOMETRY EQUIPMENTS OF A TURBOMACHINE, PARTICULARLY BY ARTICULATED BELLCRANKS - A system for controlling at least two variable-geometry equipments ( | 04-01-2010 |
20100158662 | SYSTEM FOR CONTROLLING AT LEAST TWO VARIABLE-GEOMETRY EQUIPMENTS OF A GAS TURBINE ENGINE, PARTICULARLY BY RACK - The invention relates to a system for controlling at least two variable-geometry equipments of a gas turbine engine. The engine comprises at least a first core rotating at a first speed and a second core rotating at a second speed, the first equipment ( | 06-24-2010 |
20100158663 | SYSTEM FOR CONTROLLING AT LEAST TWO VARIABLE-GEOMETRY EQUIPMENTS OF A GAS TURBINE ENGINE, PARTICULARLY BY CAM MECHANISM - The invention relates to a system for controlling at least two variable-geometry equipments of a gas turbine engine. The engine comprises at least a first core rotating at a first speed and a second core rotating at a second speed, the first equipment ( | 06-24-2010 |
20110150567 | MECHANICAL DRIVE DEVICE FOR DRIVING THE HIGH PRESSURE SUB ASSEMBLYSUB ASSEMBLY OF AN AIRPLANE ENGINE - Providing manual mechanical drive to the high pressure sub assembly of a turbojet, in particular during endoscopic inspection of the high pressure turbine. According to the invention, a coupling element suitable for coupling with an external actuator such as a crank handle is fitted on the axis of a specific alternator that is normally driven mechanically via the high pressure sub assembly, thereby providing a coupling suitable for driving said high pressure sub assembly. | 06-23-2011 |
20110182716 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY APPARATUSES IN A TURBINE ENGINE - 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. | 07-28-2011 |
20110184573 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY EQUIPMENT FOR A TURBINE ENGINE, ESPECIALLY BY BELLCRANKS - 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. | 07-28-2011 |
20110190950 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY EQUIPMENT OF A GAS TURBINE ENGINE ESPECIALLY COMPRISING A GUIDING TRACK CONNECTION - 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. | 08-04-2011 |
20110229310 | SYSTEM FOR CONTROLLING VARIABLE GEOMETRY EQUIPMENT OF A GAS TURBINE ENGINE PARTICULARLY COMPRISING A BARREL LINK - 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. | 09-22-2011 |
20110246151 | METHOD AND A SYSTEM FOR ESTIMATING A STREAM TEMPERATURE IN A TURBOJET - 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. | 10-06-2011 |
20120107088 | DEVICE AND METHOD FOR POSITIONING VARIABLE-GEOMETRY EQUIPMENT FOR A TURBOMACHINE, USING A RELATIVE-MEASUREMENT JACK - A device for controlling positioning of variable-geometry equipment of a turbomachine, including a computer, an actuator of variable geometry driven by the computer, and a drive train, the actuator including moving parts including a sensor for measuring its elongation, the drive train being connected at one of its ends to a point of attachment of the moving parts and at another end to a point of attachment of the equipment, the point of attachment moving under action of the actuator along a travel limited by an end stop and the drive train being elastically deformable under the action of the actuator when the point of attachment is against the end stop. An elongation instruction supplied by the computer to the moving parts is defined as a difference with respect to the value of the elongation of the moving parts that corresponds to contact between the point of attachment and the end stop. | 05-03-2012 |
20120201651 | CONTROL UNIT AND A METHOD FOR CONTROLLING BLADE TIP CLEARANCE - 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. | 08-09-2012 |
20120279334 | DEVICE FOR CHANGING THE TRANSMISSION RATIO BETWEEN A TURBINE SHAFT AND A SHAFT OF A STARTER-GENERATOR OF AN AEROENGINE - 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. | 11-08-2012 |
20130031949 | METHOD AND A DEVICE FOR CORRECTING A MEASUREMENT OF THE PRESSURE OF A GAS STREAM FLOWING IN AN AIRCRAFT ENGINE - A method to correct a current measurement of pressure of a gas stream delivered during a mission by a sensor in the engine. The method includes: estimating a drift error affecting the sensor on the basis of a difference existing between: (1) a calibration measurement of the pressure of the gas stream as delivered by the sensor in the engine, and (2) an atmospheric pressure measurement delivered by a sensor of the aircraft presenting accuracy greater than that of the sensor in the engine; these measurements being performed while the sensor in the engine and the sensor of the aircraft are subjected to same surrounding atmospheric pressure; and subtracting the estimated drift error from the current measurement. | 02-07-2013 |
20130091851 | METHOD AND A DEVICE FOR PRODUCING A SETPOINT SIGNAL - 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. | 04-18-2013 |
20130177414 | METHOD AND SYSTEM FOR CONTROLLING THE CLEARANCE AT THE BLADES TIPS OF A TURBINE ROTOR - 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. | 07-11-2013 |
20130186096 | METHOD FOR MONITORING A FUEL CIRCUIT SHUT-OFF VALVE - The invention relates to a method for monitoring the operation of a fuel circuit shut-off valve comprising an LPSOV, a flow regulator, the shut-off valve, characterised in that it comprises:
| 07-25-2013 |
20130213053 | CONTROL OF A FUEL METERING DEVICE FOR TURBOMACHINE - 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. | 08-22-2013 |
20130255221 | METHOD OF CONTROLLING A TURBOMACHINE - 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. | 10-03-2013 |
20130323016 | METHOD FOR CONTROLLING THE CLEARANCE AT THE TIPS OF BLADES OF A TURBINE ROTOR - 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. | 12-05-2013 |
20140090458 | METHOD AND DEVICE FOR DETERMINING THE AIR BLEED ON AN AIRCRAFT TURBOJET ENGINE - 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. | 04-03-2014 |
20150082802 | TURBOMACHINE COMPRISING A MONITORING SYSTEM COMPRISING A MODULE FOR ENGAGING A PROTECTION FUNCTION OF THE TURBOMACHINE AND MONITORING METHOD - An aircraft turbine engine comprising at least one spool rotating at speed N | 03-26-2015 |