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EP2307868A1 - System and method for correcting the measurement of a pre-turbine pressure sensor - Google Patents

System and method for correcting the measurement of a pre-turbine pressure sensor

Info

Publication number
EP2307868A1
EP2307868A1 EP09794016A EP09794016A EP2307868A1 EP 2307868 A1 EP2307868 A1 EP 2307868A1 EP 09794016 A EP09794016 A EP 09794016A EP 09794016 A EP09794016 A EP 09794016A EP 2307868 A1 EP2307868 A1 EP 2307868A1
Authority
EP
European Patent Office
Prior art keywords
pressure
sensor
measurement
correction
temperature
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP09794016A
Other languages
German (de)
French (fr)
Inventor
Kevin Robert
Alexandre Collet
Christophe Beucher
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Renault SAS
Original Assignee
Renault SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Renault SAS filed Critical Renault SAS
Publication of EP2307868A1 publication Critical patent/EP2307868A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/0002—Controlling intake air
    • F02D41/0007—Controlling intake air for control of turbo-charged or super-charged engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D23/00—Controlling engines characterised by their being supercharged
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/02—Circuit arrangements for generating control signals
    • F02D41/14—Introducing closed-loop corrections
    • F02D41/1438—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor
    • F02D41/1444—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor characterised by the characteristics of the combustion gases
    • F02D41/1446—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor characterised by the characteristics of the combustion gases the characteristics being exhaust temperatures
    • F02D41/1447—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor characterised by the characteristics of the combustion gases the characteristics being exhaust temperatures with determination means using an estimation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/02—Circuit arrangements for generating control signals
    • F02D41/14—Introducing closed-loop corrections
    • F02D41/1438—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor
    • F02D41/1444—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor characterised by the characteristics of the combustion gases
    • F02D41/1448—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor characterised by the characteristics of the combustion gases the characteristics being an exhaust gas pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/24—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means
    • F02D41/2406—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means using essentially read only memories
    • F02D41/2409—Addressing techniques specially adapted therefor
    • F02D41/2412—One-parameter addressing technique
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/24—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means
    • F02D41/2406—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means using essentially read only memories
    • F02D41/2425—Particular ways of programming the data
    • F02D41/2429—Methods of calibrating or learning
    • F02D41/2451—Methods of calibrating or learning characterised by what is learned or calibrated
    • F02D41/2474—Characteristics of sensors
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L9/00—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
    • G01L9/12—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means by making use of variations in capacitance, i.e. electric circuits therefor
    • G01L9/125—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means by making use of variations in capacitance, i.e. electric circuits therefor with temperature compensating means
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N11/00—Monitoring or diagnostic devices for exhaust-gas treatment apparatus, e.g. for catalytic activity
    • F01N11/002—Monitoring or diagnostic devices for exhaust-gas treatment apparatus, e.g. for catalytic activity the diagnostic devices measuring or estimating temperature or pressure in, or downstream of the exhaust apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N2560/00—Exhaust systems with means for detecting or measuring exhaust gas components or characteristics
    • F01N2560/06—Exhaust systems with means for detecting or measuring exhaust gas components or characteristics the means being a temperature sensor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N2560/00—Exhaust systems with means for detecting or measuring exhaust gas components or characteristics
    • F01N2560/08—Exhaust systems with means for detecting or measuring exhaust gas components or characteristics the means being a pressure sensor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N2560/00—Exhaust systems with means for detecting or measuring exhaust gas components or characteristics
    • F01N2560/14—Exhaust systems with means for detecting or measuring exhaust gas components or characteristics having more than one sensor of one kind
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B29/00—Engines characterised by provision for charging or scavenging not provided for in groups F02B25/00, F02B27/00 or F02B33/00 - F02B39/00; Details thereof
    • F02B29/04—Cooling of air intake supply
    • F02B29/0406—Layout of the intake air cooling or coolant circuit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/02—Circuit arrangements for generating control signals
    • F02D41/14—Introducing closed-loop corrections
    • F02D41/1401—Introducing closed-loop corrections characterised by the control or regulation method
    • F02D2041/1413—Controller structures or design
    • F02D2041/1422—Variable gain or coefficients
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/24—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means
    • F02D41/26—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means using computer, e.g. microprocessor
    • F02D41/28—Interface circuits
    • F02D2041/286—Interface circuits comprising means for signal processing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/02—Circuit arrangements for generating control signals
    • F02D41/14—Introducing closed-loop corrections
    • F02D41/1438—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor
    • F02D41/1444—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor characterised by the characteristics of the combustion gases
    • F02D41/1446—Introducing closed-loop corrections using means for determining characteristics of the combustion gases; Sensors therefor characterised by the characteristics of the combustion gases the characteristics being exhaust temperatures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/24—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means
    • F02D41/2406—Electrical control of supply of combustible mixture or its constituents characterised by the use of digital means using essentially read only memories
    • F02D41/2409—Addressing techniques specially adapted therefor
    • F02D41/2416—Interpolation techniques
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/02—EGR systems specially adapted for supercharged engines
    • F02M26/04—EGR systems specially adapted for supercharged engines with a single turbocharger
    • F02M26/05—High pressure loops, i.e. wherein recirculated exhaust gas is taken out from the exhaust system upstream of the turbine and reintroduced into the intake system downstream of the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/02—EGR systems specially adapted for supercharged engines
    • F02M26/09—Constructional details, e.g. structural combinations of EGR systems and supercharger systems; Arrangement of the EGR and supercharger systems with respect to the engine
    • F02M26/10—Constructional details, e.g. structural combinations of EGR systems and supercharger systems; Arrangement of the EGR and supercharger systems with respect to the engine having means to increase the pressure difference between the exhaust and intake system, e.g. venturis, variable geometry turbines, check valves using pressure pulsations or throttles in the air intake or exhaust system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/13—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories
    • F02M26/22—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories with coolers in the recirculation passage
    • F02M26/23—Layout, e.g. schematics
    • F02M26/25—Layout, e.g. schematics with coolers having bypasses
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M26/00—Engine-pertinent apparatus for adding exhaust gases to combustion-air, main fuel or fuel-air mixture, e.g. by exhaust gas recirculation [EGR] systems
    • F02M26/13—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories
    • F02M26/42—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories having two or more EGR passages; EGR systems specially adapted for engines having two or more cylinders
    • F02M26/44—Arrangement or layout of EGR passages, e.g. in relation to specific engine parts or for incorporation of accessories having two or more EGR passages; EGR systems specially adapted for engines having two or more cylinders in which a main EGR passage is branched into multiple passages
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present invention relates to the reliability of the control of supercharging pressures of an internal combustion engine, and more particularly, the correction of the measurement of a pressure sensor whose measured value varies according to the temperature of the sensor.
  • the operating conditions of a diesel engine limit its specific power, that is to say the ratio of the effective power to the engine displacement.
  • the effective power of the engine varies according to the mass of air admitted, the optimization of the air filling of the cylinders by increasing the density of the intake air makes it possible to obtain the best performance of the engine.
  • the internal combustion engine operates as a positive displacement pump, it always sucks the same volume of air.
  • the supercharging principle consists of compressing air through a compressor and then cooling it through an exchanger placed between the compressor and the engine. The objective of the supercharging is to be able to bring the best possible dynamics to the supercharging pressure, while respecting the criteria of reliability of the engine and its organs, ie the turbo speed, the pressure in the engine. charge air cooler, compressor outlet temperature, turbine front pressure, and expansion ratio.
  • Turbine pressure information is used in the boost regulation strategy to provide reliability reliability. Since the dynamics of the pressure before the turbine is greater than that of the boost pressure, the pressure before the turbine responds to a movement of the fins due to a very small volume of the exhaust manifold. In addition, the pressure before turbine is a physical information entering directly into the calculation the power recovered by the expansion in the turbine. Thus, at the same level of boost pressure set point and the same operating point of the engine, the same level of pressure before turbine will be reached.
  • the front turbine pressure control makes it possible to anticipate the reopening of the turbocharger fins with good precision despite the dispersions of the control chain and thus to control the excess of the boost pressure.
  • the pressure information before turbine must be reliable so that the control is robust.
  • the supercharging regulation is subject to two main sources of dispersions, namely the control chain comprising the solenoid valve, the spring loaded lung and the linkage mechanism between the rod and the fins, and the turbine front pressure sensor.
  • the turbine front pressure sensor is a capacitive type pressure sensor.
  • the pressure of the exhaust gases deforms the measuring diaphragm, modifies the distance between the electrodes and thus the capacity of the sensor.
  • the electrical signal that is then delivered is a linear function of the measured absolute pressure.
  • the membranes used for this type of sensor are also sensitive to temperature. The measured value for the pressure can thus differ according to the temperature of the sensor for two different measurements at the same value of real pressure.
  • the metrological characteristics of the pressure sensor induce a dispersion of the error as a function of the actual pressure and the temperature of the engine. sensor.
  • the characteristic of the pressure sensor can change as a function of time, following, for example, aging or fouling of the sensor, resulting in drift of the error which can also vary depending on the temperature.
  • US patent application 2002/0060150 describes a strategy for detecting the degradation of a gas sensor placed in the exhaust manifold. This strategy is capable of detecting an internal resistance change of the sensor and of analyzing the causes of the degradation by analyzing the signal fluctuations by comparing the current values of the internal resistance of the sensor and the heating element with respect to nominal values, but without being able to correct any error in the measurement.
  • US patent application 2007/0073503 describes a method for correcting the temperature-dependent pressure measurement dispersion for a pneumatic pressure sensor equipped with a pressure sensor and a temperature sensor.
  • the measured pressure is referenced at a defined temperature, equivalent to the law of evolution between the pressure and the temperature of the gases contained in a constant volume.
  • the principle of the method is to calculate the offset between the temperature measured by the sensor and the actual temperature in the tire, then correct the current value of temperature measured by this offset.
  • the object of the present invention is to correct the drifts and dispersions of the "pressure before turbine" information delivered by a pressure sensor whose measurement is sensitive to its own temperature.
  • a system for correcting the measurement of a pressure sensor more particularly a pressure sensor before turbine.
  • the system advantageously comprises means for determining the temperature of the pressure sensor, data storage means characterizing the dispersion and / or the drift of measurement of the sensor as a function of temperature, correction means able to determine a corrective term to be applied to the values measured by the sensor as a function of the stored data, said correction means comprising means for correcting the dispersion of pressure measurement measured by the sensor and means for correcting the drift measurement of the pressure measured by the sensor.
  • the correction means comprise means capable of delivering a correction value of the measurement of the pressure of the sensor, in particular mappings, or an analytical model.
  • the characterization of the means for correcting the dispersion of the measurement of the pressure measured by the pressure sensor is preferably carried out on a test bench or engine bench.
  • the characterization of the correction means of the measurement drift of the pressure measured by the sensor is carried out directly on the engine.
  • the means for determining the temperature of the pressure sensor may consist of a temperature sensor placed near the pressure sensor.
  • the means for determining the temperature of the pressure sensor can be estimated using a model for estimating the temperature of the pressure sensor.
  • a method for correcting the measurement of a pressure sensor more particularly a pressure sensor before turbine.
  • the temperature of the pressure sensor is advantageously determined, a correction value of the measurement dispersion of the pressure as a function of the temperature is calculated, and the measured pressure is corrected from the correction value of the measurement dispersion of the pressure sensor. pressure to obtain the value of the corrected pressure of the dispersion.
  • a correction value of the drift of measurement of the pressure is preferably calculated, and the pressure measured at from the correction value of the pressure drift drift to obtain the corrected drift pressure value.
  • a coefficient of correction of the measurement pressure drift of the sensor is determined, quantifying the measurement error existing between the measured pressure and a reference pressure, said coefficient being independent of the temperature.
  • the pressure value is advantageously corrected from the value of the corrected pressure of the dispersion and from the correction value of the pressure measurement drift, the correction of the pressure measurement drift being calculated from a coefficient of correction of the sensor pressure drift quantifying the error between the dispersion corrected pressure and the reference pressure.
  • a correction matrix for the sensor pressure measuring dispersion is preferably constructed, quantifying the error on the pressure sensor measurement as a function of the component temperature and the measured pressure.
  • a correction vector of the measurement pressure drift of the sensor is preferably determined, quantifying the measurement error existing between the dispersion-corrected pressure and the reference pressure as a function of the temperature of the pressure sensor.
  • FIG. 1 schematically describes the architecture of FIG. an engine comprising a pressure sensor before turbine
  • FIG. 2 illustrates an exemplary control architecture of the measurement dispersion correction of the front turbine pressure sensor
  • FIG. 3 illustrates an exemplary control architecture of the measurement dispersion correction of the front turbine pressure sensor
  • FIG. 4 illustrates an exemplary control architecture for determining the correction coefficient of the measurement drift of the front turbine pressure sensor
  • FIG. 5 illustrates an exemplary control architecture of the determination of the dispersion-corrected pressure and the measurement drift of the turbine-front pressure sensor.
  • FIG. 1 very schematically shows the general structure of a diesel-type internal combustion engine 1 supercharged by a turbocharger 2 comprising an electronic control unit or computer 3 making it possible to control the internal combustion engine 1 and all of its sensors and actuators using all the control laws contained in software forms and characterization parameters for calibrating the various elements.
  • the turbocharger 2 is composed of a compressor 4 and a turbine 5 whose role is to increase the amount of air admitted into the cylinders 6 of the internal combustion engine 1.
  • the turbine 5, placed at the outlet of the collector 7, is driven by the exhaust gas thus generating a rotational movement to the compressor 4 mounted on the same axis 8 as the turbine 5 and placed at the inlet of the intake manifold 9, thus compressing the air charge from the low pressure air intake line 10 comprising an air filter 1 1 and a mass flowmeter 12 of fresh air, and entering the high pressure air intake line 13 which may furthermore comprise an exchanger 14 for cooling the charge air and a flap 15 of intake air.
  • the power provided by the exhaust gases to the turbine 5 may be modulated by installing a relief valve or fins controlled by the electronic control unit 3, in the case of a variable geometry turbine.
  • the inlet and outlet pressures, whose setpoints are calculated by the electronic control unit 3, are measured by two pressure sensors 15 and 16 respectively placed on the intake manifold 9 and on the exhaust manifold 7.
  • a high pressure exhaust gas recirculation circuit 17 may be mounted between the intake manifold 9 and the exhaust manifold 7. This circuit 17 may comprise an exchanger 18 for cooling the exhaust gas recirculating towards the exhaust manifold. admission, and a bypass valve 19 of the circuit 17.
  • the sensor 20 measures the ambient pressure of the air at the inlet of the compressor 4, the sensors 21 and 22 measure the boost pressure respectively before and after the intake air flap 15.
  • the sensor 23 measures the pressure before turbine, and the sensor 24 measures the pressure of the exhaust gas after the turbine 5 escaping in the exhaust line 25.
  • All relative absolute or differential pressure information of the intake air or the exhaust gas may be measured by a pressure sensor whose raw signals are processed by the electronic control unit 3. in order to condition them for the control strategies of the engine 1.
  • a temperature sensor 26 placed near the pressure sensor 23 measures the temperature of said pressure sensor 23.
  • FIG. 2 shows an exemplary control architecture for determining the value of the corrected pressure of the measurement dispersion of the front turbine pressure sensor 23 from a vector for correcting the measurement dispersion of the sensor.
  • the first pressure is measured by means of the pressure sensor 23.
  • the temperature of the pressure sensor 23 is then measured with the aid of the temperature sensor 26.
  • the value of the pressure sensor 23 is then measured. the temperature of the pressure sensor 23 to the correction means 30 of the pressure measurement dispersion before the turbine.
  • the correction means 30 calculate the corrective value using a correction vector of the measurement dispersion of the sensor. pressure sensor before turbine 23 built during the characterization on a motor bench, or a bench of organs, of the measuring error of the sensor 230.
  • the correction vector of the measurement dispersion of the pressure sensor 23 is constructed from the quantization values of the measurement error of the front turbine pressure sensor 23 as a function of its temperature.
  • the quantified measurement error is expressed in absolute value or in relative value.
  • the measurement dispersion correction vector of the turbine front pressure sensor 23 is constructed using a mapping, an analytical model, or any other means for delivering a correction value of the measurement drift of the front pressure sensor turbine 23.
  • a correction value of the pressure measurement dispersion is thus calculated from the value of the temperature measured by the temperature sensor 23 introduced into the correction means 30. It is then combined with a means 31 combining the value of the pressure measured by the pressure sensor 23 and the correction value of the pressure measurement dispersion in order to obtain a value of the pressure corrected for the dispersion.
  • the combination is additive in the case of absolute values, and multiplicative in the case of relative values.
  • FIG. 3 shows an exemplary control architecture for determining the value of the corrected pressure of the drift of the measurement of the front turbine pressure sensor 23 from a correction coefficient of the measurement dispersion of the front pressure sensor turbine 23.
  • the value of the pressure measured by the front turbine pressure sensor 23 is combined by means of a combination means 32 subtractive to the correction value of the measurement drift of the front pressure sensor turbine delivered by correction means 33 of the measuring drift of the front turbine pressure sensor 23. From the combination of these two values, the value of the corrected pressure of the drift is obtained.
  • the pressure measured by the turbine front pressure sensor 23 can be replaced by the value of the pressure corrected for the dispersion.
  • the combination thus produced to obtain the value of the corrected pressure corresponding to the corrected pressure of the dispersion and the measurement drift of the front turbine pressure sensor 23.
  • the correction means 33 of the measurement drift perform a characterization phase of the correction of the measurement drift carried out directly on the engine 1 before the application phase seen previously with FIG. 3.
  • the correction means 33 quantify the measurement error existing between the measured pressure and a reference pressure, measuring error being expressed in absolute or relative value. From the values obtained, a correction coefficient of the measurement drift is obtained by means of a cartography, an analytical model, or any other means making it possible to deliver a correction value of the measurement drift of the measurement drift. pressure before turbine.
  • the reference pressure is delivered by a pressure sensor or estimated from a physical model.
  • an atmospheric pressure sensor 20 is used to deliver the reference pressure because of its low measurement dispersion.
  • Other pressure sensors may also serve as a reference if their measurement dispersion is smaller than that of the front turbine pressure sensor 23.
  • the value of the correction coefficient of the measurement drift determined during the characterization phase is stored in data storage means 34 such as an EEPROM memory.
  • the characterization phase of the correction of the measurement drift makes it possible to determine the correction vector of the measurement drift of the front turbine pressure sensor 23.
  • it is quantified. the measurement error between the corrected pressure of the measurement dispersion and a reference pressure as a function of the temperature of the pressure sensor 23 measured with the aid of the temperature sensor 26 or estimated using a temperature model of the pressure sensor 23.
  • the correction vector of the measurement drift of the pressure sensor is stored in data storage means 34 such as an EEPROM memory.
  • the pressure is first measured with the aid of the pressure sensor 23 and the value is introduced into the measuring means. corrections of the measurement dispersion with the value of the temperature of the pressure sensor 23 measured with the aid of the temperature sensor 26.
  • the corrective means 30 calculate this time the corrective value using a measurement dispersion correction matrix of the front turbine pressure sensor 23 constructed during the characterization on a driving bench, or a bench of organs, of the measurement error of the front turbine pressure sensor 23.
  • the matrix is constructed from the quantization values of the measurement error of the front turbine pressure sensor 23 as a function of the measured pressure and its temperature.
  • the quantified measurement error is expressed in absolute value or in relative value.
  • the measurement dispersion correction matrix of the front turbine pressure sensor 23 is constructed using a mapping, an analytical model, or any other means for delivering a correction value of the measurement drift of the front pressure sensor turbine 23.
  • a correction value of the pressure measurement dispersion is thus calculated from the value of the temperature measured by the temperature sensor 26 introduced into the correction means 30.
  • the value is then combined. the pressure measured by the pressure sensor 23 and the correction value of the pressure measurement dispersion in order to obtain the value of the pressure corrected for the dispersion.
  • the combination is additive in the case of absolute values, and multiplicative
  • the value of the temperature of the front turbine pressure sensor 23 measured with the aid of the temperature sensor 26 is introduced into the correction means 33 of the measurement drift of the sensor. pressure before turbine 23. From the correction vector of the measurement drift of the front turbine pressure sensor 23 and the value of the measured temperature, the value of the correction of the measurement drift of the front turbine pressure sensor is determined. 23 by the correction means 33. The value of the correction of the measurement drift of the turbine front pressure sensor 23 is combined with the value of the corrected pressure of the measurement dispersion of the front turbine pressure sensor 23 in order to obtain the value of the corrected pressure which is thus corrected for the dispersion and the measurement drift of the front turbine pressure sensor 23.
  • control method are applicable to all pressure sensors of the relative, absolute or differential type, placed on an engine intake or exhaust circuit and whose characteristics include a measurement drift sensitive to the engine. crushing and aging of the sensor relatively continuous as a function of time and not exceeding acceptable error limits, and a measurement dispersion resulting from the manufacture of the sensor, sensitive to the measured pressure and the ambient temperature.

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Abstract

The invention relates to a system and to a method for correcting the measurement of a pressure sensor, more particularly of a pre-turbine pressure sensor 23. The system includes: means 26 for determining the temperature of the pressure sensor; means 34 for storing data characterizing the measurement dispersion and/or the measurement drift of the sensor as a function of temperature; and correcting means 40 capable of determining a corrective term to apply to the values measured by the sensor on the basis of the stored data and including means 30 for correcting the measurement dispersion of the pressure measured by the sensor and means 33 for correcting the measurement drift of the pressure measured by the sensor.

Description

Système et procédé de correction de la mesure d'un capteur de pression avant turbine System and method for correcting the measurement of a pressure sensor before turbine
La présente invention concerne la fiabilité de la commande de pressions de suralimentation d'un moteur à combustion interne, et plus particulièrement, la correction de la mesure d'un capteur de pression dont la valeur mesurée varie suivant la température du capteur.The present invention relates to the reliability of the control of supercharging pressures of an internal combustion engine, and more particularly, the correction of the measurement of a pressure sensor whose measured value varies according to the temperature of the sensor.
Les conditions de fonctionnement d'un moteur diesel limitent sa puissance spécifique, c' est-à-dire le rapport de la puissance effective sur la cylindrée du moteur. La puissance effective du moteur variant en fonction de la masse d' air admise, l'optimisation du remplissage en air des cylindres par l' augmentation de la masse volumique de l'air d'admission permet d'obtenir les meilleures performances du moteur. Le moteur à combustion interne fonctionnant comme une pompe volumétrique, il aspire toujours le même volume d' air. Le principe de suralimentation consiste à comprimer de l' air à travers un compresseur, puis de le refroidir au travers d'un échangeur placé entre le compresseur et le moteur. L 'objectif de la suralimentation est de parvenir à apporter la meilleure dynamique possible à la pression de suralimentation, tout en respectant les critères de fiabilité du moteur et de ses organes, c 'est-à- dire le régime turbo, la pression dans le refroidisseur d' air de suralimentation, la température de sortie du compresseur, la pression avant turbine, et le taux de détente.The operating conditions of a diesel engine limit its specific power, that is to say the ratio of the effective power to the engine displacement. The effective power of the engine varies according to the mass of air admitted, the optimization of the air filling of the cylinders by increasing the density of the intake air makes it possible to obtain the best performance of the engine. The internal combustion engine operates as a positive displacement pump, it always sucks the same volume of air. The supercharging principle consists of compressing air through a compressor and then cooling it through an exchanger placed between the compressor and the engine. The objective of the supercharging is to be able to bring the best possible dynamics to the supercharging pressure, while respecting the criteria of reliability of the engine and its organs, ie the turbo speed, the pressure in the engine. charge air cooler, compressor outlet temperature, turbine front pressure, and expansion ratio.
On cherche ainsi à optimiser le fonctionnement du moteur en optimisant à la fois le dépassement de la pression de suralimentation et la dynamique de la pression de suralimentation.It is thus sought to optimize the operation of the engine by optimizing both the exceeding of the boost pressure and the dynamics of the boost pressure.
L 'information de pression avant turbine est utilisée dans la stratégie de régulation de suralimentation afin d'y apporter de la robustesse en fiabilité. La dynamique de la pression avant turbine étant supérieure à celle de la pression de suralimentation, la pression avant turbine répond à un mouvement des ailettes grâce à un volume du collecteur d'échappement très faible. De plus, la pression avant turbine est une information physique entrant directement dans le calcul de la puissance récupérée par la détente dans la turbine. Ainsi, à un même niveau de consigne de pression de suralimentation et un même point de fonctionnement du moteur, le même niveau de pression avant turbine sera atteint. La commande de pression avant turbine permet d' anticiper la réouverture des ailettes du turbocompresseur avec une bonne précision malgré les dispersions de la chaîne de commande et ainsi de maîtriser le dépassement de pression de suralimentation. L'information de pression avant turbine doit donc être fiable pour que la commande soit robuste.Turbine pressure information is used in the boost regulation strategy to provide reliability reliability. Since the dynamics of the pressure before the turbine is greater than that of the boost pressure, the pressure before the turbine responds to a movement of the fins due to a very small volume of the exhaust manifold. In addition, the pressure before turbine is a physical information entering directly into the calculation the power recovered by the expansion in the turbine. Thus, at the same level of boost pressure set point and the same operating point of the engine, the same level of pressure before turbine will be reached. The front turbine pressure control makes it possible to anticipate the reopening of the turbocharger fins with good precision despite the dispersions of the control chain and thus to control the excess of the boost pressure. The pressure information before turbine must be reliable so that the control is robust.
La régulation de suralimentation est soumise à deux sources principales de dispersions, à savoir la chaîne de commande comprenant l' électrovanne, le poumon avec ressort et la mécanique de liaison entre la tige et les ailettes, et le capteur de pression avant turbine. Le capteur de pression avant turbine est un capteur de pression de type capacitif. La pression des gaz d' échappement déforme la membrane de mesure, modifie la distance entre les électrodes et ainsi la capacité du capteur. Le signal électrique qui en est alors délivré est une fonction linéaire de la pression absolue mesurée. Les membranes utilisées pour ce type de capteur sont également sensibles à la température. La valeur mesurée pour la pression peut ainsi différer suivant la température du capteur pour deux mesures différentes à une même valeur de pression réelle.The supercharging regulation is subject to two main sources of dispersions, namely the control chain comprising the solenoid valve, the spring loaded lung and the linkage mechanism between the rod and the fins, and the turbine front pressure sensor. The turbine front pressure sensor is a capacitive type pressure sensor. The pressure of the exhaust gases deforms the measuring diaphragm, modifies the distance between the electrodes and thus the capacity of the sensor. The electrical signal that is then delivered is a linear function of the measured absolute pressure. The membranes used for this type of sensor are also sensitive to temperature. The measured value for the pressure can thus differ according to the temperature of the sensor for two different measurements at the same value of real pressure.
La forte sensibilité à la température de ce type de capteur de pression est le principal problème posé quant à la fiabilité de la mesure réalisée.The high sensitivity to the temperature of this type of pressure sensor is the main problem regarding the reliability of the measurement.
Outre une dispersion importante de l'erreur entre la pression réelle et la pression mesurée par le capteur dès la fabrication du moteur, les caractéristiques métrologiques du capteur de pression induisent une dispersion de l' erreur en fonction de la pression réelle et de la température du capteur. On regroupera ces deux types de dispersion, dans un unique terme de dispersion de la mesure de pression.In addition to a large dispersion of the error between the actual pressure and the pressure measured by the sensor as soon as the engine is manufactured, the metrological characteristics of the pressure sensor induce a dispersion of the error as a function of the actual pressure and the temperature of the engine. sensor. These two types of dispersion will be grouped into a single dispersion term of the pressure measurement.
D ' autre part, la caractéristique du capteur de pression peut évoluer en fonction du temps, suivant par exemple le vieillissement ou l' encrassement du capteur, ce qui entraîne une dérive de l' erreur qui peut également varier en fonction de la température.On the other hand, the characteristic of the pressure sensor can change as a function of time, following, for example, aging or fouling of the sensor, resulting in drift of the error which can also vary depending on the temperature.
Il résulte alors de ces deux sources d' erreur sur la mesure, des risques importants concernant la précision avec laquelle la régulation de suralimentation est réalisée, et par conséquent, des risques importants sur la fiabilité du moteur et de ses organes.It then results from these two sources of error on the measurement, significant risks concerning the precision with which the regulation of supercharging is carried out, and consequently, important risks on the reliability of the engine and its organs.
La demande de brevet US 2002/0060150 décrit une stratégie de détection de la dégradation d'un capteur de gaz placé dans le collecteur d' échappement. Cette stratégie est capable de détecter un changement de résistance interne du capteur et d' analyser les causes de la dégradation par analyse des fluctuations du signal en comparant les valeurs courantes de la résistance interne du capteur et de l' élément de chauffage par rapport à des valeurs nominales, mais sans pouvoir effectuer une correction d'une quelconque erreur sur la mesure.US patent application 2002/0060150 describes a strategy for detecting the degradation of a gas sensor placed in the exhaust manifold. This strategy is capable of detecting an internal resistance change of the sensor and of analyzing the causes of the degradation by analyzing the signal fluctuations by comparing the current values of the internal resistance of the sensor and the heating element with respect to nominal values, but without being able to correct any error in the measurement.
La demande de brevet US 2007/0073503 décrit une méthode de correction de la dispersion de mesure de pression suivant la température pour un capteur de pression pneumatique équipé d'un capteur de pression et d'un capteur de température. La pression mesurée est référenciée à une température définie, équivalente à la loi d'évolution entre la pression et la température des gaz contenus dans un volume constant. Le principe de la méthode est de calculer l'offset entre la température mesurée par le capteur et la température réelle dans le pneumatique, puis de corriger la valeur courante de température mesurée par cet offset.US patent application 2007/0073503 describes a method for correcting the temperature-dependent pressure measurement dispersion for a pneumatic pressure sensor equipped with a pressure sensor and a temperature sensor. The measured pressure is referenced at a defined temperature, equivalent to the law of evolution between the pressure and the temperature of the gases contained in a constant volume. The principle of the method is to calculate the offset between the temperature measured by the sensor and the actual temperature in the tire, then correct the current value of temperature measured by this offset.
La présente invention a pour but de corriger les dérives et dispersions de l'information « pression avant turbine » délivrée par un capteur de pression dont la mesure est sensible à sa propre température. Selon un aspect, il est proposé dans un mode de réalisation un système de correction de la mesure d'un capteur de pression, plus particulièrement d'un capteur de pression avant turbine.The object of the present invention is to correct the drifts and dispersions of the "pressure before turbine" information delivered by a pressure sensor whose measurement is sensitive to its own temperature. According to one aspect, there is provided in one embodiment a system for correcting the measurement of a pressure sensor, more particularly a pressure sensor before turbine.
Le système comprend avantageusement des moyens de détermination de la température du capteur de pression, des moyens de mémorisation de données caractérisant la dispersion et/ou la dérive de mesure du capteur en fonction de la température, des moyens de correction aptes à déterminer un terme correctif à appliquer aux valeurs mesurées par le capteur en fonction des données mémorisées, lesdits moyens de correction comprenant des moyens de correction de la dispersion de mesure de la pression mesurée par le capteur et des moyen de correction de la dérive de mesure de la pression mesurée par le capteur.The system advantageously comprises means for determining the temperature of the pressure sensor, data storage means characterizing the dispersion and / or the drift of measurement of the sensor as a function of temperature, correction means able to determine a corrective term to be applied to the values measured by the sensor as a function of the stored data, said correction means comprising means for correcting the dispersion of pressure measurement measured by the sensor and means for correcting the drift measurement of the pressure measured by the sensor.
De préférence, les moyens de correction comprennent des moyens aptes à délivrer une valeur de correction de la mesure de la pression du capteur, notamment des cartographies, ou un modèle analytique.Preferably, the correction means comprise means capable of delivering a correction value of the measurement of the pressure of the sensor, in particular mappings, or an analytical model.
La caractérisation des moyens de correction de la dispersion de mesure de la pression mesurée par le capteur de pression est réalisée de préférence sur un banc d'organe ou banc moteur. La caractérisation des moyens de correction de la dérive de mesure de la pression mesurée par le capteur est réalisée quant à elle directement sur le moteur.The characterization of the means for correcting the dispersion of the measurement of the pressure measured by the pressure sensor is preferably carried out on a test bench or engine bench. The characterization of the correction means of the measurement drift of the pressure measured by the sensor is carried out directly on the engine.
Les moyens de détermination de la température du capteur de pression peuvent être composés d'un capteur de température placé à proximité du capteur de pression.The means for determining the temperature of the pressure sensor may consist of a temperature sensor placed near the pressure sensor.
Dans un autre mode de réalisation, les moyens de détermination de la température du capteur de pression peuvent être estimés à l' aide d'un modèle d'estimation de la température du capteur de pression.In another embodiment, the means for determining the temperature of the pressure sensor can be estimated using a model for estimating the temperature of the pressure sensor.
Selon un autre aspect, il est proposé dans un mode de mise en oeuvre un procédé de correction de la mesure d'un capteur de pression, plus particulièrement d'un capteur de pression avant turbine.According to another aspect, it is proposed in one embodiment a method for correcting the measurement of a pressure sensor, more particularly a pressure sensor before turbine.
On détermine avantageusement la température du capteur de pression, on calcule une valeur de correction de la dispersion de mesure de la pression en fonction de la température, et on corrige la pression mesurée à partir de la valeur de correction de la dispersion de mesure de la pression pour obtenir la valeur de la pression corrigée de la dispersion.The temperature of the pressure sensor is advantageously determined, a correction value of the measurement dispersion of the pressure as a function of the temperature is calculated, and the measured pressure is corrected from the correction value of the measurement dispersion of the pressure sensor. pressure to obtain the value of the corrected pressure of the dispersion.
On calcule préférentiellement une valeur de correction de la dérive de mesure de la pression, et on corrige la pression mesurée à partir de la valeur de correction de la dérive de mesure de la pression pour obtenir la valeur de la pression corrigée de la dérive.A correction value of the drift of measurement of the pressure is preferably calculated, and the pressure measured at from the correction value of the pressure drift drift to obtain the corrected drift pressure value.
On peut construire un vecteur de correction de la dispersion de mesure de la pression du capteur quantifiant l' erreur sur la mesure du capteur de pression en fonction de la température composant.It is possible to construct a correction vector for measuring the dispersion of the pressure of the sensor, quantifying the error on the measurement of the pressure sensor as a function of the component temperature.
De préférence, on détermine un coefficient de correction de la dérive de mesure de la pression du capteur quantifiant l'erreur de mesure existant entre la pression mesurée et une pression de référence, ledit coefficient étant indépendant de la température. On corrige avantageusement la valeur de pression à partir de la valeur de la pression corrigée de la dispersion et de la valeur de correction de la dérive de mesure de la pression, la correction de la dérive de mesure de la pression étant calculée à partir d'un coefficient de correction de la dérive de mesure de la pression du capteur quantifiant l' erreur entre la pression corrigée de la dispersion et la pression de référence.Preferably, a coefficient of correction of the measurement pressure drift of the sensor is determined, quantifying the measurement error existing between the measured pressure and a reference pressure, said coefficient being independent of the temperature. The pressure value is advantageously corrected from the value of the corrected pressure of the dispersion and from the correction value of the pressure measurement drift, the correction of the pressure measurement drift being calculated from a coefficient of correction of the sensor pressure drift quantifying the error between the dispersion corrected pressure and the reference pressure.
On construit préférentiellement une matrice de correction de la dispersion de mesure de la pression du capteur quantifiant l 'erreur sur la mesure du capteur de pression en fonction de la température composant et de la pression mesurée.A correction matrix for the sensor pressure measuring dispersion is preferably constructed, quantifying the error on the pressure sensor measurement as a function of the component temperature and the measured pressure.
On détermine de préférence un vecteur de correction de la dérive de mesure de la pression du capteur quantifiant l'erreur de mesure existant entre la pression corrigée de la dispersion et la pression de référence en fonction de la température du capteur de pression.A correction vector of the measurement pressure drift of the sensor is preferably determined, quantifying the measurement error existing between the dispersion-corrected pressure and the reference pressure as a function of the temperature of the pressure sensor.
D ' autres avantages et caractéristiques de l'invention apparaîtront à l' examen de la description détaillée d'un mode de réalisation de l'invention nullement limitatif, et des dessins annexés, sur lesquels : - la figure 1 décrit schématiquement l' architecture d'un moteur comprenant un capteur de pression avant turbine ; la figure 2 illustre un exemple d' architecture de commande de la correction de la dispersion de mesure du capteur de pression avant turbine ; la figure 3 illustre un exemple d'architecture de commande de la correction de la dispersion de mesure du capteur de pression avant turbine ; la figure 4 illustre un exemple d'architecture de commande de la détermination du coefficient de correction de la dérive de mesure du capteur de pression avant turbine ; la figure 5 illustre un exemple d'architecture de commande de la détermination de la pression corrigée de la dispersion et de la dérive de mesure du capteur de pression avant turbine.Other advantages and characteristics of the invention will appear on examining the detailed description of an embodiment of the invention which is in no way limitative, and the attached drawings, in which: FIG. 1 schematically describes the architecture of FIG. an engine comprising a pressure sensor before turbine; FIG. 2 illustrates an exemplary control architecture of the measurement dispersion correction of the front turbine pressure sensor; FIG. 3 illustrates an exemplary control architecture of the measurement dispersion correction of the front turbine pressure sensor; FIG. 4 illustrates an exemplary control architecture for determining the correction coefficient of the measurement drift of the front turbine pressure sensor; FIG. 5 illustrates an exemplary control architecture of the determination of the dispersion-corrected pressure and the measurement drift of the turbine-front pressure sensor.
Sur la figure 1 , on a représenté, de manière très schématique, la structure générale d'un moteur à combustion interne 1 de type diesel suralimenté par un turbocompresseur 2 comportant une unité de commande électronique ou calculateur 3 permettant de commander le moteur à combustion interne 1 et l' ensemble de ses capteurs et actionneurs à l'aide de l'ensemble des lois de commande contenus sous formes logicielles et des paramètres de caractérisation permettant la calibration des différents éléments.FIG. 1 very schematically shows the general structure of a diesel-type internal combustion engine 1 supercharged by a turbocharger 2 comprising an electronic control unit or computer 3 making it possible to control the internal combustion engine 1 and all of its sensors and actuators using all the control laws contained in software forms and characterization parameters for calibrating the various elements.
Le turbocompresseur 2 est composé d'un compresseur 4 et d'une turbine 5 dont le rôle est d' augmenter la quantité d' air admise dans les cylindres 6 du moteur à combustion interne 1. La turbine 5 , placée à la sortie du collecteur d'échappement 7, est entraînée par les gaz d' échappement générant ainsi un mouvement de rotation au compresseur 4 monté sur le même axe 8 que la turbine 5 et placé à l' entrée du collecteur d' admission 9, comprimant ainsi l' air frais issu de la ligne d'admission d'air basse pression 10 comprenant un filtre à air 1 1 et un débitmètre massique 12 d' air frais, et entrant dans la ligne d'admission d'air haute pression 13 qui peut comprendre en outre un échangeur 14 permettant de refroidir l' air de suralimentation et un volet 15 d' air d' admission. La puissance fournie par les gaz d' échappement à la turbine 5 peut être modulée en installant une soupape de décharge ou des ailettes commandées par l'unité de commande électronique 3 , dans le cas d'une turbine à géométrie variable. Les pressions d' admission et d' échappement, dont les consignes sont calculées par l'unité de commande électronique 3 , sont mesurées par deux capteurs de pression 15 et 16 respectivement placés sur le collecteur d'admission 9 et sur le collecteur d' échappement 7.The turbocharger 2 is composed of a compressor 4 and a turbine 5 whose role is to increase the amount of air admitted into the cylinders 6 of the internal combustion engine 1. The turbine 5, placed at the outlet of the collector 7, is driven by the exhaust gas thus generating a rotational movement to the compressor 4 mounted on the same axis 8 as the turbine 5 and placed at the inlet of the intake manifold 9, thus compressing the air charge from the low pressure air intake line 10 comprising an air filter 1 1 and a mass flowmeter 12 of fresh air, and entering the high pressure air intake line 13 which may furthermore comprise an exchanger 14 for cooling the charge air and a flap 15 of intake air. The power provided by the exhaust gases to the turbine 5 may be modulated by installing a relief valve or fins controlled by the electronic control unit 3, in the case of a variable geometry turbine. The inlet and outlet pressures, whose setpoints are calculated by the electronic control unit 3, are measured by two pressure sensors 15 and 16 respectively placed on the intake manifold 9 and on the exhaust manifold 7.
Un circuit 17 haute pression de re-circulation des gaz d' échappement peut être monté entre le collecteur d'admission 9 et le collecteur d' échappement 7. Ce circuit 17 peut comprendre un échangeur 18 permettant de refroidir les gaz d' échappement recirculant vers l'admission, et une vanne 19 de by-pass du circuit 17.A high pressure exhaust gas recirculation circuit 17 may be mounted between the intake manifold 9 and the exhaust manifold 7. This circuit 17 may comprise an exchanger 18 for cooling the exhaust gas recirculating towards the exhaust manifold. admission, and a bypass valve 19 of the circuit 17.
Cinq autres capteurs de pression 20, 21 , 22, 23 et 24 permettent de mesurer les pressions à différentes étapes de la circulation des gaz. Le capteur 20 mesure la pression ambiante de l' air à l' entrée du compresseur 4, les capteurs 21 et 22, mesurent la pression de suralimentation respectivement avant et après le volet d' air d'admission 15. Le capteur 23 mesure la pression avant turbine, et le capteur 24 mesure la pression des gaz d' échappement après la turbine 5 s 'échappant dans la ligne d' échappement 25.Five other pressure sensors 20, 21, 22, 23 and 24 make it possible to measure the pressures at different stages of the gas flow. The sensor 20 measures the ambient pressure of the air at the inlet of the compressor 4, the sensors 21 and 22 measure the boost pressure respectively before and after the intake air flap 15. The sensor 23 measures the pressure before turbine, and the sensor 24 measures the pressure of the exhaust gas after the turbine 5 escaping in the exhaust line 25.
Toute l'information de pression relative, absolue ou différentielle, de l' air d'admission ou des gaz d' échappement est susceptible d'être mesurée par un capteur de pression dont les signaux bruts sont traités par l'unité de commande électronique 3 afin de les conditionner pour les stratégies de commande du moteur 1.All relative absolute or differential pressure information of the intake air or the exhaust gas may be measured by a pressure sensor whose raw signals are processed by the electronic control unit 3. in order to condition them for the control strategies of the engine 1.
Enfin, un capteur de température 26 placé à proximité du capteur 23 de pression mesure la température dudit capteur de pression 23.Finally, a temperature sensor 26 placed near the pressure sensor 23 measures the temperature of said pressure sensor 23.
Sur la figure 2 est présenté un exemple d' architecture de commande de la détermination de la valeur de la pression corrigée de la dispersion de mesure du capteur de pression avant turbine 23 à partir d'un vecteur de correction de la dispersion de mesure du capteur de pression avant turbine 23. On mesure tout d' abord la pression à l' aide du capteur de pression 23. On mesure ensuite la température du capteur de pression 23 à l' aide du capteur de température 26. On fournit alors la valeur de la température du capteur de pression 23 aux moyens de correction 30 de la dispersion de mesure de pression avant turbine.FIG. 2 shows an exemplary control architecture for determining the value of the corrected pressure of the measurement dispersion of the front turbine pressure sensor 23 from a vector for correcting the measurement dispersion of the sensor. The first pressure is measured by means of the pressure sensor 23. The temperature of the pressure sensor 23 is then measured with the aid of the temperature sensor 26. The value of the pressure sensor 23 is then measured. the temperature of the pressure sensor 23 to the correction means 30 of the pressure measurement dispersion before the turbine.
Les moyens de correction 30 calculent la valeur corrective à l' aide d'un vecteur de correction de la dispersion de mesure du capteur de pression avant turbine 23 construit lors de la caractérisation sur un banc moteur, ou un banc d'organes, de l' erreur de mesure du capteur 230.The correction means 30 calculate the corrective value using a correction vector of the measurement dispersion of the sensor. pressure sensor before turbine 23 built during the characterization on a motor bench, or a bench of organs, of the measuring error of the sensor 230.
Le vecteur de correction de la dispersion de mesure du capteur de pression 23 est construit à partir des valeurs de quantification de l' erreur de mesure du capteur de pression avant turbine 23 en fonction de sa température. L 'erreur de mesure quantifiée est exprimée en valeur absolue ou en valeur relative. Le vecteur de correction de la dispersion de mesure du capteur de pression avant turbine 23 est construit à l' aide d'une cartographie, d'un modèle analytique, ou tout autre moyen permettant de délivrer une valeur de correction de la dérive de mesure du capteur de pression avant turbine 23.The correction vector of the measurement dispersion of the pressure sensor 23 is constructed from the quantization values of the measurement error of the front turbine pressure sensor 23 as a function of its temperature. The quantified measurement error is expressed in absolute value or in relative value. The measurement dispersion correction vector of the turbine front pressure sensor 23 is constructed using a mapping, an analytical model, or any other means for delivering a correction value of the measurement drift of the front pressure sensor turbine 23.
Une valeur de correction de la dispersion de mesure de la pression est ainsi calculée à partir de la valeur de la température mesurée par le capteur de température 23 introduite dans les moyens de correction 30. On combine ensuite à l' aide d'un moyen 31 de combinaison la valeur de la pression mesurée par le capteur de pression 23 et la valeur de correction de la dispersion de mesure de la pression afin d'obtenir valeur de la pression corrigée de la dispersion. La combinaison est additive dans le cas de valeurs absolues, et multiplicative dans le cas de valeurs relatives.A correction value of the pressure measurement dispersion is thus calculated from the value of the temperature measured by the temperature sensor 23 introduced into the correction means 30. It is then combined with a means 31 combining the value of the pressure measured by the pressure sensor 23 and the correction value of the pressure measurement dispersion in order to obtain a value of the pressure corrected for the dispersion. The combination is additive in the case of absolute values, and multiplicative in the case of relative values.
Sur la figure 3 est présenté un exemple d' architecture de commande de la détermination de la valeur de la pression corrigée de la dérive de la mesure du capteur de pression avant turbine 23 à partir d'un coefficient de correction de la dispersion de mesure du capteur de pression avant turbine 23. La valeur de la pression mesurée par le capteur de pression avant turbine 23 est combinée à l'aide d'un moyen 32 de combinaison soustractive à la valeur de correction de la dérive de mesure du capteur de pression avant turbine délivrée par des moyens de correction 33 de la dérive de mesure du capteur de pression avant turbine 23. De la combinaison de ces deux valeurs, on obtient la valeur de la pression corrigée de la dérive.FIG. 3 shows an exemplary control architecture for determining the value of the corrected pressure of the drift of the measurement of the front turbine pressure sensor 23 from a correction coefficient of the measurement dispersion of the front pressure sensor turbine 23. The value of the pressure measured by the front turbine pressure sensor 23 is combined by means of a combination means 32 subtractive to the correction value of the measurement drift of the front pressure sensor turbine delivered by correction means 33 of the measuring drift of the front turbine pressure sensor 23. From the combination of these two values, the value of the corrected pressure of the drift is obtained.
Dans la combinaison précédente, on peut remplacer la pression mesurée par le capteur de pression avant turbine 23 par la valeur de la pression corrigée de la dispersion. La combinaison ainsi réalisée, permet d'obtenir la valeur de la pression corrigée correspondant à la pression corrigée de la dispersion et de la dérive de mesure du capteur de pression avant turbine 23.In the above combination, the pressure measured by the turbine front pressure sensor 23 can be replaced by the value of the pressure corrected for the dispersion. The combination thus produced, to obtain the value of the corrected pressure corresponding to the corrected pressure of the dispersion and the measurement drift of the front turbine pressure sensor 23.
Afin de déterminer la valeur du coefficient de correction de la dérive de mesure du capteur de pression avant turbine 23 , les moyens de corrections 33 de la dérive de mesure réalisent une phase de caractérisation du correctif de la dérive de mesure réalisée directement sur le moteur 1 avant la phase d' application vu précédemment avec la figure 3. Lors de cette phase de caractérisation, illustrée sur la figure 4, les moyens de corrections 33 quantifient l 'erreur de mesure existant entre la pression mesurée et une pression de référence, l' erreur de mesure étant exprimée en valeur absolue ou relative. A partir des valeurs obtenues on détermine un coefficient de correction de la dérive de mesure à l' aide d'une cartographie, d'un modèle analytique, ou de tout autre moyen permettant de délivrer une valeur de correction de la dérive de mesure de la pression avant turbine.In order to determine the value of the correction coefficient of the measurement drift of the front turbine pressure sensor 23, the correction means 33 of the measurement drift perform a characterization phase of the correction of the measurement drift carried out directly on the engine 1 before the application phase seen previously with FIG. 3. During this characterization phase, illustrated in FIG. 4, the correction means 33 quantify the measurement error existing between the measured pressure and a reference pressure, measuring error being expressed in absolute or relative value. From the values obtained, a correction coefficient of the measurement drift is obtained by means of a cartography, an analytical model, or any other means making it possible to deliver a correction value of the measurement drift of the measurement drift. pressure before turbine.
La pression de référence est délivrée par un capteur de pression ou estimée à partir d'un modèle physique. En général, on utilise un capteur de pression atmosphérique 20 pour délivrer la pression de référence en raison de sa faible dispersion de mesure. D ' autres capteurs de pression peuvent également servir de référence dans le cas où leur dispersion de mesure est plus faible que celle du capteur de pression avant turbine 23. La valeur du coefficient de correction de la dérive de mesure déterminée lors de la phase de caractérisation est mémorisée dans des moyens de mémorisation 34 de données tels qu'une mémoire EEPROM.The reference pressure is delivered by a pressure sensor or estimated from a physical model. In general, an atmospheric pressure sensor 20 is used to deliver the reference pressure because of its low measurement dispersion. Other pressure sensors may also serve as a reference if their measurement dispersion is smaller than that of the front turbine pressure sensor 23. The value of the correction coefficient of the measurement drift determined during the characterization phase is stored in data storage means 34 such as an EEPROM memory.
Sur la figure 5 , la phase de caractérisation du correctif de la dérive de mesure permet de déterminer le vecteur de correction de la dérive de mesure du capteur de pression avant turbine 23. Pour déterminer le vecteur de correction de la dérive de mesure, on quantifie l'erreur de mesure entre la pression corrigée de la dispersion de mesure et une pression de référence en fonction de la température du capteur de pression 23 mesurée à l' aide du capteur de température 26 ou estimée à l' aide d'un modèle estimateur de température du capteur de pression 23. Le vecteur de correction de la dérive de mesure du capteur de pression est mémorisée dans des moyens de mémorisation de données 34 tels qu'une mémoire EEPROM. Pour déterminer la valeur de la pression corrigée de la dispersion et de la dérive de mesure du capteur de pression avant turbine, on mesure tout d'abord la pression à l'aide du capteur de pression 23 et on introduit la valeur dans les moyens de corrections 30 de la dispersion de mesure avec la valeur de la température du capteur de pression 23 mesurée à l'aide du capteur de température 26.In FIG. 5, the characterization phase of the correction of the measurement drift makes it possible to determine the correction vector of the measurement drift of the front turbine pressure sensor 23. In order to determine the correction vector of the measurement drift, it is quantified. the measurement error between the corrected pressure of the measurement dispersion and a reference pressure as a function of the temperature of the pressure sensor 23 measured with the aid of the temperature sensor 26 or estimated using a temperature model of the pressure sensor 23. The correction vector of the measurement drift of the pressure sensor is stored in data storage means 34 such as an EEPROM memory. In order to determine the value of the corrected pressure of the dispersion and of the measurement drift of the pressure sensor before the turbine, the pressure is first measured with the aid of the pressure sensor 23 and the value is introduced into the measuring means. corrections of the measurement dispersion with the value of the temperature of the pressure sensor 23 measured with the aid of the temperature sensor 26.
Les moyens de correction 30 calculent cette fois la valeur corrective à l' aide d'une matrice de correction de la dispersion de mesure du capteur de pression avant turbine 23 construite lors de la caractérisation sur un banc moteur, ou un banc d'organes, de l' erreur de mesure du capteur de pression avant turbine 23. La matrice est construite à partir des valeurs de quantification de l' erreur de mesure du capteur de pression avant turbine 23 en fonction de la pression mesurée et de sa température. L ' erreur de mesure quantifiée est exprimée en valeur absolue ou en valeur relative. La matrice de correction de la dispersion de mesure du capteur de pression avant turbine 23 est construite à l'aide d'une cartographie, d'un modèle analytique, ou tout autre moyen permettant de délivrer une valeur de correction de la dérive de mesure du capteur de pression avant turbine 23. Une valeur de correction de la dispersion de mesure de la pression est ainsi calculée à partir de la valeur de la température mesurée par le capteur de température 26 introduite dans les moyens de correction 30. On combine ensuite la valeur de la pression mesurée par le capteur de pression 23 et la valeur de correction de la dispersion de mesure de la pression afin d'obtenir la valeur de la pression corrigée de la dispersion. La combinaison est additive dans le cas de valeurs absolues, et multiplicative dans le cas de valeurs relatives.The corrective means 30 calculate this time the corrective value using a measurement dispersion correction matrix of the front turbine pressure sensor 23 constructed during the characterization on a driving bench, or a bench of organs, of the measurement error of the front turbine pressure sensor 23. The matrix is constructed from the quantization values of the measurement error of the front turbine pressure sensor 23 as a function of the measured pressure and its temperature. The quantified measurement error is expressed in absolute value or in relative value. The measurement dispersion correction matrix of the front turbine pressure sensor 23 is constructed using a mapping, an analytical model, or any other means for delivering a correction value of the measurement drift of the front pressure sensor turbine 23. A correction value of the pressure measurement dispersion is thus calculated from the value of the temperature measured by the temperature sensor 26 introduced into the correction means 30. The value is then combined. the pressure measured by the pressure sensor 23 and the correction value of the pressure measurement dispersion in order to obtain the value of the pressure corrected for the dispersion. The combination is additive in the case of absolute values, and multiplicative in the case of relative values.
La valeur de la température du capteur de pression avant turbine 23 mesurée à l'aide du capteur de température 26 est introduite dans les moyens de correction 33 de la dérive de mesure du capteur de pression avant turbine 23. A partir du vecteur de correction de la dérive de mesure du capteur de pression avant turbine 23 et de la valeur de la température mesurée, on détermine la valeur de la correction de la dérive de mesure du capteur de pression avant turbine 23 grâce aux moyens de correction 33. La valeur de la correction de la dérive de mesure du capteur de pression avant turbine 23 est combinée à la valeur de la pression corrigée de la dispersion de mesure du capteur de pression avant turbine 23 afin d'obtenir la valeur de la pression corrigée qui est ainsi corrigée de la dispersion et de la dérive de mesure du capteur de pression avant turbine 23.The value of the temperature of the front turbine pressure sensor 23 measured with the aid of the temperature sensor 26 is introduced into the correction means 33 of the measurement drift of the sensor. pressure before turbine 23. From the correction vector of the measurement drift of the front turbine pressure sensor 23 and the value of the measured temperature, the value of the correction of the measurement drift of the front turbine pressure sensor is determined. 23 by the correction means 33. The value of the correction of the measurement drift of the turbine front pressure sensor 23 is combined with the value of the corrected pressure of the measurement dispersion of the front turbine pressure sensor 23 in order to obtain the value of the corrected pressure which is thus corrected for the dispersion and the measurement drift of the front turbine pressure sensor 23.
Ces types de procédé de commande sont applicables à l' ensemble des capteurs de pression du type relatif, absolu, ou différentiel, placé sur un circuit d' admission ou d' échappement du moteur et dont les caractéristiques regroupent une dérive de mesure sensible à l' écrasement et au vieillissement du capteur relativement continue en fonction du temps et ne dépassant pas des bornes acceptables d' erreur, et une dispersion de mesure issue de la fabrication du capteur, sensible à la pression mesurée et à la température ambiante. These types of control method are applicable to all pressure sensors of the relative, absolute or differential type, placed on an engine intake or exhaust circuit and whose characteristics include a measurement drift sensitive to the engine. crushing and aging of the sensor relatively continuous as a function of time and not exceeding acceptable error limits, and a measurement dispersion resulting from the manufacture of the sensor, sensitive to the measured pressure and the ambient temperature.

Claims

REVENDICATIONS
1. Système de correction de la mesure d'un capteur de pression avant turbine (23), caractérisé par le fait qu'il comprend des moyens (26) de détermination de la température du capteur de pression, des moyens de mémorisation (34) de données caractérisant la dispersion et/ou la dérive de mesure du capteur en fonction de la température, des moyens de correction (40) aptes à déterminer un terme correctif à appliquer aux valeurs mesurées par le capteur en fonction des données mémorisées, lesdits moyens de correction (40) comprenant des moyens de correction (30) de la dispersion de mesure de la pression mesurée par le capteur et des moyens de correction (33) de la dérive de mesure de la pression mesurée par le capteur.1. System for correcting the measurement of a pressure sensor before turbine (23), characterized in that it comprises means (26) for determining the temperature of the pressure sensor, storage means (34) of data characterizing the dispersion and / or the measurement drift of the sensor as a function of temperature, correction means (40) able to determine a correction term to be applied to the values measured by the sensor as a function of the data stored, said means of correction (40) comprising correction means (30) for measuring the dispersion of the pressure measured by the sensor and means (33) for correcting the drift for measuring the pressure measured by the sensor.
2. Système selon la revendication 1 , dans lequel les moyens de correction (40) comprennent des moyens aptes à délivrer une valeur de correction de la mesure de la pression du capteur, notamment des cartographies, ou un modèle analytique.2. System according to claim 1, wherein the correction means (40) comprise means capable of delivering a correction value of the measurement of the pressure of the sensor, in particular mappings, or an analytical model.
3. Système selon l'une des revendication 1 ou 2, dans lequel la caractérisation des moyens de correction (30) de la dispersion de mesure de la pression mesurée par le capteur de pression est réalisée sur un banc d'organe ou banc moteur.3. System according to one of claims 1 or 2, wherein the characterization of the correction means (30) of the measuring dispersion of the pressure measured by the pressure sensor is performed on a test bench or engine bench.
4. Système selon l'une quelconque des revendications 1 à 3 , dans lequel la caractérisation des moyens de correction (33) de la dérive de mesure de la pression mesurée par le capteur est réalisée directement sur le moteur. 4. System according to any one of claims 1 to 3, wherein the characterization of the correction means (33) of the drift measuring the pressure measured by the sensor is performed directly on the engine.
5. Système selon l'une des revendications 1 à 4, dans lequel les moyens (26) de détermination de la température du capteur de pression comprennent un capteur de température placé à proximité du capteur de pression. 5. System according to one of claims 1 to 4, wherein the means (26) for determining the temperature of the pressure sensor comprises a temperature sensor placed near the pressure sensor.
6. Système selon l'une des revendications 1 à 5 , dans lequel les moyens (26) de détermination de la température du capteur de pression comprennent un modèle d'estimation de la température du capteur de pression. 6. System according to one of claims 1 to 5, wherein the means (26) for determining the temperature of the pressure sensor comprises a model for estimating the temperature of the pressure sensor.
7. Procédé de correction de la mesure d'un capteur de pression avant turbine (23), caractérisé en ce que l'on détermine la température du capteur de pression, on calcule une valeur de correction de la dispersion de mesure de la pression en fonction de la température, et l'on corrige la pression mesurée à partir de la valeur de correction de la dispersion de mesure de la pression.7. A method for correcting the measurement of a front turbine pressure sensor (23), characterized in that the temperature of the pressure sensor is determined, a correction value of the pressure measurement dispersion is calculated. depending on the temperature, and the measured pressure is corrected from the correction value of the pressure measurement dispersion.
8. Procédé selon la revendication 7, dans lequel on calcule une valeur de correction de la dérive de mesure de la pression, et l'on corrige la pression mesurée à partir de la valeur de correction de la dérive de mesure de la pression. The method of claim 7, wherein a correction value of the pressure measurement drift is calculated, and the measured pressure is corrected from the correction value of the pressure measurement drift.
9. Procédé selon l'une des revendications 7 ou 8, dans lequel on construit un vecteur de correction de la dispersion de mesure de la pression du capteur quantifiant l'erreur sur la mesure du capteur de pression en fonction de la température composant.9. Method according to one of claims 7 or 8, wherein a vector is constructed to correct the dispersion of measurement of the pressure of the sensor quantifying the error on the measurement of the pressure sensor as a function of the component temperature.
10. Procédé selon l'une des revendications 7 à 9, dans lequel on détermine un coefficient de correction de la dérive de mesure de la pression du capteur quantifiant l' erreur de mesure existant entre la pression mesurée et une pression de référence, ledit coefficient étant indépendant de la température.10. Method according to one of claims 7 to 9, wherein determining a correction coefficient of the drift measuring the sensor pressure quantifying the measurement error between the measured pressure and a reference pressure, said coefficient being independent of the temperature.
1 1. Procédé selon l'une des revendications 7 à 10, dans lequel on corrige la valeur de pression à partir de la valeur de la pression corrigée de la dispersion et de la valeur de correction de la dérive de mesure de la pression, la correction de la dérive de mesure de la pression étant calculée à partir d'un coefficient de correction de la dérive de mesure de la pression du capteur quantifiant l'erreur entre la pression corrigée de la dispersion et la pression de référence. The method according to one of claims 7 to 10, wherein the pressure value is corrected from the value of the pressure corrected for the dispersion and the correction value of the pressure measurement drift. correction of the pressure measurement drift being calculated from a correction coefficient of the sensor pressure drift, quantifying the error between the dispersion-corrected pressure and the reference pressure.
12. Procédé selon l'une des revendications 7 à 1 1 , dans lequel on construit une matrice de correction de la dispersion de mesure de la pression du capteur quantifiant l'erreur sur la mesure du capteur de pression en fonction de la température composant et de la pression mesurée.12. Method according to one of claims 7 to 11, wherein a correction matrix is constructed for measuring the dispersion of the pressure of the sensor quantifying the error on the measurement of the pressure sensor as a function of the component temperature and the measured pressure.
13. Procédé selon l'une des revendications 7 à 12, dans lequel on détermine un vecteur de correction de la dérive de mesure de la pression du capteur quantifiant l' erreur de mesure existant entre la pression corrigée de la dispersion et la pression de référence en fonction de la température du capteur de pression. 13. Method according to one of claims 7 to 12, wherein determining a correction vector of the drift measuring the sensor pressure quantifying the measurement error existing between the pressure corrected dispersion and the reference pressure. depending on the temperature of the pressure sensor.
EP09794016A 2008-06-30 2009-06-15 System and method for correcting the measurement of a pre-turbine pressure sensor Withdrawn EP2307868A1 (en)

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FR0854390A FR2933137B1 (en) 2008-06-30 2008-06-30 SYSTEM AND METHOD FOR CORRECTING THE MEASUREMENT OF A TURBINE FRONT PRESSURE SENSOR
PCT/FR2009/051125 WO2010004152A1 (en) 2008-06-30 2009-06-15 System and method for correcting the measurement of a pre-turbine pressure sensor

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