FR3063109A1 - METHOD FOR DETERMINING EXHAUST PRESSURE BEFORE THE TURBINE OF A TURBOCHARGER EQUIPPED WITH A THERMAL ENGINE - Google Patents
METHOD FOR DETERMINING EXHAUST PRESSURE BEFORE THE TURBINE OF A TURBOCHARGER EQUIPPED WITH A THERMAL ENGINE Download PDFInfo
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- FR3063109A1 FR3063109A1 FR1751273A FR1751273A FR3063109A1 FR 3063109 A1 FR3063109 A1 FR 3063109A1 FR 1751273 A FR1751273 A FR 1751273A FR 1751273 A FR1751273 A FR 1751273A FR 3063109 A1 FR3063109 A1 FR 3063109A1
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- 238000000034 method Methods 0.000 title claims abstract description 21
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- 239000003054 catalyst Substances 0.000 description 1
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Classifications
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- 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
- F02D41/145—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 with determination means using an estimation
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- 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
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
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- 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
- F02D23/02—Controlling engines characterised by their being supercharged the engines being of fuel-injection type
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- 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
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- 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
- 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
- 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
- F02D41/1445—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 related to the exhaust flow
-
- 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
- F02D41/24—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
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- 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
Abstract
L'invention concerne un procédé de détermination de la pression (P3) des gaz d'échappement entrant dans une turbine (12) d'un turbocompresseur de moteur thermique, dans lequel on détermine pour la turbine une grandeur caractéristique de son ouverture, la température (T3) du gaz entrant, la pression (P4) du gaz sortant, le débit de gaz la traversant, caractérisé en ce qu'on lit dans une cartographie une valeur de son rendement isentropique associée au couple de valeur formé par le débit de gaz et la grandeur caractéristique de son ouverture, -on détermine la température (T4) du gaz sortant de la turbine (12), -on détermine la température isentropique du gaz sortant de la turbine, puis la pression (P3) des gaz d'échappement entrant dans la turbine (12) à partir de la pression (P4) du gaz sortant de la turbine (12), de la température isentropique et d'un modèle de détente isentropique de la turbine (12).The invention relates to a method for determining the pressure (P3) of the exhaust gases entering a turbine (12) of a thermal engine turbocharger, in which a characteristic quantity of its opening, the temperature, is determined for the turbine. (T3) of the incoming gas, the pressure (P4) of the outgoing gas, the gas flow therethrough, characterized in that a map is read of a value of its isentropic efficiency associated with the value pair formed by the gas flow rate. and the characteristic quantity of its opening, the temperature (T4) of the gas leaving the turbine (12) being determined, the isentropic temperature of the gas leaving the turbine and then the pressure (P3) of the exhaust gases being determined. entering the turbine (12) from the pressure (P4) of the gas leaving the turbine (12), the isentropic temperature and an isentropic expansion model of the turbine (12).
Description
Titulaire(s) : PEUGEOT CITROEN AUTOMOBILES SA Société anonyme.Holder (s): PEUGEOT CITROEN AUTOMOBILES SA Société anonyme.
Demande(s) d’extensionExtension request (s)
Mandataire(s) : PEUGEOT CITROEN AUTOMOBILES SA Société anonyme.Agent (s): PEUGEOT CITROEN AUTOMOBILES SA Public limited company.
PROCEDE DE DETERMINATION DE LA PRESSION DES GAZ D'ECHAPPEMENT EN AMONT DE LA TURBINE D'UN TURBOCOMPRESSEUR EQUIPANT UN MOTEUR THERMIQUE.METHOD FOR DETERMINING THE PRESSURE OF EXHAUST GASES UPSTREAM OF THE TURBINE OF A TURBOCHARGER EQUIPPED WITH A THERMAL ENGINE.
FR 3 063 109 - A1 (5/) L'invention concerne un procédé de détermination de la pression (P3) des gaz d'échappement entrant dans une turbine (12) d'un turbocompresseur de moteur thermique, dans lequel on détermine pour la turbine une grandeur caractéristique de son ouverture, la température (T3) du gaz entrant, la pression (P4) du gaz sortant, le débit de gaz la traversant, caractérisé en ce qu'on lit dans une cartographie une valeur de son rendement isentropique associée au couple de valeur formé par le débit de gaz et la grandeur caractéristique de son ouverture,FR 3 063 109 - A1 (5 /) The invention relates to a method for determining the pressure (P3) of the exhaust gases entering a turbine (12) of a turbocharger of an engine, in which it is determined for the turbine a characteristic quantity of its opening, the temperature (T3) of the entering gas, the pressure (P4) of the leaving gas, the flow of gas passing through it, characterized in that a value of its associated isentropic efficiency is read in a map the value couple formed by the gas flow and the characteristic magnitude of its opening,
-on détermine la température (T4) du gaz sortant de la turbine (12),the temperature (T4) of the gas leaving the turbine (12) is determined,
-on détermine la température isentropique du gaz sortant de la turbine, puis la pression (P3) des gaz d'échappement entrant dans la turbine (12) à partir de la pression (P4) du gaz sortant de la turbine (12), de la température isentropique et d'un modèle de détente isentropique de la turbine (12).-the isentropic temperature of the gas leaving the turbine is determined, then the pressure (P3) of the exhaust gases entering the turbine (12) from the pressure (P4) of the gas leaving the turbine (12), the isentropic temperature and an isentropic expansion model of the turbine (12).
PROCEDE DE DETERMINATION DE LA PRESSION DES GAZ D’ECHAPPEMENT EN AMONT DE LA TURBINE D’UN TURBOCOMPRESSEUR EQUIPANT UN MOTEUR THERMIQUEMETHOD FOR DETERMINING THE PRESSURE OF EXHAUST GASES UPSTREAM OF THE TURBINE OF A TURBOCHARGER COMPRISING A HEAT ENGINE
La présente invention se rapporte se rapporte au domaine des moteurs à combustion interne suralimentés. L’invention concerne plus particulièrement un procédé de détermination de la pression des gaz d’échappement en amont de la turbine d’un turbocompresseur.The present invention relates to the field of supercharged internal combustion engines. The invention relates more particularly to a method for determining the pressure of the exhaust gases upstream of the turbine of a turbocharger.
Les contraintes dues aux normes, par exemple les normes européennes dites Euro VI, relatives aux niveaux d’émissions polluantes générées par le fonctionnement des moteurs à combustion interne, deviennent de plus en plus en plus sévères.The constraints due to standards, for example European standards known as Euro VI, relating to the levels of polluting emissions generated by the operation of internal combustion engines, are becoming more and more severe.
Les niveaux de performance requis pour les fonctions de contrôle moteur étant par conséquent de plus en plus exigeant, il est intéressant de bien connaître l’état du système à contrôler. Cette connaissance passe actuellement par l’implantation de capteur complétée par une modélisation des phénomènes physiques présents. Une grandeur spécifique du système peut alors être estimée via la mesure du capteur et par le résultat de la modélisation.As the performance levels required for engine control functions are therefore increasingly demanding, it is interesting to know the state of the system to be controlled. This knowledge currently involves the implantation of a sensor supplemented by a modeling of the physical phenomena present. A specific quantity of the system can then be estimated via the measurement of the sensor and by the result of the modeling.
Une grandeur caractéristique du système peut alors être estimée via la mesure d’un capteur et par le résultat d’un modèle. Ces deux sources d’information présentent des qualités et compromis différents : fiabilité, dynamique, coût...A characteristic quantity of the system can then be estimated via the measurement of a sensor and by the result of a model. These two sources of information have different qualities and compromises: reliability, dynamics, cost ...
En particulier dans le cas d’un moteur à combustion interne équipé d’un système de suralimentation tel qu’un turbocompresseur et/ ou d’un système de recirculation des gaz d’échappement vers l’admission, encore désigné EGR, l’estimation de la pression de collecteur échappement est un des estimateurs nécessaires au contrôle moteur pour respecter les critères de contraintes thermomécanique du collecteur et de la turbine mais également pour la maîtrise de la pression de suralimentation et de la quantité de gaz recirculés.In particular in the case of an internal combustion engine equipped with a supercharging system such as a turbocharger and / or a system for recirculating the exhaust gases to the intake, also designated EGR, the estimate of the exhaust manifold pressure is one of the estimators necessary for engine control in order to meet the criteria of thermomechanical constraints of the manifold and the turbine, but also for controlling the boost pressure and the quantity of recirculated gases.
On connaît le document FR2921114 qui décrit une méthode de détermination, dans un moteur thermique suralimenté, d'une pression en entrée de turbine basé sur un champ turbine.Document FR2921114 is known, which describes a method for determining, in a turbocharged engine, a pressure at the turbine inlet based on a turbine field.
Il existe donc un besoin pour améliorer la précision de la détermination de la pression instantanée des gaz échappement en amont de la turbine, lorsque le moteur ne comprend pas de capteur de pression collecteur.There is therefore a need to improve the accuracy of determining the instantaneous pressure of the exhaust gases upstream of the turbine, when the engine does not include a manifold pressure sensor.
Pour atteindre cet objectif, il est prévu selon l’invention un procédé de détermination de la pression des gaz d’échappement entrant dans une turbine d’un turbocompresseur équipant un moteur thermique, dans lequel :To achieve this objective, there is provided according to the invention a method for determining the pressure of the exhaust gases entering a turbine of a turbocharger fitted to a heat engine, in which:
-on détermine une grandeur caractéristique de l’ouverture de la turbine, la température du gaz entrant dans la turbine, la pression du gaz sortant de la turbine,-a characteristic size of the turbine opening is determined, the temperature of the gas entering the turbine, the pressure of the gas leaving the turbine,
-on détermine le débit de gaz traversant la turbine, caractérisé en ce qu’on lit dans une cartographie une valeur du rendement isentropique de la turbine associée au couple de valeur formé par le débit de gaz et la grandeur caractéristique de l’ouverture de la turbine,-the gas flow through the turbine is determined, characterized in that a value of the isentropic efficiency of the turbine associated with the torque formed by the gas flow and the characteristic quantity of the opening of the turbine is read in a map. turbine,
-on détermine la température du gaz sortant de la turbine,-the temperature of the gas leaving the turbine is determined,
-on détermine à partir de cette température du gaz sortant de la turbine et du rendement isentropique la température isentropique du gaz sortant de la turbine, puis on détermine la pression des gaz d’échappement entrant dans la turbine à partir de la pression du gaz sortant de la turbine, de la température isentropique et d’un modèle de détente isentropique de la turbine.-the isentropic temperature of the gas leaving the turbine is determined from this temperature of the gas leaving the turbine and the isentropic efficiency, then the pressure of the exhaust gases entering the turbine is determined from the pressure of the gas leaving of the turbine, the isentropic temperature and an isentropic expansion model of the turbine.
L’effet technique est d’améliorer la détermination de la pression des gaz d’échappement en amont de la turbine en utilisant uniquement des informations de la turbine.The technical effect is to improve the determination of the exhaust gas pressure upstream of the turbine by using only information from the turbine.
Diverses caractéristiques supplémentaires peuvent être prévues, seules ou en combinaisons :Various additional characteristics can be provided, alone or in combination:
En variante, la pression en sortie de turbine est déterminée par un estimateur de pression.As a variant, the pressure at the outlet of the turbine is determined by a pressure estimator.
En variante, la température du gaz entrant dans la turbine est déterminée par un estimateur de température.Alternatively, the temperature of the gas entering the turbine is determined by a temperature estimator.
En variante, la température du gaz sortant de la turbine est déterminée par un capteur de température.As a variant, the temperature of the gas leaving the turbine is determined by a temperature sensor.
Dans une variante où le turbocompresseur est du type à géométrie variable à ailettes mobiles, la grandeur caractéristique de l’ouverture de la turbine est une valeur représentative de la position des ailettes.In a variant where the turbocharger is of the variable geometry type with movable fins, the characteristic size of the turbine opening is a value representative of the position of the fins.
Dans une variante où le turbocompresseur est du type à géométrie fixe avec un circuit de dérivation des gaz de la turbine, la grandeur caractéristique de l’ouverture de la turbine est une valeur représentative de l’ouverture de cette branche de dérivation.In a variant where the turbocharger is of the fixed geometry type with a gas bypass circuit from the turbine, the characteristic size of the turbine opening is a value representative of the opening of this branch branch.
L’invention à également pour objet un calculateur, caractérisé en ce qu’il comprend les moyens d’acquisition, de traitement par instructions logicielles stockées dans une mémoire ainsi que les moyens de commande requis à mise en œuvre d’un procédé selon l’une quelconque des variantes précédemment décrites.The invention also relates to a computer, characterized in that it comprises the means of acquisition, of processing by software instructions stored in a memory as well as the control means required for implementing a method according to the any of the previously described variants.
L’invention à également pour objet un moteur comprenant un turbocompresseur, caractérisé en ce qu’il comprend un tel calculateur.The invention also relates to an engine comprising a turbocharger, characterized in that it comprises such a computer.
L’invention à également pour objet un véhicule, caractérisé en ce qu’il comprend un tel moteur thermique.The invention also relates to a vehicle, characterized in that it comprises such a heat engine.
D’autres particularités et avantages apparaîtront à la lecture de la description ci-après d’un mode particulier de réalisation, non limitatif de l’invention, faite en référence aux figures dans lesquelles :Other particularities and advantages will appear on reading the description below of a particular embodiment, without limitation of the invention, made with reference to the figures in which:
- La figure 1 est une représentation schématique d’un moteur thermique de l’invention.- Figure 1 is a schematic representation of a heat engine of the invention.
- La figure 2 est un logigramme schématisant les étapes du procédé de l’invention.- Figure 2 is a flow diagram diagramming the steps of the method of the invention.
La figure 1 présente un moteur thermique, par exemple un moteur à combustion interne à allumage commandé ou à allumage par compression, comprenant un bloc moteur 1 avec au moins un cylindre 2, par exemple ici quatre cylindres, pour la combustion. Un tel moteur thermique peut équiper un véhicule, par exemple un véhicule automobile pour permettre un déplacement de celui-ci.FIG. 1 shows a heat engine, for example an internal combustion engine with positive ignition or with compression ignition, comprising an engine block 1 with at least one cylinder 2, for example here four cylinders, for combustion. Such a heat engine can be fitted to a vehicle, for example a motor vehicle to allow movement thereof.
Le moteur thermique comporte en outre un calculateur, non représenté, comprenant les moyens d’acquisition, de traitement par instructions logicielles stockées dans une mémoire ainsi que les moyens de commande requis à mise en oeuvre du procédé détaillé après.The heat engine also comprises a computer, not shown, comprising the means of acquisition, of processing by software instructions stored in a memory as well as the control means required for implementing the method detailed below.
Le moteur thermique est relié à une ligne 3 d’admission d’air destinée à diriger vers le moteur 1 thermique l’air nécessaire à son fonctionnement. La ligne d’admission 3 comprend classiquement et dans cet ordre selon le sens de l’écoulement de l’air dans la ligne :The heat engine is connected to an air intake line 3 intended to direct the air necessary for its operation to the heat engine 1. The intake line 3 conventionally comprises and in this order according to the direction of the air flow in the line:
- une entrée E d’air,- an air inlet E,
- un filtre 4 à air pour retenir les poussières contenues dans l’air admis,- an air filter 4 to retain the dust contained in the intake air,
- un compresseur 5 de turbocompresseur 13,a compressor 5 of turbocharger 13,
- un refroidisseur 6 d’air comprimé,- a compressed air cooler 6,
- une vanne 7 de dosage d’air pour le contrôle du débit d’air admis dans le moteur 1, pouvant être par exemple classiquement un boîtier papillon,a valve 7 for metering air for controlling the flow of air admitted into the engine 1, which can for example be conventionally a throttle body,
- un répartiteur 8 d’air vers les cylindres 2 du moteur thermique.- a distributor 8 of air to the cylinders 2 of the heat engine.
Le moteur thermique est encore relié à une ligne 9 d’échappement pour l’évacuation des gaz de combustion produits dans les cylindres 2 pendant le fonctionnement du moteur. La ligne 9 d’échappement comprend classiquement et dans cet ordre selon le sens de l’écoulement des gaz dans la ligne :The heat engine is also connected to an exhaust line 9 for the evacuation of the combustion gases produced in the cylinders 2 during the operation of the engine. The exhaust line 9 conventionally comprises and in this order according to the direction of flow of the gases in the line:
- un collecteur 10 de gaz d’échappement,- an exhaust gas collector 10,
- un capteur 11 de température en amont de la turbine 12 de turbocompresseur 13 pour la détente des gaz d’échappement et l’entrainement du compresseur 5.- a temperature sensor 11 upstream of the turbine 12 of turbocharger 13 for the expansion of the exhaust gases and the drive of the compressor 5.
- un capteur 14 de température en aval de la turbine 12,a temperature sensor 14 downstream from the turbine 12,
- un capteur 15 de pression en aval de la turbine 12,a pressure sensor 15 downstream of the turbine 12,
- au moins un organe 16 de dépollution, tel que par exemple un catalyseur d’oxydation, un filtre à particules,- at least one depollution device 16, such as for example an oxidation catalyst, a particle filter,
- une sortie S des gaz d’échappement.- an exhaust outlet S.
La turbine 12 et le compresseur 5 du turbocompresseur 13 sont reliés par un arbre 17 d’entrainement, maintenu par un palier, non représenté.The turbine 12 and the compressor 5 of the turbocharger 13 are connected by a drive shaft 17, held by a bearing, not shown.
Le moteur thermique comprend encore une ligne 18 de recirculation des gaz d’échappement reliant la ligne 9 d’échappement à la ligne 3 d’admission. La ligne 18 de recirculation des gaz d’échappement est reliée à une de ses extrémités à la ligne 9 d’échappement par un piquage situé entre le collecteur 10 d’échappement et la turbineThe heat engine also includes an exhaust gas recirculation line 18 connecting the exhaust line 9 to the intake line 3. The exhaust gas recirculation line 18 is connected at one of its ends to the exhaust line 9 by a connection located between the exhaust manifold 10 and the turbine.
12. La ligne 18 de recirculation des gaz d’échappement est reliée à l’autre de ses extrémités à la ligne 3 d’admission par un piquage situé entre le collecteur 8 d’admission et la vanne 7 de dosage d’air. Cette ligne 18 de recirculation des gaz d’échappement comprend classiquement :12. The exhaust gas recirculation line 18 is connected at the other of its ends to the intake line 3 by a connection located between the intake manifold 8 and the air metering valve 7. This exhaust gas recirculation line 18 conventionally comprises:
- une vanne 19 de dosage de la quantité de gaz d’échappement à faire recirculer,- a valve 19 for metering the quantity of exhaust gas to be recirculated,
- un échangeur 20 de refroidissement des gaz d’échappement à faire recirculer.- An exchanger 20 for cooling the exhaust gases to be recirculated.
Comme indiqué sur la figure 1, la pression et la température des gaz d’échappement en amont de la turbine 12 sont respectivement notés P3 et T3, la pression et la température des gaz d’échappement en aval de la turbine 12 étant respectivement P4 et T4. L’amont et l’aval sont déterminés par le sens de circulation des fluides, de l’air pour la ligne 3 d’admission et des gaz brûlés pour la ligne 9 d’échappement. La température T4 est mesurée par le capteur 14.As indicated in FIG. 1, the pressure and the temperature of the exhaust gases upstream of the turbine 12 are respectively denoted P3 and T3, the pressure and the temperature of the exhaust gases downstream of the turbine 12 being respectively P4 and T4. The upstream and downstream are determined by the direction of circulation of the fluids, the air for the intake line 3 and the burnt gases for the exhaust line 9. The temperature T4 is measured by the sensor 14.
L’invention porte sur un procédé de détermination de la pression P3 en amont de la turbine 12 permettant d’utiliser uniquement les informations de l’environnement de la turbine.The invention relates to a method for determining the pressure P3 upstream of the turbine 12 making it possible to use only information from the environment of the turbine.
Ici, la détente thermique de la turbine 12 est modélisée par une détente isentropique :Here, the thermal expansion of the turbine 12 is modeled by an isentropic expansion:
YechYech
P3 _ / T3 \ Yech ~P4~ \T4Ïs) (1)P3 _ / T3 \ Yech ~ P4 ~ \ T4Ïs) (1)
Où P3 est la pression en amont de la turbine 12, c’est-à-dire la pression des gaz entrant dans la turbine 12 que l’on souhaite modéliser,Where P3 is the pressure upstream of the turbine 12, that is to say the pressure of the gases entering the turbine 12 that we wish to model,
T3 est la température en amont de la turbine 12,T3 is the temperature upstream of the turbine 12,
P4 est la pression en aval de la turbine 12, c’est-à-dire la pression sortant de la turbine 12,P4 is the pressure downstream of the turbine 12, that is to say the pressure leaving the turbine 12,
Yech est le coefficient adiabatique des gaz d’échappement.Y ech is the adiabatic coefficient of the exhaust gases.
T4is est la température isentropique en aval de la turbine 12, c’est-à-dire la température des gaz sortant de la turbine 12 pour une détente isentropique.T4is is the isentropic temperature downstream of the turbine 12, that is to say the temperature of the gases leaving the turbine 12 for isentropic expansion.
La température T4is n’est pas la température T4 mesurée par le capteur 14 de température en aval de la turbine 12. On détermine donc la température isentropique en aval de la turbine, T4is, en fonction de la température T4 mesurée par le capteur de température 14 :The temperature T4is is not the temperature T4 measured by the temperature sensor 14 downstream of the turbine 12. The isentropic temperature downstream of the turbine, T4is, is therefore determined as a function of the temperature T4 measured by the temperature sensor 14:
T4is= T3T3 — T4 (2)T4is = T3T3 - T4 (2)
Où % est le rendement isentropique de la turbine 12.Where% is the isentropic efficiency of the turbine 12.
Ceci requiert donc une modélisation du rendement isentropique, qis, de la turbine 12. Celle-ci est obtenu à partir d’une cartographie qui, en fonction d’une grandeur caractéristique de l’ouverture de la turbine 12, Posturbo, et du débit, Q,urblne, traversant la turbine 12, donne la valeur du rendement isentropique, qis, de la turbine 12.This therefore requires modeling of the isentropic efficiency, q is , of the turbine 12. This is obtained from a map which, as a function of a quantity characteristic of the opening of the turbine 12, Pos turbo , and of the flow rate, Q, urbl ne, passing through the turbine 12, gives the value of the isentropic efficiency, q is , of the turbine 12.
— Cccrto(PoSi-Urbo> Qturbine) (2) - Cccrto (PoSi- U rbo> Qturbine) (2)
Le turbocompresseur 13 peut être du type à géométrie variable comprenant des ailettes mobiles, l'inclinaison des ailettes du stator qui canalisent l'introduction du gaz dans les aubes du rotor de turbine étant par exemple variable, et étant pilotée par le calculateur. Dans ce cas, la grandeur caractéristique de l’ouverture de la turbine 12, Posturbo, peut être une valeur représentative de la position des ailettes.The turbocharger 13 may be of the variable geometry type comprising movable fins, the inclination of the stator fins which channel the introduction of gas into the blades of the turbine rotor being for example variable, and being controlled by the computer. In this case, the characteristic size of the opening of the turbine 12, Pos tur bo, can be a value representative of the position of the fins.
Le turbocompresseur 13 peut aussi être un turbocompresseur à géométrie fixe, le circuit de suralimentation peut comprendre une branche de dérivation de la turbine 12, appelée en anglais bypass ou waste gâte, pourvue d'une électrovanne pilotée par le calculateur, qui permet de réguler le débit et donc la pression en entrée de turbine 12. Dans ce cas, la grandeur caractéristique de l’ouverture de la turbine 12, Posturbo, peut être une valeur représentative de l’ouverture de cette branche de dérivation.The turbocharger 13 can also be a turbocharger with fixed geometry, the supercharging circuit can comprise a branch branch of the turbine 12, called in English bypass or waste tank, provided with a solenoid valve controlled by the computer, which makes it possible to regulate the flow rate and therefore the pressure at the turbine inlet 12. In this case, the characteristic magnitude of the opening of the turbine 12, Pos turbo , may be a value representative of the opening of this branch branch.
La cartographie peut être apprise via des essais préalables de caractérisation de la turbine 12. Le débit Cabine, traversant la turbine 12 est une information qui peut être déterminée à partir d’une information capteur débitmètre à laquelle on ajoute le débit carburant pour en déduire le débit échappement passant dans la turbine.The mapping can be learned via preliminary characterization tests of the turbine 12. The cabin flow rate, passing through the turbine 12 is information which can be determined from flowmeter sensor information to which the fuel flow is added to deduce the exhaust flow passing through the turbine.
La figure 2 présente un logigramme schématisant les étapes du procédé.FIG. 2 presents a flow diagram schematizing the steps of the method.
Ayant préalablement détermine la grandeur caractéristique, Posturbo ,de l’ouverture de la turbine 12, et le débit, Qturbine, de gaz traversant la turbine 12,Having previously determined the characteristic quantity, Pos tur bo, of the opening of the turbine 12, and the flow rate, Q tur bine, of gas passing through the turbine 12,
A l’étape 30, on lit dans la cartographie la valeur du rendement isentropique, qis, de la turbine 12 associée au couple de valeur formé par le débit de gaz, Qturbine, et la grandeur caractéristique de l’ouverture de la turbine 12, Posturbo,In step 30, the value of the isentropic efficiency, q is , of the turbine 12 associated with the torque of value formed by the gas flow, Qturbine, and the characteristic quantity of the opening of the turbine 12 are read in the mapping. , Pos tur bo,
A l’étape 40, on procède à la détermination de la température isentropique, T4is, en aval de la turbine 12, à l’aide de la relation (2), du rendement isentropique, qis, de la température T3 déterminée en amont de la turbine 12 et de la température T4 déterminée en aval de la turbine 12.In step 40, the isentropic temperature, T4is, is determined downstream of the turbine 12, using the relation (2), isentropic efficiency, q is , of the temperature T3 determined upstream of the turbine 12 and of the temperature T4 determined downstream of the turbine 12.
A l’étape 50, on détermine la pression P3 des gaz d’échappement entrant dans la turbine 12 à partir de la pression P4 du gaz sortant de la turbine 12, de la température isentropique T4is et du modèle de détente isentropique de la turbine de la relation (1).In step 50, the pressure P3 of the exhaust gases entering the turbine 12 is determined from the pressure P4 of the gas leaving the turbine 12, the isentropic temperature T4is and the isentropic expansion model of the turbine of the relation (1).
L’invention ne se limite pas au mode de réalisation décrit. En variante, le capteur de température T3 des gaz en amont de la turbine 12 et/ou le capteur de température T4 des gaz en aval de la turbine 12 et/ou le capteur de pression P4 des gaz en aval de la turbine 12 peuvent être remplacés chacun par un estimateur pour déterminer ces paramètres. Ainsi on peut avoir la configuration spécifique suivante : un estimateur pour la température T3 avec un capteur de température T4 et un estimateur de pression P4.The invention is not limited to the embodiment described. As a variant, the temperature sensor T3 of the gases upstream of the turbine 12 and / or the temperature sensor T4 of the gases downstream of the turbine 12 and / or the pressure sensor P4 of the gases downstream of the turbine 12 can be each replaced by an estimator to determine these parameters. So we can have the following specific configuration: an estimator for temperature T3 with a temperature sensor T4 and a pressure estimator P4.
L’invention permet l’obtention d’une pression P3 en amont de la turbine 12 plus précis en statique et plus fiable que l’art antérieur. L’usage d’une pression P3en amont de la turbine 12 déterminé selon le procédé de l’invention de supprimer les risques d’instabilité des régulations de la suralimentation et de la recirculation de gaz d’échappement. L’invention permet d’améliorer la protection des composants à l’échappement et la précision du prépositionnement des actionneurs du turbocompresseur 13 et / ou de la vanne 19 de dosage EGR.The invention makes it possible to obtain a pressure P3 upstream of the turbine 12 which is more precise in static and more reliable than the prior art. The use of a pressure P3 upstream of the turbine 12 determined according to the method of the invention eliminates the risks of instability of the regulations of the supercharging and of the recirculation of exhaust gases. The invention makes it possible to improve the protection of the components at the exhaust and the precision of the prepositioning of the actuators of the turbocharger 13 and / or of the EGR metering valve 19.
Claims (7)
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| FR1751273A FR3063109B1 (en) | 2017-02-17 | 2017-02-17 | PROCESS FOR DETERMINING THE PRESSURE OF THE EXHAUST GASES UPSTREAM OF THE TURBINE OF A TURBOCHARGER EQUIPPED WITH A THERMAL ENGINE |
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| FR1751273A FR3063109B1 (en) | 2017-02-17 | 2017-02-17 | PROCESS FOR DETERMINING THE PRESSURE OF THE EXHAUST GASES UPSTREAM OF THE TURBINE OF A TURBOCHARGER EQUIPPED WITH A THERMAL ENGINE |
| FR1751273 | 2017-02-17 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2856738A1 (en) * | 2003-06-30 | 2004-12-31 | Siemens Ag | Exhaust gas counter-pressure detecting method for internal combustion engine, involves determining pressure quotient from operating point, where quotient represents ratio between upstream and downstream exhaust gas pressures |
| DE102004051837A1 (en) * | 2004-10-25 | 2006-05-04 | Siemens Ag | Method and device for controlling and diagnosing an exhaust gas turbocharger |
| US20090094009A1 (en) * | 2007-10-04 | 2009-04-09 | Martin Muller | System and method for modeling of turbo-charged engines and indirect measurement of turbine and waste-gate flow and turbine efficiency |
| FR2923538A3 (en) * | 2007-11-12 | 2009-05-15 | Renault Sas | Turbine upstream pressure estimating system for supercharged oil engine of motor vehicle, has calculation units calculating expansion ratio of turbine from magnitude representing temperature variation to deduce upstream pressure of turbine |
| DE102015201449B3 (en) * | 2015-01-28 | 2016-04-07 | Ford Global Technologies, Llc | Method and device for determining a derived value for the pressure in the exhaust manifold of an internal combustion engine |
-
2017
- 2017-02-17 FR FR1751273A patent/FR3063109B1/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2856738A1 (en) * | 2003-06-30 | 2004-12-31 | Siemens Ag | Exhaust gas counter-pressure detecting method for internal combustion engine, involves determining pressure quotient from operating point, where quotient represents ratio between upstream and downstream exhaust gas pressures |
| DE102004051837A1 (en) * | 2004-10-25 | 2006-05-04 | Siemens Ag | Method and device for controlling and diagnosing an exhaust gas turbocharger |
| US20090094009A1 (en) * | 2007-10-04 | 2009-04-09 | Martin Muller | System and method for modeling of turbo-charged engines and indirect measurement of turbine and waste-gate flow and turbine efficiency |
| FR2923538A3 (en) * | 2007-11-12 | 2009-05-15 | Renault Sas | Turbine upstream pressure estimating system for supercharged oil engine of motor vehicle, has calculation units calculating expansion ratio of turbine from magnitude representing temperature variation to deduce upstream pressure of turbine |
| DE102015201449B3 (en) * | 2015-01-28 | 2016-04-07 | Ford Global Technologies, Llc | Method and device for determining a derived value for the pressure in the exhaust manifold of an internal combustion engine |
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