WO2015185856A1 - Système d'alimentation de turbomachine en fluide avec un ensemble de pompage basse pression comprenant deux pompes en parallèle - Google Patents
Système d'alimentation de turbomachine en fluide avec un ensemble de pompage basse pression comprenant deux pompes en parallèle Download PDFInfo
- Publication number
- WO2015185856A1 WO2015185856A1 PCT/FR2015/051465 FR2015051465W WO2015185856A1 WO 2015185856 A1 WO2015185856 A1 WO 2015185856A1 FR 2015051465 W FR2015051465 W FR 2015051465W WO 2015185856 A1 WO2015185856 A1 WO 2015185856A1
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- WO
- WIPO (PCT)
- Prior art keywords
- pressure pump
- fluid
- low
- low pressure
- pump
- Prior art date
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/236—Fuel delivery systems comprising two or more pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/40—Use of a multiplicity of similar components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/98—Lubrication
Definitions
- the invention relates to the general technical field of aircraft turbomachines such as turbojets and turboprops. More specifically, the invention belongs to the technical field of turbomachine fluid supply systems, in particular lubricant or fuel.
- a fuel supply system for a turbomachine comprises a low pressure pump configured to increase the pressure of the fuel flowing to a high pressure displacement pump after passing through a hydraulic resistor.
- the low pressure pump is in particular a centrifugal pump.
- the high pressure displacement pump is intended to supply constant flow fluid both a variable geometry feed circuit and a fuel supply circuit of a combustion chamber.
- the carburizing fuel system of the combustion chamber comprises a fuel metering device configured to regulate the flow of fuel to the fuel injection systems of the combustion chamber. More specifically, the fuel dispenser is intended to allow an excess fuel flow through a recirculation loop configured to route fuel upstream of the high pressure pump.
- the invention aims to at least partially solve the problems encountered in the solutions of the prior art.
- turbomachine supply system fluid preferably fuel, comprising:
- a low pressure pumping assembly comprising a main branch comprising a first low pressure pump
- a downstream hydraulic resistor comprising at least one element chosen from a fluid doser, a filter, a flow meter, an exchanger, a shut-off valve and an injection system, and
- a high pressure displacement pump located between the low pressure pumping assembly and the downstream hydraulic resistor.
- the low-pressure pumping assembly comprises a secondary branch in parallel with the main branch, the secondary branch comprising a second low-pressure pump and a power supply controller configured to vary the flow rate of fluid supplying the second pump. low pressure.
- the low pressure pumping assembly makes it possible to obtain a better compromise with regard to the energy efficiency, both during the phases of takeoff flight, climb and cruising phases of the turbomachine, which would not be possible. so significantly a low pressure pumping assembly with a single centrifugal pump.
- the power converter is in particular configured to control the fluid supply of the second low pressure pump.
- the power inverter is configured to vary the flow rate of fluid supplying the second low-pressure pump relative to those supplying the first low-pressure pump.
- the power converter is preferably able to limit the flow of fluid supplying the second low pressure pump.
- the fluid in the feed system is especially lubricant or fuel.
- the invention may optionally include one or more of the following features combined with one another or not.
- the power supply variator comprises a shutter movable between an extreme open position in which the power converter circulates fluid to the second low-pressure pump, and an extreme closing position in which the power converter prevents at least partially the supply of the second fluid low pressure pump,
- the opening of the shutter is electrically or electromechanically controlled, so as to allow fluid to flow to the second low pressure pump when the rotational speed of the high pressure body of the turbomachine exceeds a variable threshold .
- the pressure threshold is likely to be fixed during operation of the turbomachine and / or between flights.
- the power supply dimmer is bistable with a stable opening state in which the power supply controller circulates fluid to the second low-pressure pump, and a stable state of closure in which the drive controller power supply at least partially prevents the supply of the second fluid low pressure pump.
- the power converter comprises at least one stable intermediate position between the closed state and the open state, preferably a plurality of stable intermediate positions.
- the power converter is then notably configured to vary the flow rate feeding the second low pressure pump within a continuous range of flow values.
- the power supply controller is a valve comprising a non-return valve, a valve, a fur or a drawer.
- the first low pressure pump and the second low pressure pump are centrifugal pumps whose wheels are located head to tail. It is thus possible to simplify the integration of low pressure pumps in the turbomachine, and reduce the energy levy operated by these pumps to operate. In addition, the implementation of such a solution allows the balancing of the resulting axial forces on the pumping assembly.
- the first low pressure pump and the second low pressure pump are preferably identical.
- This preferred configuration has the advantage of reducing handling and manufacturing costs.
- the main branch preferably comprises a resistive element downstream of the first low-pressure pump, the hydraulic resistance of the resistive element being equal to that of the power supply controller.
- the recirculation phenomena between the main loop and the secondary loop are limited.
- the high pressure pump is a positive displacement pump gear configured to be driven mechanically by a turbomachine transmission box.
- the transmission box preferably transmits a torque transmitted by a turbomachine high pressure shaft to mechanically drive the high pressure displacement pump.
- the high pressure displacement pump is mounted on an accessory relay box, also known as the "Accessorry Gear Box” or "AGB”.
- AGB Accessorry Gear Box
- the high-pressure displacement pump is then a robust and proven technology, which requires development efforts and limited certifications.
- the downstream hydraulic resistor preferably comprises a fluid metering device and an injection system, the fluid metering device being configured to regulate the flow towards the injection system and / or in the direction of a fluid recirculation loop configured to convey fluid upstream of the high pressure pump.
- the fluid recirculation loop is in particular configured to convey fluid from the dispenser to an evacuation node located between the low pressure pump assembly and the high pressure pump.
- the evacuation node connects for example the supply circuit of the injection system to the upstream circuit.
- the evacuation node is as close as possible to the inlet of the high pressure displacement pump, in order to limit the thermal power dissipated in the fluid recirculation loop. Nevertheless, the evacuation node is generally upstream of an upstream hydraulic resistance.
- the feed system preferably comprises an upstream hydraulic resistor located between the low pressure pump assembly and the high pressure pump.
- the upstream hydraulic resistor comprises at least one element chosen from an exchanger, a filter, a shut-off valve or a flow meter.
- the invention also relates to a turbomachine comprising a feed system as defined above.
- the turbomachine may comprise a differential gearbox configured to rotate at least one propeller, and intended to be supplied with lubricant by the feed system as defined above.
- the turbomachine is in particular a turbomachine set of counter-rotating propellers not careened, also known as the "Open Rotor".
- Figure 1 is a partial schematic representation of a turbomachine fluid supply system, according to a first embodiment of the invention
- FIG. 2 is a partial schematic representation of a turbomachine fluid supply system, according to a second embodiment of the invention
- Figure 3 is a partial schematic sectional representation of the first low pressure pump and the second low pressure pump, located head to tail.
- FIG. 1 represents a fluid turbine engine 1 supply system 10.
- the fluid is fuel.
- the turbomachine 1 comprises a differential gear (not shown) configured to rotate at least one propeller
- the fluid may also be a lubricant, typically oil.
- the turbomachine 1 comprises a combustion chamber 2 and the fuel supply system 10 of the combustion chamber 2.
- the combustion chamber 2 comprises a plurality of fuel injectors and fuel injection systems 62. injection 62 cooperate with the injectors to feed the combustion chamber 2 with the fuel passing through the feed system 10.
- the supply system 10 comprises an upstream circuit 100 and a downstream circuit 60 connected to the upstream circuit 100.
- the upstream circuit 100 is intended to regulate the flow rate and the pressure of the fuel supplying the downstream circuit 60.
- the upstream circuit 100 serves in particular to increasing the pressure of the fuel flowing in the direction of the downstream circuit 60.
- upstream and downstream are defined with reference to the general direction of flow of the fuel in the supply system 10 towards the fuel chamber. combustion 2.
- the upstream circuit 100 comprises a low pressure pumping assembly
- the term "hydraulic resistance” is used to define in this document, by analogy with the field of electricity, the quantity resulting from the ratio between the pressure difference of fluid between the inlet and the outlet of an element of the supply system on the flow of fluid passing through the element. By metonymy and always by analogy with the field of electricity, the term “hydraulic resistance” is also used to designate an element of the power system characterized by this magnitude.
- the upstream hydraulic resistor 104 comprises for example an exchanger, a fuel filter, a shut-off valve and / or a flow meter.
- the low pressure pumping assembly 101 is configured to increase the fuel pressure to the high pressure pump 102, so as to limit / prevent cavitation hazards within the high pressure pump 102.
- the high volumetric pump pressure 102 is designed to supply the downstream circuit 60 with constant flow fuel.
- the high-pressure pump 102 is a volumetric gear pump configured to be driven mechanically by a turbomachine transmission box 1.
- the constant fuel flow rate at the output of the positive-displacement gear pump 102 is greater than the flow rate necessary to supply the injection systems 62, regardless of the phase in question of the theft of the turbomachine 1.
- the constant flow rate provided by the high pressure displacement pump 102 is determined according to the flow rates necessary for the operating speeds of the turbomachine 1 the most constraining, that is to say the flow rates for low speeds.
- the flow circulating in the feed system 10 is therefore likely to be very important in conventional designs. This results in thermal power dissipated by the power system 10 and a decrease in the energy efficiency of the power system 10.
- the feed system 60 of the injection systems forming part of the downstream circuit 60, comprises a fuel feeder 64 configured to regulate the flow towards the injection systems 62.
- the fuel feeder 64 redirects the excess fuel into the fuel system.
- the supply circuit 60 of the injection systems 62 upstream of the high pressure pump 102 through a recirculation loop 610 of fuel.
- the fuel recirculation loop 610 is located between a first node A at the outlet of the fuel dispenser 64 and an evacuation node B located upstream of the high pressure pump 102. In the embodiment of FIG. evacuation B is located between the low pressure pumping assembly 101 and the upstream hydraulic resistor 104.
- the flow of fuel flowing in the recirculation loop 610 generates a substantial portion of the thermal power dissipated in the supply system 10.
- the supply circuit 60 of the injection systems further comprises, in known manner, a hydraulic resistor 66 downstream of the recirculation loop 610.
- This hydraulic resistor 66 comprises at least one element chosen from a fuel filter, a flow meter, a exchanger and a high-pressure shut-off valve.
- the fuel dispenser 64, the hydraulic resistor 66 and the injection systems 62 form a downstream hydraulic resistor 62, 64, 66.
- the low-pressure pump assembly 101 comprises a main branch comprising a first low-pressure pump 11, and a secondary branch 200 comprising a second low-pressure pump 201.
- the secondary branch 200 further comprises a power supply controller 210, 220 configured to vary the flow of fluid supplying the second low-pressure pump 201.
- the power converter 210, 220 is notably configured to vary the proportions of fluid supplying the secondary branch 200 relative to those supplying the main branch.
- the secondary branch 200 and the main branch are in parallel.
- the main branch and the secondary branch 200 are connected to each other at an input node E and meet at an output node S upstream of the high-pressure pump 102.
- the Evacuation node B is located between the output node S and the upstream hydraulic resistor 104.
- the low pressure pumping assembly 101 is configured to increase the fuel pressure flowing from the inlet node E to the output node S.
- the main branch comprises a resistive element 230.
- the resistive element 230 is configured to equalize the hydraulic resistance of the main branch and the secondary branch 220, which makes it possible to limit the fuel recirculation phenomena in the low pumping assembly. pressure 101, and in the system supply 10 in general.
- the resistive element 230 takes for example the form of a diaphragm.
- the first low pressure pump 11 and the second low pressure pump 201 are centrifugal pumps whose wheels are preferably located head to tail, so as to reduce the size of the turbomachine 1 and facilitate the integration of the low pressure assembly 101 in the turbomachine 1.
- the wheels of the first low pressure pump 11 and that of the second low pressure pump 201, shown with reference to Figure 3, are then located opposite one another, preferably being coaxial or located around the same axis.
- the fluid flows in the direction of the arrow 301 to the arrow 304 in the second low pressure pump 201 on the one hand, and the arrow 302 to the arrow 304 in the first low pressure pump 11 on the other hand.
- the first low-pressure pump 11 and the second low-pressure pump 201 are preferably identical, especially for reasons of economy of scale and maintenance costs.
- the hydraulic resistance of the resistive element 230 is equal to that of the flow limiting means 210, 220.
- the power converter 210, 220 is located in the secondary branch 220 in series with the second low-pressure pump 201, being upstream of the second low-pressure pump 201.
- the power supply controller 210, 220 may also be in series with the second low-pressure pump 201, being downstream of this pump. In the latter case, the pressure drops at the inlet of the second low-pressure pump 201 are lower than when the power supply controller 210, 220 is upstream of the second low-pressure pump 201. Risks of cavitation inside of the second low pressure pump 201 are likely to be reduced.
- the power supply controller 210, 220 comprises a shutter 214, 224 movable between an extreme open position and an extreme closed position.
- the power supply controller 210, 220 is able to limit the flow of fluid supplying the second low-pressure pump 201.
- extreme open position the power supply controller 210, 220 circulates fluid to the second low-pressure pump 201.
- the power supply controller 210, 220 In the extreme closed position, the power supply controller 210, 220 completely prevents the supply of fuel to the pump.
- second low-pressure pump 201 is allowed to circulate a leakage flow having a predetermined value, so as to cool the second low-pressure pump 201.
- the power converter 210, 220 is preferably a bistable actuator with a stable opening state in which the shutter 214, 224 is in the extreme open position, and a stable state of closure in which the shutter 214 , 224 is in the extreme closed position.
- the power supply controller 210, 220 is an "all or nothing" type actuator.
- the power supply controller 210 is a valve 210 comprising a nonreturn valve 214.
- the opening and closing of the shutter 214 in the form of non-return valve are controlled by a device electrical control 300, so as to counter the return force of a spring 212 configured to return the shutter 212 to the extreme closed position, in the absence of any control exerted on the power supply controller 210.
- opening and closing of the shutter 214 are electrically controlled directly or indirectly, so as to allow fluid to flow to the second low pressure pump 201 when the fuel pressure at the inlet node E of the low pressure pumping assembly 101 exceeds a variable threshold.
- the variable threshold is for example determined as a function of the speed of rotation of a high pressure body of the turbomachine 1 by a digital control system (not shown), also known as
- variable threshold may vary during the operation of the turbine engine 1 or between the flights of the turbomachine 1. More specifically, the control member 300 comprises an electronic control unit 302, also known as ECU. The electronic control unit 302 controls the opening and closing of the power converter 210, via a servo valve 304 or a solenoid valve 304, depending on the variable threshold.
- the power supply system 10 of FIG. 2 differs from that of FIG. 1 in that the power supply controller 220 is a valve 220 comprising a drawer 224.
- the drawer 224 acts as a shutter configured to slide between the extreme opening position and the extreme closing position, as a function of the pressure difference across the low pressure pump 11 between the pressure PI at the input node E and the pressure P2 at a control node C.
- the slide 224 is mechanically connected to a return spring 222 configured to force the shutter 224 to be in the extreme closed position when the pressure P2 is less than an opening threshold.
- the power supply controller 220 is controlled hydraulically by the pressure difference between the inlet and the discharge of the pump 11.
- the opening threshold of the power supply controller 220 is then fixed. It is in particular determined according to the characteristics of the slide 224 and the stiffness of the spring 222. In particular, it is possible to mechanically adjust the opening threshold of the power converter 210, 220 carefully choosing the stiffness of the spring 212, 222.
- the low-pressure pumping assembly 101 makes it possible to improve the energy efficiency of the supply system 10 by controlling the supply of the secondary branch 220, via the power supply controller 210, 220, in function of the pressure differential across the low pressure pumping assembly 101.
- This pressure differential reflects the rotation speed of the high pressure body of the engine and therefore the engine cycle point considered.
- the low pressure pumping assembly 101 is configured so as to obtain a satisfactory energy efficiency, both during the phases of takeoff flight, climb and cruise phases of the turbomachine 1, which would not significantly allow a low pressure pumping assembly of conventional structure with a single centrifugal pump.
- various modifications may be made by those skilled in the art to the invention which has just been described without departing from the scope of the disclosure of the invention.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Non-Positive-Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1620649.2A GB2540524B (en) | 2014-06-05 | 2015-06-03 | System for supplying a turbine engine with fluid having a low pressure pumping assembly comprising two pumps in parallel |
US15/316,057 US10526973B2 (en) | 2014-06-05 | 2015-06-03 | System for supplying a turbine engine with fluid having a low pressure pumping assembly comprising two pumps in parallel |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1455114 | 2014-06-05 | ||
FR1455114A FR3022000B1 (fr) | 2014-06-05 | 2014-06-05 | Systeme d'alimentation de turbomachine en fluide avec un ensemble de pompage basse pression comprenant deux pompes en parallele |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015185856A1 true WO2015185856A1 (fr) | 2015-12-10 |
Family
ID=51210658
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2015/051465 WO2015185856A1 (fr) | 2014-06-05 | 2015-06-03 | Système d'alimentation de turbomachine en fluide avec un ensemble de pompage basse pression comprenant deux pompes en parallèle |
Country Status (4)
Country | Link |
---|---|
US (1) | US10526973B2 (fr) |
FR (1) | FR3022000B1 (fr) |
GB (1) | GB2540524B (fr) |
WO (1) | WO2015185856A1 (fr) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3059718B1 (fr) | 2016-12-02 | 2019-06-21 | Safran Aircraft Engines | Dispositif hydromecanique de coupure a hysteresis pour systeme de lubrification de turbomachine |
FR3069021B1 (fr) * | 2017-07-13 | 2019-07-26 | Safran Aircraft Engines | Circuit et procede de dosage de carburant a compensation de variabilite de la densite du carburant |
GB201900906D0 (en) * | 2019-01-23 | 2019-03-13 | Rolls Royce Plc | Oil scavenge system |
FR3106625B1 (fr) * | 2020-01-27 | 2022-11-04 | Safran Helicopter Engines | Circuit d’alimentation en carburant d’un moteur d’aéronef |
US11629652B2 (en) | 2020-02-05 | 2023-04-18 | Hamilton Sundstrand Corporation | Metering pump system |
FR3115075B1 (fr) * | 2020-10-14 | 2022-10-21 | Safran Aircraft Engines | Circuit d’alimentation en carburant pour une chambre de combustion de turbomachine |
US11725647B2 (en) | 2021-05-18 | 2023-08-15 | Hamilton Sundstrand Corporation | On-demand dual variable displacement positive displacement pumping system |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2782595A (en) * | 1952-08-29 | 1957-02-26 | Westinghouse Electric Corp | Fuel system for a gas turbine engine |
WO2000060239A2 (fr) * | 1999-04-07 | 2000-10-12 | United Technologies Corporation | Clapet de repartition de charge et systeme permettant de faire fonctionner en parallele des pompes centrifuges |
EP1853805A1 (fr) * | 2005-02-17 | 2007-11-14 | Hispano-Suiza | Alimentation en carburant d'un moteur d'aeronef |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
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US2506611A (en) * | 1948-03-02 | 1950-05-09 | Westinghouse Electric Corp | Fuel control for aviation gas turbine power plants |
US3026929A (en) * | 1954-03-17 | 1962-03-27 | Chandler Evans Corp | Compound centrifugal and gear fuel pump |
US2989842A (en) * | 1960-04-14 | 1961-06-27 | Cyrus F Wood | Fuel pumping system for engines having afterburners |
US3433016A (en) * | 1967-03-09 | 1969-03-18 | Gen Electric | Fuel delivery system |
US3511579A (en) * | 1968-07-22 | 1970-05-12 | Liquitrol Systems Inc | Control system for liquid pressure booster systems |
US3614269A (en) * | 1970-03-09 | 1971-10-19 | Chandler Evans Inc | Integrated pump-control system using a unitized pump |
US3699774A (en) * | 1970-09-17 | 1972-10-24 | Gen Electric | Fluid supply system |
US3696612A (en) * | 1970-12-30 | 1972-10-10 | Westinghouse Electric Corp | Fuel pump system for gas turbines |
US5118258A (en) * | 1990-09-04 | 1992-06-02 | United Technologies Corporation | Dual pump fuel delivery system |
US5186757A (en) * | 1991-08-26 | 1993-02-16 | Abney Sr Marvin D | Pig loading system and method thereof |
GB0521332D0 (en) * | 2005-10-20 | 2005-11-30 | Rolls Royce Plc | A gas feed assembly |
FR3010133B1 (fr) | 2013-09-02 | 2015-10-02 | Snecma | Reservoir comprenant une cloison inclinee munie a ses extremites d'orifices traversants pour une alimentation continue de turbomachine en liquide d'alimentation |
-
2014
- 2014-06-05 FR FR1455114A patent/FR3022000B1/fr active Active
-
2015
- 2015-06-03 GB GB1620649.2A patent/GB2540524B/en active Active
- 2015-06-03 US US15/316,057 patent/US10526973B2/en active Active
- 2015-06-03 WO PCT/FR2015/051465 patent/WO2015185856A1/fr active Application Filing
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2782595A (en) * | 1952-08-29 | 1957-02-26 | Westinghouse Electric Corp | Fuel system for a gas turbine engine |
WO2000060239A2 (fr) * | 1999-04-07 | 2000-10-12 | United Technologies Corporation | Clapet de repartition de charge et systeme permettant de faire fonctionner en parallele des pompes centrifuges |
EP1853805A1 (fr) * | 2005-02-17 | 2007-11-14 | Hispano-Suiza | Alimentation en carburant d'un moteur d'aeronef |
Also Published As
Publication number | Publication date |
---|---|
US20170101935A1 (en) | 2017-04-13 |
GB201620649D0 (en) | 2017-01-18 |
GB2540524A (en) | 2017-01-18 |
GB2540524B (en) | 2020-12-30 |
US10526973B2 (en) | 2020-01-07 |
FR3022000A1 (fr) | 2015-12-11 |
FR3022000B1 (fr) | 2016-10-21 |
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