EP3462091A1 - Ensemble chambre de combustion pourvu de buse à élément de guidage d'air supérieur axial pour une chambre de combustion non étagée d'un moteur - Google Patents

Ensemble chambre de combustion pourvu de buse à élément de guidage d'air supérieur axial pour une chambre de combustion non étagée d'un moteur Download PDF

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Publication number
EP3462091A1
EP3462091A1 EP18196253.1A EP18196253A EP3462091A1 EP 3462091 A1 EP3462091 A1 EP 3462091A1 EP 18196253 A EP18196253 A EP 18196253A EP 3462091 A1 EP3462091 A1 EP 3462091A1
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EP
European Patent Office
Prior art keywords
nozzle
air
combustion chamber
longitudinal axis
radially
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.)
Granted
Application number
EP18196253.1A
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German (de)
English (en)
Other versions
EP3462091B1 (fr
Inventor
Miklos Gerendas
Ruud Eggels
Max Staufer
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.)
Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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.)
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Publication of EP3462091A1 publication Critical patent/EP3462091A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the invention relates to a combustion chamber assembly having a nozzle for a non-stepped combustion chamber of an engine for providing a fuel-air mixture at a nozzle outlet opening of the nozzle.
  • a nozzle usually also serves to distort the supplied air, which is then, mixed with the supplied fuel, conveyed to the nozzle outlet opening of the nozzle in the combustion chamber.
  • a plurality of nozzles are combined in a nozzle assembly that includes a plurality of nozzles arranged side by side, usually along a circular line, for introducing fuel into the combustion chamber.
  • nozzles with a plurality of air ducts and at least one Kraftstoffleitkanal provide that extends a first air duct along a nozzle longitudinal axis of the nozzle main body and a Kraftstoffleitkanal opposite the first air duct, based on the nozzle longitudinal axis, radially further outward. At least one further air duct is then additionally provided with respect to the fuel guide, with respect to the nozzle longitudinal axis, lying radially further out.
  • From the prior art is also known and, for example, in the US 9,423,137 B2 or the US 5,737,921 provided to provide such a nozzle with a third air duct, which optionally radially outwardly offset end in the axial direction follows the end of the second air duct.
  • the outflow edge of the Kraftstoffleitkanals and the axially projecting air guide of the radially outer air duct are thus designed to influence an air flow from the air duct in such a coordinated and coordinated that are maintained by an axial projection of the air guide or the reference angle corresponding to the geometric specifications given above.
  • the reference angle according to variant (a) given above and the reference angle according to variant (b) given above may be identical.
  • a corresponding boundary line for example, meet both above under (a) and (b) conditions and thus both tangential to the axially projecting air guide and this simultaneously by a point on the discharge edge and a maximum in the axial direction on the discharge edge projecting point of Run air guiding element.
  • the proposed design of the discharge edge and the air guide at the end of the nozzle can be achieved that when the nozzle is properly mounted on the combustion chamber, a maximum outflow angle is passed under the air from the air duct with respect to the nozzle longitudinal axis in the direction of the combustion chamber, below 50 °.
  • this air unconditionally to the fuel-air mixture respectively the spray of fuel from the Kraftstoffleitkanal and air from the first, inner air duct (and optionally another air duct, between the inner air duct and the radially outermost, to his end the air duct having air duct is) is passed.
  • the proposed nozzle design is a maximum outflow angle, is passed under the air from the radially outer air duct with respect to the nozzle longitudinal axis in the direction of the combustion chamber, below 50 °.
  • the fuel better follows the flow path of the air, which flows out of the radially outermost air duct of the nozzle at several (at least two) radially outer air ducts.
  • a fuel-air mixture generated in the middle region at the end of the nozzle, in which the fuel is already distributed in droplet form, thus follows in a variant without further ado a flow path of the air flowing out of the radially outer air duct, so that the droplet-shaped fuel flows more radially also after outside and more strongly mixed with air, which leads to a more even distribution of the fuel and thus to a reduction of soot emissions.
  • the proposed arrangement and design of the axially projecting air guide element with respect to the discharge edge is initially fundamentally independent of a geometry of the air guide element, via which air flowing out at the end of the air guide channel is guided radially inwards. Accordingly, a minimum inner diameter of the nozzle outlet opening can be further defined via the air guide element, so that a tapering of the nozzle outlet opening (possibly combined with a subsequent downstream widening of the nozzle outlet opening to the combustion chamber) is realized via the radially outer (circulating peripheral) air guide element.
  • a burner seal of the nozzle assembly combustor assembly further includes a bearing portion extending along the longitudinal axis of the nozzle having a through hole in which the nozzle is positioned. It is provided here that the burner seal has a radially expanding flow-guiding element in the region of the nozzle outlet opening of the nozzle.
  • a combustion chamber end of the Burner direction is thus formed here with a flow guide for the guidance of the generated fuel-air mixture, which radially widens this flow in the axial direction.
  • An inner circumferential surface of the radially expanding flow guide extends at the end of the burner seal at an angle to the nozzle longitudinal axis, which substantially corresponds to the reference angle between the nozzle longitudinal axis and the boundary line or coincides with this reference angle. In this way, axial end points of the air guide element of the radially outer air guide channel and the flow guide element of the burner seal lie on the limiting straight line.
  • the air guide element of the nozzle and the flow guide element of the burner seal extend along this boundary straight line or an outer jacket surface of a corresponding straight circular cone.
  • the air guide element and the flow guide element can adjoin one another in a radially outward-pointing direction.
  • the boundary straight line runs tangentially to the outflow edge and tangentially to the axially projecting air guide element.
  • Outflow edge and air-guiding element of the nozzle are thus here designed and matched to one another such that the reference angle, which is tangential to the outflow edge and tangential to the air guide between the nozzle longitudinal axis and a boundary line, is less than or equal to 50 °.
  • the limiting straight can furthermore run through a point on the air guiding element, which lies in the axial direction behind the radially inwardly pointing curvature of the air guiding element.
  • About the radially inwardly facing, typically convex curvature of the spoiler is discharged from the radially outer air duct outflowing and possibly twisted air, radially inward, so that an air flow from the air duct has a radially inwardly pointing direction component.
  • the outflow edge of the Kraftstoffleitkanals and the spoiler are then configured geometrically to each other and / or each other, that the reference angle between the nozzle longitudinal axis and the Begrenzungsgeraden is less than or equal to 50 °, in which case the tangential to the outflow edge and tangential to the air guide extending Begrenzungsstraade extends through a (reference) point on the air guide, which is behind or downstream of the inwardly facing curvature of the guide element.
  • Outflow edge and air guide are here thus configured and arranged to each other that at the nozzle outlet opening via a straight circular cone with an opening angle which corresponds to twice the predetermined reference angle and the apex of which is on the (centrally extending) nozzle longitudinal axis, in particular the length is given which projects one end of the air guide element with respect to the outflow edge of the fuel guide channel in the axial direction (pointing towards the combustion chamber in the mounted state).
  • the nozzle may have, in addition to the first, inner air duct, at least two further air ducts which are radially injured to one another.
  • the guide channel with the axially projecting air guide whose axial length and configuration is predetermined with respect to the discharge edge of the fuel guide, then forms the radially outermost air duct.
  • the air guide thus defines the radially outermost boundary of the nozzle outlet opening and defines in particular the axial course of the inner diameter of the nozzle outlet opening at the combustion chamber end.
  • the burner seal in the region of the nozzle outlet opening of the nozzle form an end that terminates substantially flush or flush with a heat shield of the combustion chamber assembly.
  • the contour of the heat shield in the region of the edge portion thus adjoins the burner seal and allows a smooth transition from the burner seal to the heat shield in a radially outward direction.
  • At least in the Substantially flush connection of the burner seal with the heat shield also allows minimization of a radial gap between the burner seal and the heat shield, thereby avoiding penetration of combustion products between the burner seal and the heat shield.
  • the heat shield may optionally be chamfered at the edge portion of the opening through which the burner seal protrudes in order to allow a smooth or even softer transition to a flow directional element of the burner seal that widens radially outward in the axial direction. It is thus achieved, for example, that when a maximum axial displacement of the burner seal with respect to the heat shield occurs during operation of the engine, a radial distance between the burner seal and the heat shield is kept below a predetermined limit which, for example, is less than or equal to 0.2 mm.
  • a combustion chamber assembly may be provided in which the burner seal in the region of the nozzle outlet opening of the nozzle forms an end which protrudes over a heat shield of the combustion chamber assembly in the axial direction by a length a, for the relative to a wall thickness d of the above End a ⁇ 1.5 d applies.
  • FIG. 7A illustrates schematically and in section a (turbofan) engine T, in which the individual engine components along a rotation axis or center axis M are arranged one behind the other and the engine T is designed as a turbofan engine.
  • a fan F At an inlet or intake E of the engine T, air is sucked in along an entrance direction by means of a fan F.
  • This arranged in a fan housing FC fan F is driven by a rotor shaft S, which is rotated by a turbine TT of the engine T in rotation.
  • the turbine TT adjoins a compressor V, which has, for example, a low-pressure compressor 11 and a high-pressure compressor 12, and possibly also a medium-pressure compressor.
  • the fan F leads on the one hand in a primary air flow F1 to the compressor V air and on the other hand, to generate the thrust in a secondary air flow F2 a secondary flow channel or bypass channel B.
  • the bypass channel B extends around a compressor V and the turbine TT comprehensive core engine, the a primary flow channel for the supplied through the fan F to the core engine air.
  • the air conveyed into the primary flow passage via the compressor V enters a combustion chamber section BKA of the core engine in which the driving power for driving the turbine TT is generated.
  • the turbine TT has a high-pressure turbine 13, a medium-pressure turbine 14 and a low-pressure turbine 15.
  • the turbine TT thereby drives the rotor shaft S and thus the fan F via the energy released during combustion in order to generate the required thrust via the air conveyed into the bypass duct B.
  • Both the air from the bypass passage B and the exhaust gases from the primary flow passage of the core engine flow through an outlet A at the end of the engine T.
  • the outlet A in this case usually has a discharge nozzle with a centrally arranged outlet cone C.
  • FIG. 7B shows a longitudinal section through the combustion chamber section BKA of the engine T. It can be seen in particular in a (ring) combustion chamber 3 of the engine T.
  • a nozzle assembly is provided for injecting fuel or an air-fuel mixture into a combustion chamber 30 of the combustion chamber 3.
  • This comprises a combustion chamber ring R, on which along a circular line around the central axis M a plurality of (fuel / injection) nozzles 2 are arranged.
  • the nozzle outlet openings of the respective nozzles 2 are provided on the combustion chamber ring R, which lie within the combustion chamber 3.
  • Each nozzle 2 in this case comprises a flange, via which a nozzle 2 is screwed to an outer housing G of the combustion chamber 3.
  • FIG. 7C now shows a cross-sectional view of the basic structure of a nozzle 2 and the surrounding components of the engine T in the installed state of the nozzle 2.
  • the nozzle 2 is in this case part of a combustion chamber system of the engine T.
  • Die Nozzle 2 is located downstream of a diffuser DF and is inserted through an access hole L through a combustion chamber head 31, through a heat shield 300 and a top plate 310 of the combustion chamber 3 to the combustion chamber 30 of the combustion chamber 3 during assembly, such that a nozzle outlet opening formed on a nozzle main body 20 in the combustion chamber 30 ranges.
  • the nozzle 2 is positioned on the combustion chamber 3 via a bearing section 41 of the burner seal 4 and held in a passage opening of the bearing section 41.
  • the nozzle 2 further comprises a nozzle stem 21 extending substantially radially with respect to the center axis M and housing a fuel supply line 210 which delivers fuel to the nozzle main body 20.
  • a fuel chamber 22 On the nozzle main body 20, there are further formed a fuel chamber 22, fuel passages 220, heat shields 23, and air chambers for isolation 23a and 23b.
  • the nozzle main body 20 forms a (first) inner air duct 26 extending centrally along a nozzle longitudinal axis DM and radially outer (second and third) outer air ducts 27a and 27b for this purpose.
  • These air guide channels 26, 27 a and 27 b extend in the direction of the nozzle outlet opening of the nozzle 2.
  • At least one fuel guide channel 26 is formed on the nozzle main body 20.
  • This Kraftstoffleitkanal 25 is located between the first inner air duct 26 and the second outer air duct 27 a.
  • Verdralletti 270a, 270b for twisting the air supplied thereto. Furthermore, the nozzle main body 20 at the end of the third outer air duct 27b still an outer, radially inwardly facing air guide element 271b.
  • the nozzle 2 which is, for example, a pressure-assisted injection nozzle, follow according to the FIG. 7C with respect to the nozzle longitudinal axis DM and in the direction of the nozzle exit opening, onto the end of the fuel guide channel 25, from which fuel is supplied from the first inner, centrally extending air duct 26 during operation of the engine T, the ends of the second and third radially outward lying shipsleitkanäle 27a and 27b.
  • a sealing element 28 is still provided peripherally on the nozzle main body 20.
  • This seal member 28 is floatingly mounted between the heat shield 300 and the top plate 310 to compensate for radial and axial movement between the nozzle 2 and the combustion chamber 3 at various operating conditions and to ensure a reliable seal.
  • the burner seal 4 usually has a flow guide element 40 to the combustion chamber 30.
  • This flow guide 40 in conjunction with the third outer air duct 27b on the nozzle 2 for a desired flow guidance of the fuel-air mixture from the nozzle 2, more precisely the twisted air from the air ducts 26, 27a and 27b, and the Kraftstoffleitkanal 25th , arises.
  • a known from the prior art combustion chamber assembly according to the FIG. 7C may be detrimental to the formation of soot emissions.
  • the air flow directed radially inward from the third air guide channel 27b via the air guide element 271b may not lead to a desired homogeneous distribution of the fuel immediately downstream of the nozzle outlet opening.
  • regions with too much excess fuel can arise directly in the area downstream of the fuel guide channel 25, which in turn lead to generation of soot emissions.
  • the proposed solution can remedy to the different embodiments in the FIGS. 1A to 6 are shown.
  • an outflow edge 250 which bounds the end of the Kraftstoffleitkanals 25 radially outward at the nozzle exit opening, and in the axial direction x along the nozzle longitudinal axis DM opposite this Abströmrand 250 protruding air guide 271b for influencing an air flow LS from the third air duct 271b are formed and matched to one another that a reference angle ⁇ is less than or equal to 50 °, which is present between the nozzle longitudinal axis DM and a Begrenzungsgeraden 6.
  • This boundary line 6 passes through a (first) point at the outflow edge 250 (eg, by a point at a trailing edge of the discharge edge 250) and tangential to the axially projecting air guide element 271b, in particular tangential to the discharge edge 250 and tangential to the air flow LS first radially inwardly conductive air guide element 271b ,
  • the boundary straight line 6 extends through a point on the outflow edge 250 and a (reference) point 2712b of a combustion chamber-side end of the air-guiding element 271b protruding maximally in the axial direction x beyond the outflow edge 250.
  • nozzle 2 shown is, for example, the air guide 271b with a predetermined length l 1 in the axial direction x over the discharge edge 250 of the Kraftstoffleitkanals 25 so that the boundary line 6, as a tangent to the discharge edge 250 and a radially inwardly facing bulge 2711b of the air guide element 271b, an angle ⁇ ⁇ 50 ° to the centrally extending nozzle longitudinal axis DM includes.
  • the resulting from the third air duct 27b air flow LS is thus guided on an inner contour 2710b of the axially projecting shipsleitelements 271b radially outward direction within a spray cone 5 of a naturally resulting spray cone of the injected fuel from the Kraftstoffleitkanal 25 and thus the generated fuel-air Mixture is approximated.
  • the air flow LS from the third air duct 27b is thus directed via the thus arranged with respect to the outflow edge 250 of the Kraftstoffleitkanals 25 air guide 271b at the nozzle exit opening in a virtual straight circular cone, whose apex is located on the nozzle longitudinal axis DM and whose opening angle is 2 ⁇ .
  • the boundary line 6 thus shows in the FIG. 1 the course of an outer circumferential surface of this straight circular cone, against which the outflow edge 250 and the air guide element 271b (in the region of its curvature 2711b).
  • the air flow LS is forced into a flow path with an angle of less than 50 °, so that the air from the third air duct 27b is unconditionally directed to the spray flowing radially outward, which flows through the fuel from the fuel guide channel 25 and the twisted air from the first, inner air duct 26 and the second air duct 27a results.
  • FIG. 1B is the axial projection of the air guide element 271b with respect to the embodiment of the Figure 1A reduced.
  • the air guide 271b with its convex inwardly facing bulge 2711b with a smaller length l 2 compared to the outflow edge 250 of the Kraftstoffleitkanals 25 before (l 2 ⁇ l 1 ).
  • the position and geometry of the Abströmrandes 250 and the Heilleitelements 271b of the third Gutleitkanals 27b selected for selectively influencing the air flow LS and matched that the Begrenzungsgerade 6 as a tangent to the discharge edge 250 and the bulge 2711b of the air guide element 271b with the nozzle longitudinal axis DM includes the angle ⁇ ⁇ 50 °.
  • the boundary line 6 thus also passes through a point at Abströmrand 250 (a so-called "pre-filmers”) and a point which is located on a tangent to the combustion chamber 30 facing inner contour 2710b of the air guide element 271b.
  • the boundary line 6 also runs tangentially and thus through a point at the outflow edge 250 of the fuel guide 25.
  • the boundary line 6 extends through an axially outermost reference point 2712b.
  • the geometry and arrangement of the air guide 271b with respect to the discharge edge 250 of the Kraftstoffleitkanals 25 are selected such that for influencing the air flow LS from the third air duct 27b the discharge edge 250 and the inner contour 2710b downstream of the (inner) buckle 2711b at an outer Abut surface of a virtual reference or circular cone 7, the cone tip 70 is located on the nozzle longitudinal axis DM and has an opening angle of 2 ⁇ , with ⁇ ⁇ 50 °.
  • FIGS. 3A to 3F illustrate different geometries of the air guide element 271b, in particular with regard to the course of an over the radially inwardly facing bulge 2711b defined inner contour 2710b and the axial length of the air guide element 271b.
  • the burner seal 4 is designed with its combustion chamber side flow guide element 40 substantially flush with the heat shield 300 final.
  • the radially widening flow guide element 40 protrudes only with a length a over the heat shield 300 or, better, over an edge opening of the heat shield 300 bordering the opening for the burner seal 4, which is smaller than 1.5 times a wall thickness d of the flow guide element 40 ,
  • an inner circumferential surface of the flow-guiding element 40 of the burner direction 4 also extends below the same reference angle ⁇ to the nozzle longitudinal axis DM and thus joins in the radially outward direction along the Begrenzungsgeraden 6 to the air guide element 271b.
  • the bearing at a bearing 311 floating burner seal 4 is provided here with a tight fit between the flow guide 40 and the heat shield 300, so that at a occurring during operation of the engine T maximum axial displacement of the burner seal 4, a radial distance between the burner seal 4 and heat shield 300 does not exceed a predetermined limit of 0.2 mm.
  • a close fit between the burner seal 4 and the heat shield 300 in the region of the end of the flow guide element 40 also prevents the penetration of combustion products into a cavity between the burner seal 4 and the heat shield 300.
  • the continuously widening flow guide 41 with respect to the variant FIG. 4 less strongly inclined inner lateral surface formed. Nevertheless, it is also provided here that the flow guide element 40 terminates substantially flush or flush with the burner seal 300 and the inner circumferential surface of the flow guide element 40 extends below the reference angle ⁇ to the nozzle longitudinal axis DM.
  • FIG. 6 illustrates a perspective view of a possible embodiment of the in the FIG. 5 schematically illustrated burner seal with the flared to the combustion chamber 30 toward flow guide 40th

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP18196253.1A 2017-09-28 2018-09-24 Ensemble chambre de combustion pourvu de buse à élément de guidage d'air supérieur axial pour une chambre de combustion non étagée d'un moteur Active EP3462091B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017217329.7A DE102017217329A1 (de) 2017-09-28 2017-09-28 Düse mit axial überstehendem Luftleitelement für eine Brennkammer eines Triebwerks

Publications (2)

Publication Number Publication Date
EP3462091A1 true EP3462091A1 (fr) 2019-04-03
EP3462091B1 EP3462091B1 (fr) 2022-01-26

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US (1) US10808935B2 (fr)
EP (1) EP3462091B1 (fr)
DE (1) DE102017217329A1 (fr)

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US20160265778A1 (en) * 2015-03-10 2016-09-15 General Electric Company Hybrid air blast fuel nozzle
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US10808935B2 (en) 2020-10-20
EP3462091B1 (fr) 2022-01-26
US20190093897A1 (en) 2019-03-28

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