Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/08—Cooling; Heating; Heat-insulation
  • F01D25/14—Casings modified therefor
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/08—Cooling; Heating; Heat-insulation
  • F01D25/12—Cooling
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/246—Fastening of diaphragms or stator-rings
• • 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
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
• • 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
  • F05D2240/10—Stators
  • F05D2240/11—Shroud seal segments
• • 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
  • F05D2240/10—Stators
  • F05D2240/14—Casings or housings protecting or supporting assemblies within
• • 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
  • F05D2260/20—Heat transfer, e.g. cooling
  • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
• • 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
  • F05D2260/30—Retaining components in desired mutual position
  • F05D2260/31—Retaining bolts or nuts
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
  • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

• the invention relates to a turbine ring assembly comprising a plurality of ring sectors of ceramic matrix composite material (CMC material) or metal material and more particularly relates to a cooling fluid distribution element.
• CMC material ceramic matrix composite material
• metal material more particularly relates to a cooling fluid distribution element.
• the field of application of the invention is in particular that of aeronautical gas turbine engines.
• the invention is however applicable to other turbomachines, for example industrial turbines.
• the turbine ring is, in fact, confronted with a hot source (the vein in which the flow of hot gas flows) and a cold source (the cavity defined by the ring and the casing, subsequently designated by the expression "ring cavity”).
• the ring cavity must be at a pressure greater than that of the vein in order to prevent gas from the vein going up into this cavity and burn the metal parts.
• This overpressure is obtained by removing "cold" fluid at the compressor, which has not passed through the combustion chamber, and conveying it to the ring cavity. The upkeep such an overpressure thus makes it impossible to completely cut off the supply of "cold" fluid from the ring cavity.
• the invention aims specifically to meet the aforementioned needs.
• the invention proposes a cooling fluid distribution element intended to be fixed to a support structure for supplying cooling fluid to a wall to be cooled facing it, said distribution element comprising a body defining a internal volume of distribution of the cooling fluid and a multi-perforated plate which delimits this internal volume and comprises a plurality of through-through perforations which put in communication said internal volume of distribution of the cooling fluid with said wall to be cooled, the element distribution device further comprising an inlet opening into said internal volume of distribution of the cooling fluid, characterized in that said internal volume of distribution of the cooling fluid comprises directional fins substantially equidistant from said inlet port and said multi-perforated plate, for directing the coolant of said inlet port to said through-through perforations.
• a fluid distribution element typically air, cooling as described above has several advantages.
• the directional fins make it possible to better distribute the "fresh" air supply and thus to homogeneously cool the wall to be cooled, for example the ring sector placed downstream of the flow. Then, the cooling air being better channeled, it limits unnecessary recirculation and pressure losses and associated heating of the cooling gas.
• the fins significantly simplify the manufacturing process by offering several possible construction orientations (and therefore possible geometries) and limiting the post-merger operations in particular because there is more media to be removed during the construction of the internal volume according to a laser powder coating process.
• said body has a substantially pyramidal shape, a base of which is intended to receive said multi-perforated plate comprising said through-passing perforations diffusing the cooling fluid and whose inclined faces meet at the apex at said inlet orifice of cooling air.
• said directional fins are evenly distributed inside said internal volume.
• said directional fins comprise respective vertices forming an arch ensuring the support of a ceiling surface of said internal volume.
• said directional fins comprise a central fin disposed in a central axis passing through the axis of said inlet orifice, at least two other fins being distributed identically on each side of said central fin with tilt angles a and ⁇ by relative to the said central axis increasing.
• said first fin is inclined relative to said central axis in a range of the order of 30 to 44 ° and said second fin is inclined relative to said central axis in a range of about 45 to 59 ° .
• said directional vanes are in a number between 3 and 9.
• the present invention also relates to a turbine ring assembly comprising a plurality of ring sectors forming a turbine ring, a ring support structure and a plurality of distribution elements as mentioned above, as well as a turbomachine comprising such a turbine ring assembly.
• FIG. 1 is a diagrammatic exploded perspective view of a turbine ring assembly incorporating a cooling fluid distribution element according to the invention
• FIG. 2 is an end view, the multi-perforated plate removed, of the cooling fluid distribution element of FIG. 1, and
• FIG. 3 is a partial sectional view of the cooling fluid distribution element of FIG. 1, and
• FIG. 4 illustrates an example of a device for the realization of a distribution element.
• FIG. 1 is a schematic perspective exploded view of a portion of a high pressure turbine ring assembly comprising a turbine ring 11 made of a ceramic matrix composite material (CMC) or metal material and a support metal structure
• the ring support structure 13 is made of a material having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the material constituting the ring sectors.
• the turbine ring 11 surrounds a set of rotating blades (not shown) and is formed of a plurality of ring sectors 110.
• the arrow D A indicates the axial direction of the turbine ring 11 while the arrow D R indicates the radial direction of the turbine ring 11.
• the arrow D C indicates in turn the circumferential direction of the turbine ring.
• Each ring sector 110 has, in a plane defined by the axial directions D A and radial DR, a substantially shaped section of the Greek letter inverted ⁇ .
• the sector 110 comprises in fact an annular base 112 and upstream and downstream radial attachment tabs 114 and 116.
• upstream and downstream are used herein with reference to the direction of flow of the gas stream in the turbine which takes place along the axial direction D A.
• the annular base 112 comprises, in the radial direction DR of the ring 11, an inner face 112a and an outer face 112b opposite to each other.
• the inner face 112a of the annular base 112 is coated with a layer 113 of abradable material forming a thermal and environmental barrier and defines a stream of flow of gas in the turbine.
• the upstream and downstream radial catching tabs 114 and 116 project in the direction D R from the outer face 112b of the annular base 112 away from the upstream and downstream ends 1121 and 1122 of the annular base. 112.
• the upstream and downstream radial hooking tabs 114 and 116 extend over the entire circumferential length of the ring sector 110, that is to say over the entire arc described by the ring sector. 110.
• the ring support structure 13 which is integral with a turbine casing 130 comprises a central ring 131, extending in the axial direction D A , and having an axis of revolution coincides with the axis of revolution of the ring. turbine 11 when secured together.
• the ring support structure 13 further comprises an upstream annular radial flange 132 and a downstream annular radial flange 136 which extend, in the radial direction DR, from the central ring 31 to the center of the ring 11 and in the circumferential direction of the ring 11.
• the downstream annular radial flange 136 comprises a first end 1361 free and a second end 1362 integral with the central ring 131.
• the downstream annular radial flange 136 comprises a first portion 1363, a second portion 1364, and a third portion 1365 between the first portion 1363 and the second portion 1364.
• the first portion 1363 extends between the first end 1361 and the third portion 1365, and the second portion 1364 extends between the third portion 1365 and the second end 1362
• the first portion 1363 of the annular radial flange 136 is in contact with the downstream radial gripping tab 116.
• the second portion 1364 is thinned with respect to the first portion 1363 and the third portion 1365 so as to give some flexibility to the annular radial flange 136 and thus not too much constrain the turbine ring 11.
• the ring support structure 13 also comprises first and second upstream flanges 133 and 134 each having, in the illustrated example, an annular shape.
• the two upstream flanges 133 and 134 are fixed together on the upstream annular radial flange 132.
• the first and second upstream flanges 133 and 134 could be segmented into a plurality of ring sections.
• the first upstream flange 133 comprises a first end 1331 free and a second end 1332 in contact with the central ring 131.
• the first upstream flange 133 further comprises a first portion 1333 extending from the first end 1331, a second portion 1334 s extending from the second end 1332, and a third portion 1335 extending between the first portion 1333 and the second portion 1334.
• the second upstream flange 134 comprises a first end 1341 free and a second end 1342 in contact with the central ring 131, and a first portion 1343 and a second portion 1344, the first portion 1343 extending between the first end 1341 and the second portion 1344, and the second portion 1344 extending between the first portion 1343 and the second end 1342.
• the first portion 1333 of the first upstream flange 133 is supported on the upstream radial clawing tab 114 of the ring sector 110.
• the first and second upstream flanges 133 and 134 are shaped to have the first portions 1333 and 1343 distant the one of the other and the second portions 1334 and 1344 in contact, the two flanges 133 and 134 being removably attached to the upstream annular radial flange 132 with screws 160 and nuts 161 fixing, the screws 160 through openings 13340, 13440 and 1320 respectively provided in the second portions 1334 and 1344 of the two upstream flanges 133 and 134 as well as in the upstream annular radial flange 132.
• the nuts 161 are in turn integral with the ring support structure 13, being for example fixed by crimping to it .
• the second upstream flange 134 is dedicated to the recovery of the force of the high pressure distributor (DHP), firstly, by deforming, and, secondly, by passing this force to the crankcase line which is more mechanically robust, that is to say towards the line of the ring support structure 13.
• DHP high pressure distributor
• downstream annular radial flange 136 of the ring support structure 13 is separated from the first upstream flange 133 by a distance corresponding to the spacing of the upstream and downstream radial fastening tabs 114 and 116. in order to maintain the latter between the downstream annular radial flange 136 and the first upstream flange 133. It is possible to perform an axial prestressing of the flange 136. This makes it possible to take up the differences in expansion between the metal elements and the sectors of FIG. CMC ring when these are used.
• the ring assembly comprises, in the illustrated example, two first cooperating pins 119 with the upstream latching lug 114 and the first upstream flange 133, and two second pins 120 cooperating with the downstream latching lug 116 and the downstream annular radial flange 136.
• the third portion 1335 of the first upstream flange 133 comprises two orifices 13350 for receiving the first two pins 119
• the third portion 1365 of the annular radial flange 136 comprises two orifices 13650 configured to receive the two second pieces 120.
• each of the upstream and downstream radial attachment tabs 114 and 116 comprises a first end, 1141 and 1161, secured to the outer face 112b of the annular base 112 and a second end, 1142 and 1162, free.
• the second end 1142 of the upstream radial gripping tab 114 comprises two first lugs 117 each having an orifice 1170 configured to receive a first pin 119.
• the second end 1162 of FIG. the downstream radial gripping lug 116 comprises two second lugs 118 each having an orifice 1180 configured to receive a second lug 120.
• the first and second lugs 117 and 118 project in the radial direction D R of the lug ring.
• turbine 11 respectively of the second end 1142 of the upstream radial attachment tab 114 and the second end 1162 of the downstream radial attachment tab 116.
• the first two ears 117 are positioned at two different angular positions relative to the axis of revolution of the turbine ring 11.
• the two seconds ears 118 are positioned at two different angular positions with respect to the axis of revolution of the turbine ring 11.
• Each ring sector 110 further comprises rectilinear support surfaces 1110 mounted on the faces of the upstream and downstream radial attachment tabs 114 and 116 in contact respectively with the first upstream annular flange 133 and the downstream annular radial flange 136, that is to say on the upstream face 114a of the upstream radial hook tab 114 and on the downstream face 116b of the downstream radial hang tab 116.
• the straight supports could be mounted on the first one. upstream annular flange 133 and on the downstream annular radial flange 136.
• the straight supports 1110 make it possible to have controlled sealing zones. Indeed, the bearing surfaces 1110 between the upstream radial attachment tab 114 and the first upstream annular flange 133, on the one hand, and between the downstream radial attachment tab 116 and the downstream annular radial flange 136 are included. in the same rectilinear plane.
• the ring assembly further comprises, for each ring sector 110, a cooling fluid distribution element 150.
• This distribution element 150 constitutes a fluid diffuser (typically air) for the impact of a cooling flow F R on the outer face 112b of the ring sector 110 (see Figure 3)
• the element 150 is present in the delimited space between the turbine ring 11 and the ring support structure 13 and more particularly between the first upstream annular flange 133, the central ring 131 and the upstream and downstream radial attachment tabs 114 and 116.
• the distribution element 150 comprises a hollow body 151 which defines an internal volume of distribution of the cooling air and a multi-perforated plate 152 which delimits this internal volume and comprises a plurality of through-through perforations 153A which put in communication the internal volume of the hollow body 151 with the space opposite the outer face 112b of the ring sector 110.
• the hollow body 151 advantageously has a substantially pyramidal shape (that is to say progressive with an inlet narrower than the outlet) whose base is intended to receive the multi-perforated plate 152 having the radial through output perforations 153 A and whose inclined faces meet at the top at an axial inlet opening of the cooling air 154 (shown in Figure 3).
• the multi-perforated plate 152 is located facing (facing) the outer face 112b of the ring sector 110 and has in the illustrated example an elongated shape along the circumferential direction D c of the turbine ring 11
• the multi-perforated plate 152 also has a plurality of lateral through-exit perforations 153B that open between the first and second 116 snap-fastening tabs of the ring sector 110.
• No third-party elements are present between the multi-perforated plate perforated 152 and the outer face 112b of the ring sector 110 or the first 114 and second 116 hooking tabs so as not to slow down or disrupt the flow of cooling air passing through the plate 152 and impacting the sector d 110.
• the multi-perforated plate 152 which delimits the internal volume of the hollow body 151 is located on the side of the ring sector 110 (radially inwards).
• the distribution element 150 further comprises a cooling air guiding portion 155 which extends from the body 151 both in the radial direction D R and in the axial direction D A.
• the guide portion 155 is positioned radially outwardly relative to the multi-perforated plate 152.
• This guide portion 155 defines an interior channel (Illustrated by the inlet orifice 154 of Figure 3 which defines its output) which is in communication with the cooling air supply ports 192 and 190 respectively formed in the first 133 and second 134 upstream flanges.
• the flow of cooling air F R taken upstream in the turbine is intended to pass through the orifices 190 and 192 in order to be conveyed to the ring sector 110.
• the guide portion 155 defines the internal channel that the The cooling air flow F R is intended to pass through in order to be transferred to the interior volume of the hollow body 151 and to be distributed to the ring sector 110 following its passage through the perforated ulti plate 152.
• the internal channel has an inlet (not visible in the figure) which is preferably located opposite (in front and in contact) or in the extension (that is to say very little spaced from the first upstream flange 133) of the supply port 192 and communicating therewith.
• the respective apices 170A, 172A, 174A, 176A, 178A of the fins form a "vault" ensuring the support of the ceiling surface 180 for which the conventional support solutions do not work with such a zone not accessible from the outside.
• the pillars and the vault that they form at their summit thus offer a permanent support solution more efficient than the supports generic generic in terms of mass and aerodynamic performance and further making the geometry fully compatible with a laser powder bed melting process.
• this central fin 170 is disposed on both sides of this central fin 170, a first fin 172, 174 inclined relative to the central axis in a range of the order of 30 ° to 44 ° and a second fin 176, 178 inclined in a range of about 45 ° to 59 °.
• these fins have been defined by a single angle, and can therefore be called straight, it is of course possible, depending on the desired airflow deflection, to make a more complex geometry, specific to the image of turbine blades with inclinations and curvatures having a different angle upstream and downstream.
• the central fin may or may not be present.
• the number of directional fins can not be limiting and is advantageously between 3 and 9.
• the guide portion 155 also defines a housing 156 passing through, in this case, but which could alternatively be blind and including a fixing screw 163 intended to cooperate with this housing 156. ensures the fixing of the distribution element 150 to the ring support structure 13.
• the distribution element 150 comprises, in the illustrated example, an additional portion of maintenance 157 distinct from the guide portion 155 (the portion 157 does not necessarily have an internal channel for routing the cooling fluid which must then pass through an inner wall 186 open between these two portions).
• the portions 155 and 157 of the same distribution element 150 are offset along the circumferential direction D c .
• the holding portion 157 also defines a housing 158 cooperating with a fixing screw 163 to allow the attachment of the element 150 to the ring support structure 13.
• the securing screws 163 extend along the axial direction D A of the turbine ring and pass through the first 133 and second 134 upstream flanges when housed in the housings 156 and 158.
• the ring sectors 110 are made of CMC material, the latter are formed by forming a fiber preform having a shape close to that of the ring sector and densification of the ring sector by a ceramic matrix.
• ceramic fiber yarns for example SiC fiber yarns, such as those marketed by the Japanese company Nippon Carbon under the name "Hi-Nicalon S", or yarns made of carbon.
• the fiber preform is advantageously made by three-dimensional weaving, or multilayer weaving with development of debonding zones to separate the preform portions corresponding to the tabs 114 and 116 of the sectors 110.
• the weave can be interlock type, as illustrated.
• Other weaves of three-dimensional weave or multilayer can be used as for example multi-web or multi-satin weaves.
• the blank may be shaped to obtain a ring sector preform which is consolidated and densified by a ceramic matrix, the densification being able to be carried out in particular by chemical vapor infiltration (CVI) which is well known per se.
• CVI chemical vapor infiltration
• the textile preform can be a little hardened by CVI so that it is rigid enough to be manipulated, before raising liquid silicon by capillarity in the textile to densify.
• the ring sectors 110 are made of metallic material, the latter may for example be formed by one of the following materials: AMI alloy, C263 alloy or M509 alloy.
• the ring support structure 13 is made of a metallic material such as a Waspaloy® alloy or Inconel 718 or C263.
• the distribution element 150 is advantageously produced by a Laser Beam Melting (LBM) method which guarantees a better geometrical precision and a reduction of the gap with the ring. because of a monobloc design.
• LBM Laser Beam Melting
• the LBM process by reducing the overall volume of the supports, the surfaces to be resumed in machining, or the bulkiness on the production platform, makes it possible to obtain a significant reduction in manufacturing costs by reducing the mass (low thickness). while providing an improvement in terms of performance (cooling, lightness).
• the realization of the turbine ring assembly is continued by mounting the ring sectors 110 on the ring support structure 13.
• This mounting can be carried out ring sector by ring sector as follows .
• the first pins 119 are first placed in the orifices 13350 provided in the third portion 1335 of the first upstream flange 133, and the ring sector 110 is mounted on the first upstream flange 133 by engaging the first pins 119 in the orifices 1170.
• first ears of the upstream hooking tab 114 until the first portion 1333 of the first upstream flange 133 bears against the bearing surface 1110 of the upstream face 114a of the upstream hooking tab 114 of the sector ring 110.
• the second upstream flange 134 is then attached to the first upstream flange 133 and to the distribution element 150 present between the flaps 114 and 116 by positioning the fastening screws 163 through the orifices 13440, 13340, 154 and 158.
• the assembly comprising the ring sector 110, the flanges 133 and 134 and the distribution element 150 obtained previously is then mounted on the ring support structure 13 by inserting each second pin 120 into each of the holes 1180 seconds. ears 118 of the downstream radial tabs 116 of the ring sector 110. During this assembly, the second portion 1334 of the first upstream flange 133 is placed in abutment against the upstream annular radial flange 132.
• the assembly of the ring sector is then finalized by inserting the fastening screws 160 in the orifices 13440, 13340 still free and 1320, coaxial, and each screw is tightened in the nuts 161 secured to the ring support structure. .
• the embodiment which has just been described comprises, for each ring sector 110, two first pins 119 and two second pins 120. However, it is not beyond the scope of the invention if for each ring sector, two first pins 119 and one second pin 120 or one first pin 119 and two second pins 120 are used.
• a distribution element 150 having the same structure as that described in FIG. 1 and pins extending in the radial direction between the central ring 131 and the attachment tabs 114 and 116. in order to maintain these tabs in a radial position.
• the ends of these pieces are inserted by force in orifices made in the central ring 131 to ensure their maintenance.
• these pins could be mounted with a game in the orifices of the central ring 131 and then be welded thereafter.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Applications Claiming Priority (2)

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• 2017
  • 2017-10-19 FR FR1759843A patent/FR3072711B1/fr active Active
• 2018
  • 2018-10-16 RU RU2020116177A patent/RU2020116177A/ru unknown
  • 2018-10-16 CA CA3084342A patent/CA3084342A1/fr not_active Abandoned
  • 2018-10-16 EP EP18803746.9A patent/EP3698025A1/fr active Pending
  • 2018-10-16 WO PCT/FR2018/052577 patent/WO2019077265A1/fr unknown
  • 2018-10-16 US US16/756,736 patent/US11391178B2/en active Active
  • 2018-10-16 CN CN201880065186.5A patent/CN111201370B/zh active Active
  • 2018-10-16 BR BR112020006497-1A patent/BR112020006497A2/pt not_active Application Discontinuation
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