EP3976320A1 - Tool for mounting the high-pressure shaft of an aircraft engine - Google Patents
Tool for mounting the high-pressure shaft of an aircraft engineInfo
- Publication number
- EP3976320A1 EP3976320A1 EP20729011.5A EP20729011A EP3976320A1 EP 3976320 A1 EP3976320 A1 EP 3976320A1 EP 20729011 A EP20729011 A EP 20729011A EP 3976320 A1 EP3976320 A1 EP 3976320A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- shaft
- end cap
- shaft end
- fastening
- tool
- 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
Links
- 238000002485 combustion reaction Methods 0.000 claims description 9
- 239000004033 plastic Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 3
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 3
- 230000002265 prevention Effects 0.000 abstract 1
- 238000010276 construction Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 2
- 241000937413 Axia Species 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000007665 sagging Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- 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
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/14—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same
-
- 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
- F05D2230/00—Manufacture
- F05D2230/72—Maintenance
-
- 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
- F05D2260/02—Transport and handling during maintenance and repair
-
- 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
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
-
- 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
- F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
-
- 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
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
- F05D2300/432—PTFE [PolyTetraFluorEthylene]
Definitions
- the invention relates to a tool for holding and axially fixing the high-pressure shaft of an aircraft engine when the high-pressure turbine stage is mounted and its use.
- V2500 engine type from the manufacturer International Aero Engines (IAE).
- IAE International Aero Engines
- the high-pressure shaft is mounted on one side in a non-rotating front bearing receptacle ("Front Bearing Compartment") with a fixed bearing designed as a roller bearing, which is arranged in front of the high-pressure compressor module In the area of the combustion chamber and thus in front of the high-pressure turbine module, another roller bearing is provided as a floating bearing. If only the front bearing mount is removed - e.g. for maintenance purposes - the high-pressure shaft is axially secured by one on the high-pressure turbine module attached retainer. If only the high-pressure turbine module is removed, the axial securing takes place exclusively through the fixed bearing of the front bearing mount.
- the object of the present invention is to create a tool and a use of this tool with which the disadvantages of the prior art can be avoided or at least reduced.
- the invention relates to a tool for holding and axially fixing the hollow high-pressure shaft of an aircraft engine when the high-pressure turbine stage is dismantled, comprising a shaft end cap element with an inner radius adapted to a predetermined shaft diameter for attachment to the end of the high-pressure shaft on the turbine side, a shaft end cap holder for receiving the shaft end cap element in a radially movable manner and axially limited in a first direction,
- a connector element attachable to the shaft end cap receptacle with a shaft which can be inserted into the high pressure shaft comprising a fixing element for axia len securing of the shaft end cap receptacle, with a spring element fixed in relation to the shaft end cap receptacle for applying a predetermined spring force to the shaft end cap element in the radial direction.
- the invention also relates to a use of the tool according to the invention with the following steps: a) dismantling the high-pressure turbine stage (s) of the aircraft engine; b) plugging the shaft end cap element onto the turbine end of the high pressure shaft; c) inserting the shaft of the connector element with the Fi x michselement in the high pressure shaft; d) attaching the shaft end cap receptacle to the shaft end cap element; e) connecting the connector element with the Wellenendkap penability, so that the shaft end cap holder is axially fi xed by the fixing element of the connector element; and f) Applying a spring force to the Wellenendkappenele ment in the radial direction by the opposite of the Wel lenendkappenability fixed spring element.
- the tool according to the invention it is possible to completely secure the high-pressure shaft of an aircraft engine with the high-pressure turbine stage dismantled in the axial direction and at the same time to hold it in the radial direction via the spring element so that the weight force acting on the high-pressure shaft when the high-pressure turbine stage is installed is via the specified spring force can be simulated.
- the high-pressure shaft is not completely fixed in the radial direction, but is only loaded with a spring force corresponding to the weight force mentioned, whereby the shaft is held in the required, desired position on the one hand, but on the other hand no undesirable tensions by a Festlage tion at the rear end the high pressure wave are entered into this.
- Axial securing takes place through the interaction of the Wel lenendkappenau, which prevents movement of the high-pressure shaft with the shaft end cap element attached by the axial limitation in the first direction, in particular, for example, in the direction of the shaft end cap element, and a connected shaft with its fixing element
- Axial movement of the high-pressure wave against the shaft end cap counter to the first direction can prevent.
- the high-pressure shaft can thus be completely fixed in the axial direction with respect to the shaft end caps, while only a predetermined force is exerted in the radial direction, but the high-pressure shaft is basically at least somewhat opposite in the radial direction the shaft end cap holder can move, since in particular there is no fixed bearing in this direction.
- the spring element is adjustable with regard to the spring force.
- the spring force specified for a certain engine, a certain engine variant (that is, one of several variants of an engine type) and / or a certain engine type can be set. It may also be possible, if necessary, to readjust the spring force when the tool is mounted on a drive unit.
- the fixing element on the shaft of the connector element can in principle be designed for a non-positive connection with the inside of the hollow high-pressure shaft. But it is preferably designed for a positive connection with the high pressure shaft.
- the fixing element can interact with undercuts that are regularly present in the case of high-pressure waves of an aircraft turbine due to an inner diameter that changes in the axial direction.
- the fixing element can be arranged at the free end of the shaft to be inserted into the high-pressure shaft, around a bar extending on both sides of the shaft and preferably pivotable perpendicular to its longitudinal axis and / or to the axis of the shaft.
- the fixing element In the pivoted state, the fixing element can be inserted into the hollow high-pressure axle, while the bolt in the non-pivoted state extends maximally in the radial direction and can thus interact with a contact surface in the interior of the hollow shaft.
- an actuating device for example a wire pull, can be provided.
- the bolt has an asymmetrical weight distribution with respect to the shaft. In this case, the bolt can be moved into a vertical orientation or an orientation pivoted relative to the shaft simply by rotating the shaft.
- a fastening element is therefore preferably provided for the stationary fastening of the tool to the aircraft engine when the high-pressure turbine stage is demounted, with a fastening area for fastening the shaft end cap receptacle thereon.
- the fastening element can be designed for fastening the tool to a flange of the combustion chamber.
- the detachable attachment of the tool can be achieved, for example, with screws.
- the fastening element is preferably to be fastened to the aircraft engine in a predetermined position.
- the fastening area can preferably be designed in such a way that the tool can actually only be fastened to the engine in a single predetermined position. This can be achieved, for example, in that the fastening area and in particular the bores provided thereon for the engagement of screws are adapted to fit precisely to the intended fastening points on the engine.
- the spring element is at least is also arranged on the fastening element or attached to it, a predetermined alignment of the spring element can be achieved by appropriate proper fastening of the tool to the aircraft engine in order to be able to simulate weight forces, for example.
- the abutment and / or contact surfaces of the shaft end cap element and / or the fixing element provided for contact with the high pressure shaft are made of a softer material than the material of the high pressure shaft, preferably plastic, more preferably PTFE. In this way, damage to the high-pressure shaft when using the tool according to the invention can be effectively prevented.
- the fastening area can be precisely adapted to the respective intended fastening points of an engine type and the relative position and curvature of the shaft contact element can be precisely adapted to the high pressure wave of the engine type. This simplifies the use of a tool according to the invention, since no special engine-specific settings have to be made on the tool.
- the high-pressure turbine of an aircraft engine is demon benefits first.
- the rear end of the high pressure shaft protrudes from the engine.
- the high-pressure shaft is axially fixed by the fixed bearing of the high-pressure shaft, which is provided, for example, in a front bearing seat close to the high-pressure compressor.
- the shaft end cap element is then first placed on the turbine-side end of the high-pressure shaft and the shaft of the connector element with the fixing element is inserted into the high-pressure shaft.
- the shaft end cap holder is attached to the shaft end cap element and so connected to the shaft of the connector element when the connector element is connected to the high pressure shaft through the fixing element that the parts of the tool according to the invention mounted on the high pressure shaft are stationary in the axial direction compared to the high pressure shaft.
- the high-pressure shaft can then be fixed in the axial direction with respect to the engine by suitable fastening of the shaft end cap holder, with a certain mobility being maintained in the radial direction due to the mobility of the shaft end cap element and the shaft end cap holder.
- the spring element which is stationary with respect to the shaft end cap receptacle, however, if necessary, a predetermined spring force can be exerted in the radial direction on the shaft end cap element and thus the high pressure wave.
- the attachment of the shaft end cap receptacle can preferably be achieved by a fastening element, as described above be and which allows a fixed attachment to the engine itself.
- the Federele element is preferably not yet mounted during the fastening of the shaft end cap holder, but is only attached later.
- the fastening element is fastened to the engine with the means provided for this purpose, for example on the combustion chamber flange, in such a way that the fastening area of the fastening element is suitable for fastening the shaft end cap mount to it is arranged.
- the Wel lenendkappenfact is attached to the attachment area, preferably axially and / or radially variable, that is, the shaft end cap mount and the attachment area do not have a fixed position relative to each other, but can be connected to each other shifted axially and / or radially relative to each other.
- the connection or attachment can be made with a force fit.
- a predetermined spring force can be applied to the shaft end cap element in the radial direction via the spring element already mentioned, in particular to simulate the weight of the high pressure turbine otherwise acting on the high pressure shaft.
- the spring element can preferably be arranged on the fastening element or connected to it.
- a temporary radial support can first be attached to the high-pressure shaft in the area remote from the tool.
- Corresponding supports, which form an additional floating bearing for the high-pressure shaft, are known from the prior art and are available for a large number of different engine types.
- FIG. 1 a first exemplary embodiment of a tool according to the invention
- FIG. 2 a schematic representation of the tool according to the invention according to FIG. 1;
- FIG. 1 a first exemplary embodiment of a tool 1 according to the invention is shown, the individual components of the tool explained below being added together.
- the tool 1 is shown in the state of use
- Figure 3d finally shows a section through the tool 1 in the state of use according to Figure 2.
- Figures 2 and 3 in addition to the tool 1 or its components, parts of an aircraft engine are indicated, namely the rear end of the high pressure shaft 80 and the end area of the combustion chamber 81 with a circumferential flange 82.
- the tool 1 comprises a shaft end cap element 2, the inside diameter of which is adapted to the diameter of the turbine-side end of the high-pressure shaft of an aircraft engine for which the tool 1 is intended.
- the shaft end cap element 2 can be separated from the other components of the tool 1 and is designed so that it can be attached to the end of the high pressure shaft in question.
- the shaft end cap element 2 is arranged in a shaft end cap receptacle 3, which limits or restricts a movement of the shaft end cap element 2 in the first direction indicated by the arrow 90, but which simultaneously causes a radial movement of the shaft end cap element 2 in to a certain extent.
- the inner radius of the shaft end cap receptacle 3, which is also cap-shaped in this embodiment, is greater than the outer radius of the shaft end cap element 2.
- the fixing element 6 is, as explained below with reference to FIG. 3, for the form-fitting connection with the high-pressure shaft 80 as a bolt 8 pivotable about the axis 7, extending on both sides of the shaft 5 and having an asymmetrical weight compared to the shaft 5 having distribution. Because of this asymmetrical weight distribution, in which the center of gravity of the bolt 8 is in a vertical orientation, depending on the rotation of the shaft 5, a variable orientation below or above the axis 7, the bolt 8 either moves into the position shown in FIG axial fixation or in a ge compared to the shaft 5 angled position in which the connector element 4 can be inserted into a high-pressure shaft of an engine or removed from it again.
- a guide element 5 'made of soft plastic is also provided on the shaft 5, with which it is ensured that the shaft 5 itself does not come into contact with the inner wall of the high pressure wave 80 and can possibly cause damage there.
- the shaft end cap receptacle 3 is fastened to the fastening area 9 egg nes fastening element 10.
- the fastening area 9 is designed in the form of a sleeve or socket and is thus attached to the outer diameter of the shaft end cap receptacle 3 adapted so that it can be fastened not only axially in the fastening area 9, but also to a certain extent in the axial direction in a variable manner.
- the shaft end cap receptacle 3 has a certain amount of play with respect to the fastening area 9 before it can be fixed in the desired axial and radial position by the screws 11.
- the spring element 12 arranged, which when the shaft end cap receptacle 3 has been fixed on the fastening element 10 is stationary relative to this.
- the spring element 12 protrudes through the shaft end cap 3 and is designed to apply its spring force to the shaft end cap element 2 in the radial direction (see FIG. 3).
- the spring element 12 is on the adjusting screw
- the fastening element 2 has three arms 14 for fastening to the flange 82 of the combustion chamber 81 of an aircraft engine (see FIG. 2).
- the arms 14 are arranged and designed in such a way that the fastening element 10 can only be fastened to the aircraft engine in a predetermined position. Due to this unique position in the assembled state, it can be ensured that the spring element 12 arranged on the fastening element 10 is vertically aligned in the assembled state and can simulate a weight force of a high-pressure turbine stage otherwise acting on the turbine-side end.
- the components shaft end cap element 2 and fixing element 6 which come into direct contact with the high pressure shaft when the tool 1 is used are made entirely of plastic or at least provided with a plastic layer on the corresponding contact surfaces. Since plastic, such as PTFE, which is generally softer than the material of the high pressure shaft, can effectively prevent possible damage to the high pressure shaft.
- the high-pressure turbine stage (s) is dismantled from an aircraft engine, of which only the rear part of the high-pressure shaft 80 and the end region of the combustion chamber 81 are shown, so that the turbine-side end 84 of the high-pressure shaft 80 is exposed.
- the shaft end cap element 2 is slipped onto this exposed end 84 of the high pressure shaft 80 (FIG. 3b). Due to its inner radius adapted to the diameter of the high pressure shaft 80, the shaft end cap element 2 sits securely on the high pressure shaft 80, the cap shape ensuring that the shaft end cap element 2 actually remains on the turbine-side end 84 of the high pressure shaft 80.
- the shaft 5 of the connector element 4 is then inserted into the high-pressure shaft 80 to such an extent that the fixing element 6 is located in a region 85 of the high-pressure shaft 80 in which the shaft diameter is increased (FIG. 3c).
- the shaft 5 By appropriately rotating the shaft 5 around its longitudinal axis, due to the uneven weight distribution of the fixing element 6, which is designed as a bolt 8, an orthogonal alignment can be achieved with respect to the shaft 5, in which the fixing element 6 can no longer be pulled out by the high-pressure shaft 80, but rather a form-fitting connection binding with the undercut arising in the area 85 of the diameter enlargement of the high pressure shaft 80.
- the shaft 5 is kept away from the inner wall of the high-pressure shaft 80 by the guide element 5 ′.
- the shaft end cap receptacle 3 is attached to the shaft end cap element 2 and the connection between the shaft 5 of the connector element 4 is established (FIG. 3d).
- the already assembled components 2-4 of the tool 1 can be fixed in the axial direction relative to the high pressure shaft 80: an axial movement of the shaft end cap element 2 relative to the high pressure shaft 80 is prevented by the correspondingly limiting shaft end cap holder 3, which in turn is fixed by the bracing with the United binder element 4 in the axial direction.
- the fastening element 10 is mounted (FIG. 3e).
- the fastening element 10 is fastened via the arm 14 in the only possible position on the rear flange 82 of the combustion chamber 80, to which at least one high-pressure turbine stage is otherwise fastened.
- the shaft end cap holder 3 lies within the fastening area 9 and can be finely positioned therein until it is fixed in the desired position by the screws 11.
- the spring element 12 provided on the fastening element 10 can then be fine-tuned using the adjusting screw 13 so that a predetermined spring force is exerted on the shaft end cap element 2, which is still fundamentally movable in the radial direction, which simulates the weight of the high-pressure turbine stage (s) otherwise mounted at this point.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
- Gripping On Spindles (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102019114029.3A DE102019114029A1 (en) | 2019-05-24 | 2019-05-24 | Tool for holding the high pressure shaft of an aircraft engine |
PCT/EP2020/064253 WO2020239620A1 (en) | 2019-05-24 | 2020-05-22 | Tool for mounting the high-pressure shaft of an aircraft engine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3976320A1 true EP3976320A1 (en) | 2022-04-06 |
EP3976320B1 EP3976320B1 (en) | 2023-06-21 |
Family
ID=70918412
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20729011.5A Active EP3976320B1 (en) | 2019-05-24 | 2020-05-22 | Tool for mounting the high-pressure shaft of an aircraft engine |
Country Status (6)
Country | Link |
---|---|
US (1) | US11530624B2 (en) |
EP (1) | EP3976320B1 (en) |
CN (1) | CN113874169B (en) |
DE (1) | DE102019114029A1 (en) |
ES (1) | ES2950271T3 (en) |
WO (1) | WO2020239620A1 (en) |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2641831A (en) * | 1950-11-21 | 1953-06-16 | Helton William Henry | Sleeve puller |
US8127417B1 (en) * | 2007-02-26 | 2012-03-06 | American Airlines, Inc. | Bearing assembly removal system and method |
US8528192B2 (en) * | 2008-06-30 | 2013-09-10 | General Electric Company | Fixture for removing slip rings from rotating electrical machinery |
US8683670B2 (en) * | 2010-12-20 | 2014-04-01 | Turbine Tooling Solutions Llc | Method for partial disassembly of a bypass turbofan engine |
RU2593053C2 (en) * | 2011-02-09 | 2016-07-27 | Сименс Акциенгезелльшафт | Method of removing bearing housing with gas turbine rotor, as well as tubular shaft for continuation of rotor |
KR101451155B1 (en) * | 2013-10-11 | 2014-10-15 | 현대자동차주식회사 | Mounting structure of Drive-shaft |
CN203847444U (en) * | 2014-03-25 | 2014-09-24 | 南方风机股份有限公司 | Motor installation structure of nuclear grade high-pressure axial flow fan |
US10012082B2 (en) * | 2014-11-25 | 2018-07-03 | United Technologies Corporation | Gas turbine engine shaft members and maintenance method |
EP3067627B1 (en) * | 2015-03-12 | 2019-09-18 | Ansaldo Energia Switzerland AG | Mounting and dismounting device for a liner of a gas turbine and a related method |
US10088167B2 (en) * | 2015-06-15 | 2018-10-02 | General Electric Company | Combustion flow sleeve lifting tool |
-
2019
- 2019-05-24 DE DE102019114029.3A patent/DE102019114029A1/en not_active Ceased
-
2020
- 2020-05-22 WO PCT/EP2020/064253 patent/WO2020239620A1/en unknown
- 2020-05-22 US US17/613,497 patent/US11530624B2/en active Active
- 2020-05-22 ES ES20729011T patent/ES2950271T3/en active Active
- 2020-05-22 CN CN202080038909.XA patent/CN113874169B/en active Active
- 2020-05-22 EP EP20729011.5A patent/EP3976320B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
CN113874169A (en) | 2021-12-31 |
CN113874169B (en) | 2023-05-30 |
DE102019114029A1 (en) | 2020-11-26 |
EP3976320B1 (en) | 2023-06-21 |
US11530624B2 (en) | 2022-12-20 |
US20220243619A1 (en) | 2022-08-04 |
ES2950271T3 (en) | 2023-10-06 |
WO2020239620A1 (en) | 2020-12-03 |
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