Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/40—Casings; Connections of working fluid
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/02—Selection of particular materials
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/18—Rotors
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/26—Rotors specially for elastic fluids
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
  • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
  • B29C45/17—Component parts, details or accessories; Auxiliary operations
  • B29C45/26—Moulds
  • B29C45/263—Moulds with mould wall parts provided with fine grooves or impressions, e.g. for record discs

Definitions

• the invention relates to a turbomachine, in particular a turbomachine, preferably a fan, with at least one component that carries a flow medium, such as blades of an impeller, guide vanes, hub ring, cover ring, base plate, nozzle or housing parts-Z components, etc.
• a turbomachine in particular a turbomachine, preferably a fan, with at least one component that carries a flow medium, such as blades of an impeller, guide vanes, hub ring, cover ring, base plate, nozzle or housing parts-Z components, etc.
• the invention relates to a method for producing a component of a turbomachine that carries a flow medium.
• Turbomachines of the type in question here are well known in practice. Fans and their components are just one example.
• wall friction is a problem both in terms of noise during operation and in terms of power consumption and efficiency. It is therefore necessary to take measures to reduce wall friction.
• Riblets are raised, elongated structures on surfaces around which the fluid flows, which are advantageously aligned in the direction of the relative flow velocity in the area of the surface.
• special requirements for the cross-sections of the riblets must be met, depending on the relative flow velocities.
• the dimensions of the riblets in cross-section are rather small, for example widths, distances between neighboring riblets and heights of the riblets are advantageously in a range of 1 pm - 100 pm.
• riblets are usually arranged next to one another in order to cover a surface around which air flows. For these reasons, there is no known state of the art production suitable for large-scale production of large quantities per unit of time.
• Known production methods include applying, e.g. gluing, films provided with riblets or incorporating riblets into prefabricated components using laser processing, machining or other subsequent surface modifications.
• the present invention is based on the object of specifying a turbomachine, in particular a turbomachine, preferably a fan and its components, in which wall friction-reducing riblets can be implemented cost-effectively.
• a turbomachine in particular a turbomachine, preferably a fan and its components, in which wall friction-reducing riblets can be implemented cost-effectively.
• the use of riblets in turbomachines should be cost-effective. Above all, the production of corresponding components in turbomachines should be simple and cost-effective, depending on the relative flow speeds.
• the turbomachine according to the invention should differ from competitive products.
• the underlying object is achieved by the features of claim 1.
• the component that guides the flow medium which is important in each case, is made from plastic by casting, preferably by injection molding.
• Riblets are at least partially formed on or in and/or in the surface of the component, in each case in a flow-around and therefore relevant area, which are easily integrated into the component, namely on the basis of casting technology.
• the riblets are advantageously formed in an area of high flow losses or high wall friction losses and/or noise generation on the respective component. This measure reduces wall friction in relevant areas.
• the riblets are designed as elongated, preferably raised structures approximately parallel to the direction of flow. They can be straight or curved.
• several riblets can be arranged next to each other in an arrangement depending on the specific component, if necessary with several such arrangements, at least largely parallel to each other. If there are several rows of such riblets arranged next to each other, they can be arranged equidistant from each other.
• the arrangement of the riblets describes a circular arc or an involute curve.
• the arrangement of the riblets can otherwise be curved, with the individual riblets arranged next to one another. If necessary, two or more such arrangements can advantageously be designed approximately parallel to one another.
• all or at least the majority of the riblets are designed without undercuts in relation to the demolding direction of the tools.
• the riblets can be designed asymmetrically or non-symmetrically to a local normal on the riblet-free base surface of the respective components, which facilitates the removal of the tool in a specific demolding direction that is tailored to the component geometry or required.
• the respective component including the riblets can be demolded from a casting tool in one piece and without undercuts, namely due to the specific design of the riblets.
• the object mentioned at the outset is achieved by the features of the independent claim 11, wherein the component carrying the flow medium is equipped with riblets at least in some areas.
• the casting technology is essential, wherein the component is produced in particular by means of injection molding technology using shaping tools. Negative contours of the riblets are or are introduced into the tools. Due to the reference of the method according to the invention to the turbomachine according to the invention, the relevant features are also incorporated into the method according to the invention.
• the tool surfaces into which the negative contours of the riblets are introduced are surface-treated to obtain a low roughness or roughness depth, in particular a roughness depth of less than 10 pm, preferably less than 4 pm, before the riblet contours are introduced.
• the surfaces can in particular be ground or honed.
• an increased wall temperature of the tool is provided during production, for example at least 5 K higher than in other areas of the tool surface.
• This can be achieved, for example, by a separate cooling circuit with an increased flow temperature, or by other targeted measures relating to the tool cooling system.
• the cross-section of the riblets is designed in such a way that the wall friction-reducing effect is ensured, while at the same time the stability of the riblets on the component and the robustness of the tool against erosion or other signs of wear is high.
• the mold can be demolded without undercuts.
• Fig. 1 in perspective view from the inflow side of an impeller of an axial fan with a schematic representation of the course of riblets on air-conducting surfaces
• Fig. 2 shows a detailed schematic representation of a state of the art of riblets on the air-conducting surface of a component of a turbomachine including the associated shaping tool in a section on a plane locally approximately perpendicular to the air-conducting surface or its base area and approximately perpendicular to the longitudinal course of the riblets,
• Fig. 3 is a representation comparable to Fig. 2, wherein modified rib geometries are formed according to the invention for undercut-free demoulding,
• Fig. 4 in a plan view from the inflow side of an impeller of a radial fan with a schematic representation of the course of riblets on air-conducting surfaces
• Fig. 5 shows a plan view of a radial fan impeller from the downstream side with a schematic representation of the course of riblets on air-conducting surfaces
• Fig. 6 shows a perspective view of an axial fan housing from the inflow side with a schematic representation of the course of riblets on air-conducting surfaces.
• Fig. 1 shows a perspective view from the inflow side of an impeller 19 of an axial-type fan.
• the impeller 19 is a rotating component of a fan (not shown in full), i.e. a turbomachine and in particular a turbo-fluidmachine, and in the assembled fan is driven by a motor to which it is attached in order to convey a flow medium. It essentially consists of a hub ring 21 and blades 22 attached to it.
• the impeller 19 is a flow-around component 1 of a turbomachine, in particular a turbomachine and in particular a fan with air-conducting surfaces 13, in particular on the surfaces of the blades 22 on their suction and pressure sides, but also on the hub ring 21.
• wall shear stresses arise due to the relative speeds of the conveying medium to the surfaces around which it flows 13, which contribute to an increase in the drive power and/or a reduction in the conveying volume flow.
• a reduction in the wall shear stresses at comparable operating points, i.e. comparable relative speeds of the flow, can consequently result in a reduction in the drive power and/or an increase in the conveying volume flow and thus an increase in efficiency.
• the generation of noise can also be reduced by reducing the wall shear stresses.
• riblets 14 are now formed on the air-guiding surfaces 13 of the blades 22.
• the longitudinal course of some riblets 14 is shown schematically. Physically, a very large number are parallel and with little Distance between adjacent riblets 14 is formed; for the sake of clarity, only the course of a few riblets 14 is indicated.
• the riblets 14 run largely parallel to the relative flow on the flow-around surfaces 13 of the blades 22 from the inflow edges 27 to the outflow edges 28.
• the riblets 14 extend only over part of the blades 22 or that they only cover part of the blades 22, for example in areas with particularly high flow losses or noise generation due to wall shear stresses. It is also conceivable that riblets are formed on the flow-around surface 13 of the hub ring 21, although this is not provided for here.
• the component 1, 19 including the riblets 14 is manufactured in one piece in a casting process, advantageously in plastic injection molding. This enables high quantities to be produced.
• the negative contours of the riblets 14 are therefore introduced into the corresponding shaping surfaces of the casting tool in a suitable manner (see also description of Fig. 2 and Fig. 3).
• the impeller 19 in Fig. 1 is manufactured with a tool that consists of two essential shaping parts, among other things.
• one shaping part which mainly shapes the impeller surfaces facing the inflow side that are visible in the illustration shown, moves approximately to the left away from component 1 in demolding direction 12.
• the other shaping part of the casting tool which mainly shapes the impeller surfaces facing the outflow side that are not visible in the illustration shown, moves approximately to the right away from component 1 in a different demolding direction 12a during the demolding process. Since component 1 has a complex geometry with three-dimensionally twisted wings 22, these demolding directions are largely predetermined by this basic geometry.
• the demoulding directions cannot be adapted, or can only be adapted with great difficulty and effort, to any undercuts that may arise as a result of the Riblets 14 can arise.
• the demolding directions 12, 12a are often not parallel to the local wall normal directions of the flow-around surfaces 13, as is the case here with the inflow and outflow sides of the wings 22. Therefore, it has not been possible to form such components 1 in one casting.
• Riblets can be realized in the state of the art using special films with riblets that are applied to components, or by laser processing of components. However, these technologies do not allow for low production times or production costs and do not allow for high quantities.
• FIG. 2 shows a detailed schematic representation of a prior art of riblets 14a on the air-conducting surface 13a of a component 1a of a turbomachine including the associated shaping tool part 17a in a section on a plane locally approximately perpendicular to the air-conducting surface 13a or its base surface 23a and approximately perpendicular to the longitudinal course of the riblets 14a.
• a demolding direction 12 for a tool part 17a relative to the component 1a, the air-conducting component 1a is drawn in.
• This demolding direction 12 can be seen as a projection into the representation plane; the actual demolding direction can also have a component perpendicular to the drawing plane in three dimensions.
• the riblets 14a are each designed in cross-section approximately symmetrically to an imaginary local normal to the air-conducting surface 13a or its base surface 24a.
• the base surface 24a corresponds to the course of the air-conducting surface 13a imagined without riblets.
• the riblets 14a each have a lateral distance from the next neighboring riblet 14a (measured transversely to their longitudinal direction), measured at their center in the cross-section, namely a jump dimension, as well as a height above the base surface.
• the height above the base surface advantageously corresponds to 15% - 70% of the jump dimension.
• the riblets 14a each have two side flanks 18a that are not parallel to one another, but are at a wedge angle to one another, which is advantageously 10°-50°.
• undercuts are created on the riblets 14a on their side flanks 18a (in the illustration on the upward-facing side flanks 18a), as can be clearly seen from the hatching of the tool part 17a running parallel to the demolding direction 12 specified by the component. This is because the demolding direction 12 specified by the component 1a deviates significantly from the local wall normal directions on the flow-around surfaces 13a.
• Fig. 3 shows, in a representation comparable to Fig. 2, an embodiment of a flow-around surface 13 of a component 1 of a turbomachine provided with riblets 14, adapted according to the invention to the manufacturing process or the demolding process.
• Fig. 3 shows a detailed section of a schematic representation of a flow-around component 1 with riblets 14 on the air-guiding surface 13 of a component 1 of a turbomachine including the associated shaping tool part 17 in a section on a plane locally approximately perpendicular to the air-guiding surface 13 or its base area 23 and approximately perpendicular to the longitudinal course of the riblets 14.
• a demolding direction 12 for a tool part 17 relative to the component 1, the air-guiding component 1, is drawn in.
• This demolding direction 12 can be seen as a projection into the representation plane; the actual demolding direction can additionally have a component perpendicular to the drawing plane in three-dimensional form.
• modified riblet geometries are designed compared to the prior art according to Fig. 2, which essentially correspond to the nor have the function of reducing wall friction during operation of the turbomachine.
• the riblets 14, in particular their cross section are now modified to take into account the demolding direction 12 specified by the component 1.
• the riblets 14, in a cross section such as that shown in Fig. 3 are not symmetrical to imaginary local normals to the air-guiding surface 13 or its base area 23.
• the two side flanks 18 of the respective riblets 14 are not symmetrical to an imaginary local normal to the air-guiding surface 13 or its base area 23.
• the shaping tool part 17 has the negative shape of the component 1 provided with riblets 14, the component 1 around which the flow occurs, whereby the aforementioned design features of the riblets 14 are also found on the tool part 17.
• the course of the side flanks 18 is, in cross section, adapted to the demolding direction 12 in such a way that the riblets 14 can be demolded in the demolding direction 12 essentially without undercuts.
• the ability to be demolded without undercuts can be easily verified in Fig. 3 using the hatching of the section through the tool part 17, which is executed parallel to the (projected) demolding direction 12.
• the riblets 14 are not damaged or destroyed during the demolding process.
• the riblets 14 each have a lateral distance from the next adjacent riblet 14 (measured transversely to their longitudinal direction) measured at their center in the cross section, namely a step dimension, as well as a height above the base area.
• the height above the base area advantageously corresponds to 15% - 70% of the step dimension.
• the riblets 14 each have two side flanks 18 that are not parallel to each other, but are at a wedge angle to each other, which is advantageously 10°-50°.
• upper end faces 24 are formed on the riblets 14, which are advantageous for the stability and durability of the riblets 14.
• the width of the end faces 24 of the riblets 14, seen in cross section, is advantageously in a range of approximately 30 - 200% of the height of the riblet 14 in question.
• Embodiments without end faces 24 are also conceivable, for example if the riblets or their side flanks merge into one another at their outer ends in a pointed manner or with a rounded portion.
• pronounced outer edges 20 are provided at the transition from the side flanks 18 to the end faces 24.
• pronounced inner edges 29 are designed at the transition of the side flanks 18 to the base surface 23.
• the rounding increases the stability of the component 1 or the riblets 14 on it and of the shaping tool part 17, and reduces wear during production but also during operation of the fluid-flow machine with the air-conducting component 1 with the riblets 14.
• the radius of curvature for possible rounding of the outer edges 20 or the inner edges 29 is advantageously in a range of a maximum of 30% of the height of the respective riblets 14.
• the areas of the inner edges 29 are rounded, following the example of tree trunks with a variable radius of curvature.
• the radii of curvature at the transition to the base surface 23 are smaller than at the transition to the side flank 18, advantageously by a factor of at least 1.4.
• the flow-around component 1 including the riblets 14 can be demolded from a casting tool in one piece and without undercuts.
• the riblets 14 are not damaged or destroyed during demolding.
• Components 1 can be manufactured cost-effectively in large quantities.
• suitable process parameters and materials must be selected in the case of plastic injection molding of thermoplastic plastic, which can also be provided with reinforcing fibers. It is advantageous to use materials that flow well and well-heated tool surfaces in the area of the riblets 14.
• the holding pressure time should be rather long and the holding pressure rather high.
• tool areas that mold riblets can advantageously be at least partially heated to a higher temperature in the injection molding process than other tool areas that do not mold riblets locally, by at least 10 K.
• the demolding direction 12 shown in Fig. 3 is to be understood as a projection into the representation plane.
• the actual three-dimensional demolding direction can therefore also have a component perpendicular to the representation plane.
• this component running perpendicular to the representation plane would lie parallel to the longitudinal course of the riblets 14.
• this directional component of the demolding direction running perpendicular to the representation plane would be irrelevant with regard to the occurrence of possible undercuts.
• the special measures on the riblets 14, which ensure the undercut-free demoldability, in particular the asymmetrical design of the two side flanks 18 of a riblet 14 to one another, are necessary in particular in those areas of a flow-around surface 13 of a flow-around component 1 when the angle that the demolding direction 12 projected into the drawing plane according to Fig. 3 forms with the local wall normal to the base surface 23 is greater than 20°, in particular greater than 45°, i.e. when the projected demolding direction is not parallel to the local wall normal to the base surface 23.
• This is typically the case with a significant proportion of the flow-guiding surfaces 13 of a flow-around component 1 provided with riblets 14, for example with more than 25% or with more than 50% of the flow-around surfaces.
• Fig. 4 shows a planar view of an impeller 19 of a radial fan, seen from the inflow side, with a schematically illustrated course of riblets 14 on air-conducting surfaces 13.
• the impeller 19 in the exemplary embodiment has a radial design and consists in particular of a hub ring 21 (in the case of radial impellers also referred to as the base plate), a cover ring 16 and wings 22 extending between them.
• the impeller 19 When the radial fan is in operation, the impeller 19 rotates about the central axis of symmetry and conveys a conveying medium in a conveying direction approximately from the inflow edges 27 of the blades 22 to the outflow edges 28 (Fig. 5). The conveying medium enters the impeller 19 through the central opening in the cover ring 16 and is conveyed radially outwards.
• the impeller 19 is a flow-around component 1 of a turbo machine, in this case a fan.
• the reduction of the wall shear stresses with the help of riblets 14 on flow-around surfaces 13 serves to reduce the drive torque and/or increase the conveying volume flow and thus increase the efficiency. This can also reduce the noise generated during operation.
• riblets 14 are schematically attached to various flow-guiding surfaces 13 as an example.
• riblets 14 run closely spaced apart on surfaces 13 around which the flow occurs.
• surfaces 13 around which the flow occurs occur on the visible outside of the cover ring 16; there, the relative flow velocity runs approximately in the circumferential direction, which is why the riblets 14 run in the circumferential direction.
• the relative demolding direction of a tool part demolding the outside of the cover ring 16 would normally be approximately perpendicular to the plane of the illustration.
• the demolding direction is not always perpendicular to the base area of the outside of the cover ring 16, and the riblets 14 are designed in accordance with the invention in accordance with Fig. 4 in some areas where necessary in order to avoid undercuts.
• Riblets 14 are also attached to the inner surface of the hub ring 21 visible in Fig. 4, which is also a flow-around surface 13, and are aligned in the relative overflow direction to be expected there.
• the hub ring 21 or its base surface is also usually not flat and not parallel to the plane of representation, but rather as a conical rotational body, for example, which is why the expected demoulding direction of the moulded frequently does not run perpendicular to the base surface around which the air flows and also not parallel to the course of the riblets 14, which is why the geometric design of the riblets 14 is adapted in accordance with the description in Fig. 4 in order to avoid undercuts.
• the situation is very similar with the riblets 14 which are designed on the surfaces 13 of the wings 22 around which the air flows.
• Fig. 5 shows a planar view from the downstream side of an impeller 19 as a flow-around component 1 of a radial fan similar to that shown in Fig. 4.
• Riblets 14 are attached to the visible outside of the hub ring 21, a flow-around surface 13.
• the hub ring 21 or its base surface is advantageously not flat.
• the riblets 14 run on the outer surface of the hub ring 21 approximately in the circumferential direction.
• the riblets 14 are designed according to Fig.
• Impellers 19 are components that rotate and transmit power during operation. The reduction of a wall shear stress of an impeller 19 in the circumferential direction leads to a reduction in the loss torque. In a turbomachine in which power is transferred from the impeller to the fluid, the required drive torque and thus the required drive power are reduced. In a turbomachine in which power is transferred from the fluid to the impeller, the effective drive torque transferred to the impeller and the transferred drive power are increased by reducing the loss torque.
• a perspective view of a housing 2 of an axial fan is shown from the inflow side with a schematic representation of the course of riblets on air-conducting surfaces 13.
• a housing is a stationary, non-driven component and wall shear stresses do not contribute to drive torques or drive power. Nevertheless, the reduction of wall shear stresses can contribute to an increase in the volume flow and thus to an increase in efficiency, and also to an improvement in the acoustic performance.
• the housing 2 is a flow-around component 1 of a turbomachine.
• the housing consists of an outer ring 4, comprising in particular an integrated inlet nozzle 9, a running area for an impeller (not shown) and a diffuser area within which an integrated guide device 15 is arranged.
• the guide device 15 comprises outer strut elements 3a, a circumferential intermediate ring 5, inner guide elements 3 and a hub ring 10.
• a motor (not shown) with the impeller of a fan can be attached to the hub ring, and the guide device 15 connects the outer ring 4 of the housing 2 to the hub ring 10 and in this way holds the motor with the impeller in relation to the outer ring 4, to which the housing 2 can be attached to a higher-level system.
• an impeller runs inside the housing 2 or its outer ring 4 on the inflow side of the guide device 15 and, driven by a motor, conveys the conveying medium in the conveying direction approximately from left to right, which enters the housing at the inlet nozzle 9. 2 and exits the housing 2 again after the guide device 15.
• the attachment of riblets 14 with a suitable geometric design can minimize wall friction and thus flow losses and contribute to increasing the efficiency and reducing noise emissions.
• the riblets 14 are designed as shown in Fig. 4 and, where necessary, their cross-section is adjusted to ensure demolding without undercuts.
• the longitudinal direction of the riblets 14, which is indicated in the illustration according to Fig. 6 based on the course of a few exemplary riblets 14, is advantageously always selected approximately parallel to the local relative flow velocity with respect to the flow-around surface 13.
• the relative demolding directions of the shaping tool parts are predominantly aligned parallel to the central axis of the component.
• the riblets 14 on the inner contour of the inlet nozzle 9 have no circumferential component in their longitudinal course, corresponding to the overflow direction of the corresponding flow-around surface 13 to be expected there. It is therefore possible and advantageous to realize riblet cross-sections symmetrical to the local wall normal, without obtaining undercuts when demolding the housing 2 with a demolding direction parallel to the housing axis. This is because in a section on a plane perpendicular to the longitudinal course of the riblets 14 and perpendicular to the local base area of the flow-guiding surface 13 there according to Fig. 4, there would be no undercut between the (projected) demolding direction and the riblets 14.
• a component 1, i.e. a component 1 around which the flow is carried out has symmetrical ribbed cross-sections in relation to the local wall normal in cross-section, as long as it is possible to do so locally without undercuts while maintaining effective ribbed cross-sections due to the demoulding directions, and everywhere asymmetrical ric rib cross-sections, where it is necessary due to the demoulding direction in order to ensure undercut-free demoulding.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

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• 2022
  • 2022-12-16 DE DE102022213765.5A patent/DE102022213765A1/de active Pending
• 2023
  • 2023-12-05 JP JP2025534416A patent/JP2025539577A/ja active Pending
  • 2023-12-05 CN CN202380085736.0A patent/CN120359355A/zh active Pending
  • 2023-12-05 WO PCT/DE2023/200244 patent/WO2024125734A1/de not_active Ceased
  • 2023-12-05 EP EP23837167.8A patent/EP4453434A1/de active Pending

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