WO2021013964A1 - Extruded wing-tube portion, wing tube comprising an extruded wing-tube portion, and heat exchanger comprising a wing tube, and method for producing a wing-tube portion - Google Patents
Extruded wing-tube portion, wing tube comprising an extruded wing-tube portion, and heat exchanger comprising a wing tube, and method for producing a wing-tube portion Download PDFInfo
- Publication number
- WO2021013964A1 WO2021013964A1 PCT/EP2020/070876 EP2020070876W WO2021013964A1 WO 2021013964 A1 WO2021013964 A1 WO 2021013964A1 EP 2020070876 W EP2020070876 W EP 2020070876W WO 2021013964 A1 WO2021013964 A1 WO 2021013964A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- wing
- section
- tube
- area
- extruded
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F1/00—Tubular elements; Assemblies of tubular elements
- F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
- F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
- F28F1/14—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally
- F28F1/16—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending longitudinally the means being integral with the element, e.g. formed by extrusion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F1/00—Tubular elements; Assemblies of tubular elements
- F28F1/10—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses
- F28F1/12—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element
- F28F1/34—Tubular elements and assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending obliquely
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F2255/00—Heat exchanger elements made of materials having special features or resulting from particular manufacturing processes
- F28F2255/16—Heat exchanger elements made of materials having special features or resulting from particular manufacturing processes extruded
Definitions
- Extruded wing tube section Extruded wing tube section, wing tube with extruded wing tube section and heat exchanger with wing tube and manufacturing method of a wing tube section
- the present invention relates to an extruded wing tube section consisting of a shaped tube area with at least one wing section integrally formed thereon, a wing tube with at least two extruded wing tube sections and a heat exchanger with wing tube.
- the present invention also relates to a method of manufacturing an extruded wing tube section.
- Wing tubes used in a heat exchanger are known in the art.
- WO 2009/068979 A1 describes a heat transfer tube for evaporators or condensers of heating and cooling units.
- the heat transfer tube has on the outside at least one axially extending and wing-like enlarged heat transfer surface, which is formed from the material of the tube or is connected to the heat transfer tube by metal.
- the heat exchanger comprises a plurality of tubes which are arranged transversely to an air flow direction through the heat exchanger and in a plurality of rows of tubes which extend along the air flow direction.
- the heat exchanger comprises a plurality of tracks that are integrally formed with two or more tubes of the plurality of tubes, each track being between adjacent tubes of the extends a plurality of tubes and is connected to these.
- At least one of the plurality of tubes has a cross section with an aspect ratio of more than 1: 1 relative to a horizontal web.
- WO 2013/139507 A1 describes a heat exchanger for removing heat from a medium with at least one serpentine-shaped wing tube arranged in a housing.
- the straight wing sections of the wing tube are arranged in such a way that the wings of the wing sections form an angle in the range of
- the object of the present invention is to provide a heat exchanger with a wing tube, an associated wing tube and a corresponding wing tube section, which are improved compared to the prior art in terms of heat dissipation and the dissipation of the condensate that forms when used.
- an extruded wing tube section consisting of a shaped tube area with at least one wing section integrally formed thereon according to independent claim 1, a wing tube with at least two extruded wing tube sections according to independent claim 12, a heat exchanger with wing tube according to independent claim 13 and a manufacturing method of an extruded wing tube section according to the independent patent claim 14.
- An extruded wing tube section consists of a molded tube region with at least one first wing section formed integrally thereon in a first radial plane of the tube region, the first wing section having a plurality of first radial incisions, so that a plurality of first wings are present in the first wing section, and each of the first wings is rotated about a radial axis of rotation, so that each of the first wings is rotated out of the first radial plane by a first angle 0 ° ⁇ a 1 ⁇ 90 °, with a first continuous overlap between the tube area and each of the first wings.
- Gang area is present, which has a twisted area in the area of the axis of rotation and at least one expansion area adjacent thereto.
- a wing tube section is extruded in the usual way, as is also the case, for example, in WO
- the first wing section does not have a gap with a connection to the pipe area.
- the first wing section is therefore preferably solid, i.e. not hollow.
- the extruded wing tube section consists of the molded tube region with at least one first wing section integrally formed thereon in a first radial plane.
- a plurality of first radial incisions is now provided in the first wing section.
- the first radial incisions are thus made in the first radial plane transversely or perpendicularly to the longitudinal direction of the pipe area.
- the first incisions preferably do not extend as far as the tube area. Rather, it is preferred that the incisions are made in at most 99% of the extent of the first wing section in the radial plane, preferably at most 97.5% and more preferably at most 95%. If the extension of the first wing section in the first radial plane is 20 mm, for example, then this means that the first incisions extend over a maximum of 19.8 mm, preferably a maximum of 19.5 mm and particularly preferably a maximum of 19 mm.
- a first wing section remains with an extension in the first radial plane, which measures 0.2 mm, preferably 0.5 mm and more preferably 1 mm.
- the first wing section has a plurality of first wings.
- Each of the first blades is rotated by the first angle a 1 about a radial axis of rotation, so that it is rotated out of the radial plane. Therefore, the radial axis of rotation of the respective first wing runs perpendicular to the longitudinal axis of the pipe area and lies in the first radial plane.
- the first angle a 1 0 ° ⁇ a 1 ⁇ 90 ° applies.
- the value of 0 ° is excluded, as otherwise there would be no rotation from the first radial plane. Values over 90 ° are excluded due to the risk of the respective first sash being severed by the rotation.
- the forces resulting from the twisting are absorbed in the first continuous transition area between each of the plurality of first blades and the tube area.
- the first continuous transition area is thus deformed and absorbs the forces that occur when the respective first wing is rotated while maintaining a connection to the pipe area.
- the deformation of the respective first continuous transition area takes place in at least two areas, namely in a first area that is twisted and in at least one further area that is stretched. This is explained below using two examples.
- the radial axis of rotation about which the respective first wing is rotated can be arranged at different positions in relation to the width of the first wing.
- width denotes the extension of the respective first wing in the first radial plane along the longitudinal axis of the tube area.
- the respective first wing has the first area, ie the twisted area, after the rotation. If the axis of rotation is directly adjacent to the incision in the respective first wing, exactly one expansion area results adjacent to the twisted area. If, in an alternative example, the axis of rotation does not run directly adjacent to the incision but, for example, centrally through the respective first wing, two expansion areas result, each of which is adjacent to the twisted area.
- the positioning of the radial axis of rotation in relation to the respective first wing is therefore selected in particular as a function of the desired first angle a 1 and thus of the later desired application.
- a technical effect and thus an advantage of this extruded wing tube section is that, due to the first incisions, the surface available for heat exchange is increased in comparison to a wing section without incisions.
- the specific arrangement of the first wings provides aerodynamic elements that increase the turbulence in the air flow, which in turn leads to an improved heat transfer coefficient.
- a wing tube section with a continuous flat wing section ie a single wing arranged exclusively in the radial plane, increases in performance in the range of approximately 15 to 30% can be achieved.
- no additional material is required for fastening individual wings to the raw area, since the wing section is already present when the wing tube is produced by means of extrusion.
- the first angle a 1 is between 30 ° and 60 °, preferably 45 °.
- this angular range in addition to the above technical effects, also contributes to a particularly efficient removal of condensate that occurs in the wing section or the respective wing.
- the condensate that forms during operation can be discharged more reliably compared to the provision of recesses in a continuous wing section directly adjacent to the
- the extruded wing tube section consists of aluminum.
- Aluminum in particular as the material for the extruded wing tube section leads to good deformability of the first continuous transition area, so that the first continuous transition area preferably has the same width as the respective first wing, i.e. preferably no cracks.
- the first continuous transition area is preferably completely connected to the raw area on the one hand and the respective wing on the other. In this way, the heat dissipation can be further improved.
- an outer diameter of the pipe area extending straight is between 3 and 10 mm and / or a wall thickness in the pipe area is 0.3 to 0.9 mm.
- the first wing section has an extension in the radial direction between 10 and 20 mm and / or each of the first incisions has a width of 3 to 8 mm. On the one hand, this provides a large area of application for the extruded wing tube section. On the other hand, it is also possible to maintain the technical effects listed above in different areas of application.
- the radial extension of the first wing section is preferably defined as a distance between the rotationally symmetrical longitudinal axis of the tube section and the radial outside of the first wing.
- the first continuous transition area comprises two expansion areas on opposite sides in relation to the twisted area.
- the axis of rotation does not run directly adjacent to the incision but, for example, centrally through the respective first wing based on the width of the first wing.
- the Axis of rotation at any other position through the first wing, with the exception of the locations immediately adjacent to the respective first incision. This results in two expansion areas, each of which is adjacent to the twisted area.
- the configuration in which the axis of rotation runs centrally through the respective first wing is particularly preferred.
- the extruded wing tube section further comprises a second wing section formed integrally on the tube area in a second radial plane of the tube area, the second wing section having a plurality of second radial incisions, so that a plurality of second wings are present in the second wing section, each of the second blades is rotated about a radial axis of rotation so that each of the second blades is rotated out of the second radial plane by a second angle 0 ° ⁇ a 2 ⁇ 90 °, with a second continuous transition area being present between the tube area and every second blade, which has a twisted area in the area of the axis of rotation and at least one expansion area adjacent to it.
- a second wing section is introduced by means of this configuration. This further intensifies the effects caused by the wings designed according to the invention, so that with regard to the resulting technical effects and advantages, reference is made to the above statements on the first wing section with the plurality of first wings.
- the statements relating to the first wing section and the associated first wing apply analogously to the second wing section and every further possible wing section.
- the second wing section is arranged opposite the first wing section on the straight tube section so that the first radial plane and the second radial plane form a common plane in which the longitudinal axis of the tube area lies.
- the first angle a 1 and the second angle a 2 are the same.
- This configuration further strengthens the technical effects achieved with the extruded wing tube section, in particular due to the synergy effects of the first and second wing sections.
- the second wing section has an extension in the radial direction between 10 and 20 mm and / or each of the second incisions has a width of 3 to 8 mm.
- the second continuous transition area comprises two expansion areas on opposite sides in relation to the twisted area.
- the radial extension of the first wing section is preferably defined as a distance between the rotationally symmetrical longitudinal axis of the tube section and the radial outside of the first wing.
- a distance AF between the wing tips of two wings arranged opposite one another is in a range of 20 mm ⁇ Ai ⁇ 40 mm.
- the respective wings are rotated in the same direction or in opposite directions out of the radial plane. In other words, the wings of a wing section are rotated in a first direction of rotation.
- the wings of the second wing section are rotated either in the same direction or in the opposite direction.
- the wing tube section can be further adapted to the desired application.
- the blades of a blade section are rotated alternately in opposite directions of rotation, for example, or all blades of a blade section have the same direction of rotation.
- a wing tube according to the invention for a heat exchanger in particular an evaporator or a condenser, comprises at least two extruded wing tube sections according to the invention, the longitudinal axes of which run parallel to one another and which are connected to one another by means of a wingless curved section. Since the wing tube has the extruded wing tube section according to the invention, reference is made to the above statements with regard to the resulting technical effects and advantages in order to avoid repetition.
- a heat exchanger according to the invention comprises a wing tube according to the invention.
- the heat exchanger is preferably an evaporator or condenser with a wing tube according to the invention.
- the wing tube section consisting of the tube area and at least one first wing section formed integrally thereon is extruded. If the wing tube section is later to have both a plurality of first wings and a plurality of second wings, the wing tube section is additionally extruded with a second wing section formed integrally thereon. This also applies to other possible wing sections.
- the wing tube section After the extrusion of the wing tube section, it thus has a first radial plane and a longitudinal axis defined by the tube area, which lies in the radial plane.
- the first wing section, as well as possible further wing sections, are thus designed to be planar and extend radially outward from the tube area.
- the plurality of radial incisions is made transversely to the longitudinal axis of the pipe area in the respective wing section, so that a plurality of first wings is created in relation to the first wing section. Due to the plurality of incisions, the surface of the respective wing section is already enlarged. Simultaneously with or after the
- the incisions are made by twisting at least one wing out of the plurality of first wings out of the radial plane.
- a continuous transition area present between the respective wing and the pipe area is deformed and absorbs the forces that arise when the wing is rotated while maintaining a connection to the pipe area.
- the continuous transition area therefore comprises a twisted area in the area of the axis of rotation and at least one expansion area, depending on the positioning of the axis of rotation in relation to the width of the respective wing.
- Figure 1 is a perspective view of an extruded wing tube section
- FIG. 2 shows a first perspective view of an extruded wing tube section according to an embodiment of the present invention
- FIG. 3 shows a side view of the extruded wing tube section according to an embodiment of the present invention
- FIG. 4 shows a second perspective view of the extruded wing tube section according to an embodiment of the present invention
- FIG. 5 shows a third perspective view of the extruded wing tube section according to an embodiment of the present invention
- FIG. 6 shows a fourth perspective view of the extruded wing tube section according to an embodiment of the present invention
- FIG. 7 shows a fifth perspective view of the extruded wing tube section according to an embodiment of the present invention.
- FIG. 8 shows a flow diagram of an embodiment of a production method according to the invention for an extruded wing tube section.
- extruded wing tube section can be part of a Be wing tube and is used in heat exchangers, such as an evaporator or condenser.
- an extruded wing tube section 1 is shown. This has a tube area 3 as well as a first 5 and a second wing section 7 and was extruded in the usual way, as also described, for example, in WO 2009/068979 A1 with reference to FIG.
- the first 5 and the second wing section 7 are solid, i.e. not hollow.
- the extruded wing tube section 1 thus consists of the shaped tube region 3 with a first wing section 5 integrally formed thereon in a first radial plane and a second wing section 7 integrally formed thereon in a second radial plane.
- the straight pipe region 3 defines a longitudinal axis.
- the second wing section 7 is arranged on the side of the tube region 3 opposite the first wing section 5. Therefore, the first and the second radial plane form a common plane in which the longitudinal axis of the tube region 3 runs.
- An outer diameter of the pipe region 12 extending straight is between 3 and 10 mm and / or the wall thickness in the pipe region 12 is 0.3 to 0.9 mm.
- the outside diameter and the wall thickness depend on the desired area of application, for example whether it is to be used in the context of an evaporator or condenser.
- a plurality of first radial incisions was provided in the first wing section 20 of the extruded wing tube section 10. Accordingly, a plurality of second radial incisions was provided in the second wing section 30 of the extruded wing tube section 10.
- the first and the second radial incisions can be made on opposite sides with respect to the tube region 12 simultaneously or one after the other.
- a first incision in the first wing section 20 can be made at the same time as a second incision in the second wing section 30.
- a desired number of first incisions in the first wing section 20 and then a desired number of second incisions in the second wing section 30 is provided.
- Each incision has a width of 3 to 8 mm and ensures an enlargement of the surface that flows against during operation and is thus available for heat exchange compared to a wing section without incisions.
- Straight incisions with a width of 3 to 8 mm have been identified as particularly advantageous.
- Both wing sections 20, 30 each have a preferred extension in the radial direction between 10 and 20 mm.
- a radial extension in this direction is also referred to as the radial length of the wing sections 20, 30, which is measured between the rotationally symmetrical center point of the tube section and the radial outside or tip of the wing.
- the radial incisions are thus made in the respective radial plane transversely or perpendicular to the longitudinal direction of the tube area 12.
- the respective incisions preferably do not extend to the tube area 12, but at most over 99% of the respective wing section 20, 30 in the radial plane.
- each wing section 20, 30 has a plurality of wings 22, 32.
- Each wing 22, 32 is rotated by an angle a 1 , a 2 about a radial axis of rotation, so that it is rotated out of the radial plane.
- the radial axis of rotation of the respective vane 22, 32 therefore runs perpendicular to the longitudinal axis of the tube region 12 and lies in the radial plane.
- angles a 1 , a 2 , 0 ° ⁇ a 1 , a 2 ⁇ 90 ° applies.
- the value of 0 ° is excluded, as otherwise there would be no rotation from the radial plane, and values over 90 ° are due the risk of the respective wing being severed by the rotation is excluded.
- the angles a 1 , a 2 are 45 °.
- angles between 30 ° and 60 ° are generally preferred, since it is precisely this angle range that contributes to a particularly efficient removal of condensate arising in the wing section 20, 30 or the respective wing 22, 32.
- the condensate that forms during operation can be discharged more reliably compared to the provision of recesses in a continuous wing section immediately adjacent to the pipe area.
- the specific arrangement of the wings provides aerodynamic elements that increase the turbulence in the air flow, which in turn leads to an improved heat transfer coefficient.
- the forces resulting from the rotation are absorbed in the first continuous transition area between each of the plurality of blades 22, 32 and the tube area.
- the continuous transition area is thus deformed and absorbs the forces that occur when the respective wing 22, 32 is rotated while maintaining a connection to the pipe area 12.
- the deformation of the respective continuous transition area takes place in at least two areas, namely in a first area that is twisted and in at least one further area that is stretched.
- the respective axis of rotation does not run directly adjacent to the incision but rather centrally through the respective wing.
- the term central refers to a width of the wing 22, 32, i.e. to the extent of the respective wing in the radial plane along the longitudinal axis of the pipe region 12. This results in two expansion regions, each of which is adjacent to a twisted region. The twisted area is present in the area of the axis of rotation of the respective wing 22, 32 after the wing 22, 32 has been rotated.
- the axis of rotation is arranged directly adjacent to the incision. In this case, there is exactly one stretch area adjacent to the twisted area.
- the positioning of the axis of rotation in relation to the respective wing 22, 32 is therefore selected in particular as a function of the desired angle a 1 , a 2 and thus the later desired application.
- the respective wings 22, 32 can be rotated in the same direction or in opposite directions out of the radial plane.
- the respective direction of rotation depends in particular on the later application.
- the blades 22, 32 were rotated in the same direction.
- wings in the same wing section can also have a twist in opposite directions of rotation.
- Aluminum is used as the material for the extruded wing tube section 10.
- Aluminum in particular leads to good deformability of the continuous transition area, so that preferably the continuous transition area has the same width as possible as the respective wing 22, 32, i.e. preferably no cracks.
- the continuous transition area is preferably completely connected to the raw area 12 on the one hand and the respective wing 22, 32 on the other hand, so that the heat dissipation can be further improved, in particular compared to an only punctiform connection between the wing 22, 32 and the pipe area
- a non-illustrated embodiment of a wing tube according to the invention for a heat exchanger, in particular for an evaporator or a condenser, comprises at least two wing tube sections 10 according to FIGS. 2 to 7, whose longitudinal axes run parallel to one another and which are connected to one another by means of a wingless curved section.
- An embodiment of a heat exchanger according to the invention comprises the embodiment of the wing tube described above.
- the heat exchanger is preferably an evaporator or condenser.
- a flow chart of an embodiment of a production method according to the invention for the extruded wing tube section 10 is briefly explained.
- a first step A the wing tube section 10 consisting of the tube region 12 and the two wing sections 20, 30 formed integrally thereon is extruded.
- each wing section 20, 30 is thus designed to be planar and extends radially outward from the tube region 12 on opposite sides.
- the plurality of incisions is made transversely to the longitudinal axis of the pipe region 12 in the respective wing section 20, 30, so that a plurality of wings 22, 32 is produced. Due to the plurality of incisions, the surface of the respective wing section 20, 30 is already enlarged.
- a wing 22, 32 from the plurality of wings 22, 32 is rotated in step C.
- the continuous transition area between the respective wing 22, 32 and the tube area 12 is deformed and expanded the forces arising when the wing 22, 32 is rotated while maintaining the connection to the pipe area 12.
- the continuous transition area therefore comprises a twisted area in the area of the axis of rotation and at least one expansion area, depending on the positioning of the axis of rotation in relation to the width of the respective wing 22, 32.
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Geometry (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
- Extrusion Of Metal (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US17/628,705 US20230016139A1 (en) | 2019-07-23 | 2020-07-23 | Extruded wing tube portion, wing tube comprising an extruded wing-tube portion, and heat exchanger comprising a wing tube, and method for producing a wing-tube portion |
EP20745198.0A EP3994410A1 (en) | 2019-07-23 | 2020-07-23 | Extruded wing-tube portion, wing tube comprising an extruded wing-tube portion, and heat exchanger comprising a wing tube, and method for producing a wing-tube portion |
BR112022001146A BR112022001146A2 (en) | 2019-07-23 | 2020-07-23 | Extruded wing-shaped tube section, wing-shaped tube with extruded wing-shaped tube section and wing-shaped tube heat exchanger as well as manufacturing process of a wing-shaped tube section |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE202019104073.4U DE202019104073U1 (en) | 2019-07-23 | 2019-07-23 | Extruded wing tube section, wing tube with extruded wing tube section and heat exchanger with wing tube |
DE202019104073.4 | 2019-07-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2021013964A1 true WO2021013964A1 (en) | 2021-01-28 |
Family
ID=71784071
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2020/070876 WO2021013964A1 (en) | 2019-07-23 | 2020-07-23 | Extruded wing-tube portion, wing tube comprising an extruded wing-tube portion, and heat exchanger comprising a wing tube, and method for producing a wing-tube portion |
Country Status (5)
Country | Link |
---|---|
US (1) | US20230016139A1 (en) |
EP (1) | EP3994410A1 (en) |
BR (1) | BR112022001146A2 (en) |
DE (1) | DE202019104073U1 (en) |
WO (1) | WO2021013964A1 (en) |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS498625B1 (en) * | 1969-07-14 | 1974-02-27 | ||
WO2009068979A1 (en) | 2007-11-30 | 2009-06-04 | Bundy Refrigeration Gmbh | Heat transfer tube |
WO2012142070A1 (en) | 2011-04-14 | 2012-10-18 | Carrier Corporation | Heat exchanger |
WO2012172716A1 (en) * | 2011-06-16 | 2012-12-20 | 日本軽金属株式会社 | Drainage structure for corrugated-fin heat exchanger |
WO2013139507A1 (en) | 2012-03-19 | 2013-09-26 | Bundy Refrigeration International Holding B.V. | Heat exchanger, method for producing same and various systems having such a heat exchanger |
WO2014103268A1 (en) * | 2012-12-26 | 2014-07-03 | 日本軽金属株式会社 | Heat exchange tube in heat exchanger and method for producing heat exchange tube |
WO2018059443A1 (en) * | 2016-09-28 | 2018-04-05 | 丹佛斯微通道换热器(嘉兴)有限公司 | Heat exchange assembly for heat exchanger, heat exchanger, and mold |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
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US3333317A (en) * | 1964-03-12 | 1967-08-01 | Reynolds Metals Co | Method for making a heat exchanger means |
FR1416647A (en) * | 1964-11-04 | 1965-11-05 | Reynolds Metals Co | Heat exchangers and process for their manufacture |
US3457756A (en) * | 1967-10-12 | 1969-07-29 | Gen Electric | Finned heat exchanger tubing and method of manufacture thereof |
JPS555245A (en) * | 1978-06-24 | 1980-01-16 | Sumitomo Light Metal Ind Ltd | Method and device of manufacturing heat exchanging tube |
JP6016212B2 (en) * | 2012-10-16 | 2016-10-26 | 日本軽金属株式会社 | Corrugated fin heat exchanger drainage structure |
EP3491323B1 (en) * | 2016-08-08 | 2024-04-17 | Grandholm Production Services Ltd. | Heat exchanger having a micro-channel structure or wing tube structure |
-
2019
- 2019-07-23 DE DE202019104073.4U patent/DE202019104073U1/en active Active
-
2020
- 2020-07-23 EP EP20745198.0A patent/EP3994410A1/en active Pending
- 2020-07-23 US US17/628,705 patent/US20230016139A1/en active Pending
- 2020-07-23 BR BR112022001146A patent/BR112022001146A2/en unknown
- 2020-07-23 WO PCT/EP2020/070876 patent/WO2021013964A1/en unknown
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS498625B1 (en) * | 1969-07-14 | 1974-02-27 | ||
WO2009068979A1 (en) | 2007-11-30 | 2009-06-04 | Bundy Refrigeration Gmbh | Heat transfer tube |
WO2012142070A1 (en) | 2011-04-14 | 2012-10-18 | Carrier Corporation | Heat exchanger |
WO2012172716A1 (en) * | 2011-06-16 | 2012-12-20 | 日本軽金属株式会社 | Drainage structure for corrugated-fin heat exchanger |
WO2013139507A1 (en) | 2012-03-19 | 2013-09-26 | Bundy Refrigeration International Holding B.V. | Heat exchanger, method for producing same and various systems having such a heat exchanger |
WO2014103268A1 (en) * | 2012-12-26 | 2014-07-03 | 日本軽金属株式会社 | Heat exchange tube in heat exchanger and method for producing heat exchange tube |
WO2018059443A1 (en) * | 2016-09-28 | 2018-04-05 | 丹佛斯微通道换热器(嘉兴)有限公司 | Heat exchange assembly for heat exchanger, heat exchanger, and mold |
Also Published As
Publication number | Publication date |
---|---|
US20230016139A1 (en) | 2023-01-19 |
EP3994410A1 (en) | 2022-05-11 |
BR112022001146A2 (en) | 2022-03-15 |
DE202019104073U1 (en) | 2020-10-26 |
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