EP3491323A1

EP3491323A1 - Heat exchanger having a micro-channel structure or wing tube structure

Info

Publication number: EP3491323A1
Application number: EP17749468.9A
Authority: EP
Inventors: Jörg Kirchner; Matteo Codecasa; Sascha WIELAND
Original assignee: Bundy Refrigeration International Holding BV
Current assignee: Grandholm Production Services Ltd
Priority date: 2016-08-08
Filing date: 2017-08-08
Publication date: 2019-06-05
Anticipated expiration: 2037-08-08
Also published as: DE202017104743U1; WO2018029203A1; EP3491323B1

Abstract

The invention relates to a composite of components which consists of a plurality of micro-channel structures or wing tube structures which comprise a central micro-channel or a central wing tube with two wings. Two of the micro-channel structures or wing tube structures are connected by means of a fin structure. The fin structure extends across the width of the micro-channel structure or the wing tube structure, and has a trapezoidal design. Also disclosed are a condenser and an evaporator having a particularly compact design.

Description

Heat exchanger with microchannel structure or wing tube structure

1. Field of the invention

The present invention relates to a composite component of micro-channel structure or wing tube structure and lamellar structure, a heat exchanger with the composite component and the respective manufacturing process.

2. Background of the invention

Microchannel structures, for example for heat exchangers, are known in the art. An exemplary embodiment of a microchannel structure 1 according to the prior art is shown in FIGS. 1 and 2. The microchannel structure 1 consists of four microchannels 3 and has an overall rectangular cross-sectional shape with a width B _M and a height H _M (see FIG. For heat exchange with a medium flowing around the microchannel structure, therefore, only the outer surface of the microchannel structure is available. In order to increase this outer surface of the microchannel structure 1, which is available for heat dissipation, for example, the lamellar structure 10 shown in Figures 3 and 4 is used. The lamellar structure 10 has the shape of a concertina with a width B _L and a height H _L. The lamellar structure 10 in combination with two mutually parallel microchannel structures 1 results in a component composite 20, wherein in a heat exchanger of the component assembly 20 may also have a plurality of micro-channel structures 1, which are interconnected via corresponding lamellar structures 10 are. By the lamellar structure 10, the surface area of the micro-channel structure 1, which is available for heat dissipation, thus increased accordingly.

To further improve the heat transfer of such microchannel structures, it is also known to design the lamellar structure in an S shape and to arrange it transversely to the microchannel structure, as described, for example, in WO 2014/133 395 A1.

The object of the present invention is to provide a composite of microchannel or casement structure optimized in terms of heat transfer, in combination with a lamellar structure, so that these components can also be used in high-performance devices, such as, for example, a heat exchanger Motor vehicle, is cost-effectively applicable. It is a further object of the present invention to describe a corresponding heat exchanger and the associated production methods.

3. Summary of the invention

The above object is achieved by a component assembly of microchannel structure and LameUen structure according to claim 1 and wing tube structure and lamellar structure according to claim 2 and by a heat exchanger according to the independent claims 12 and 13. Likewise, the task is solved by a manufacturing method of a microchannel structure according to the independent patent claim 15, a manufacturing method of a lamellar structure according to the independent claim 16, a manufacturing method of a component assembly according to the independent patent claim 22 and a manufacturing method for a heat exchanger according to the independent patent claims 24 and 25. In addition, the above object is achieved by a condenser according to independent claim 26 and an evaporator according to independent claim 32. Further advantageous embodiments will become apparent from the following description, de n Drawings and the appended claims.

A microchannel structure for a heat exchanger or the like includes a plurality of mutually parallel microchannels defining a first region of the microchannel structure, and at least one, preferably two, outwardly extending vanes extending laterally from a surface surrounding the first region runs parallel to a longitudinal axis of the first region.

Therein, the first region consists of a plurality of mutually parallel microchannels which define a fluid flow direction. Microchannels in the sense of the present invention are channels with a diameter ≦ 11 mm. The first region is usually produced by means of extrusion, for example of aluminum.

In addition, to increase the surface available for heat removal, at least one wing is provided, which extends laterally outwards from a surface enclosing the first area. Lateral in this context means that the at least one wing extends transversely to the flow direction or to the course direction of the microchannels. The at least one wing preferably extends continuously over substantially the entire length of the first region. An advantage of this approach is that, in comparison to the known state of the art, an alternative solution for increasing the surface available for the heat removal is provided, which is not coupled to a stacking of a plurality of first regions or microchannel structures. It is particularly advantageous if the at least one wing is also produced by extrusion, preferably simultaneously with the first area. In this way, the first region and the at least one wing form an integral element, so that an additional connection of the at least one wing to the first region can be dispensed with. An advantage is thus that a larger surface available for heat transfer is provided in comparison to known microchannel structures, so that the efficiency of the microchannel structure according to the invention is also increased in comparison to known microchannel structures. One disadvantage to be mentioned is the larger installation space with the same number of microchannels, which the microchannel structure according to the invention requires due to the at least one wing.

According to one embodiment, the microchannel structure has two wings. It is particularly advantageous if the wings extend laterally outwards from opposite sides of the surface enclosing the first area. In this way, a further enlargement of the surface for heat transfer can be achieved.

Furthermore, the first region has an approximately rectangular cross-sectional shape having a greater width compared to a height, and the at least one wing extends from the surface surrounding the first region from a height-determining sidewall, preferably centrally. In the case of two wings arranged opposite each other, one wing each extends from one side wall, preferably centrally. In this way, when using the microchannel structure according to the invention, for example in a heat exchanger, good flow is provided by a heat transfer medium flowing at right angles to the fluid flow direction.

The above effect is further improved by rounding off the edges of the approximately rectangular cross-sectional shape according to a further embodiment. In this way, in particular a turbulent flow of the heat transfer medium about the microchannel structure according to the invention as well as a possible resulting stall can be avoided.

In addition, the lateral extent of the at least one wing corresponds to the outside about half the width of the first area. Further preferably, a thickness of the at least one wing is equal to a quarter of the height of the first area. With these particularly advantageous proportions, the surface can be increased by up to 40% in comparison to known microchannel structures or to the first region alone. An advantageous lamella structure for a microchannel structure, in particular for a microchannel structure described above, comprises: at least one first region in a first plane, which provides a first connection surface for a first microchannel structure, at least one second region in a second plane, which preferably provides a second connection surface for a second microchannel structure, at least one first oblique region, which is arranged with a first end on the first region and with an opposite second end on the second region, and at least a second inclined region, which is arranged with a first end on the first region or a further, preferably adjacent, first region and with an opposite second end on the second region, wherein the at least one first oblique region on a first side the first region includes a first angle α less than 90 ° and a second angle β of less than 90 ° with the second region at a second side opposite the first side. The first angle α and the second angle β are thus an alternating angle. With regard to the use with a microchannel structure, in particular with a microchannel structure according to the invention, the contact surface with the first region, preferably with the entire microchannel structure, is enlarged by the first and / or the second region. In this way, the heat from the first region or the micro-channel structure can be dissipated better compared to the known lamellar structures.

In one embodiment of the lamellar structure, the at least one second obliquely extending region on a first side closes with the first region or the further first region a third angle γ of less than 90 ° and with the second region on a second side opposite the first side a fourth angle δ smaller than 90 °. It is also advantageous if the second oblique region has a second inclination direction opposite to a first inclination direction of the first oblique region relative to a plane perpendicular to the first and / or second plane. Preferably, the first and the second direction of inclination are mirrored on the vertical plane, but this is not a mandatory requirement. An advantage of this embodiment is that now at least two obliquely extending regions are present, which have different inclination directions and different or the same inclination angle relative to the vertical plane. In this way, the surface available for heat dissipation can be further increased when used with a microchannel structure.

According to a further embodiment, the lamellar structure has a plurality of first and second regions as well as a plurality of first obliquely extending regions and a plurality of second obliquely extending regions. In this case, it is particularly preferred if the first oblique region is arranged with the first end at the first end of the first region and with the opposite second end at the first end of the second region and the second oblique region with the first end at the second End of the adjacent first region of the plurality of first regions and is arranged with the opposite second end at the second end of the second region. This has the advantage that, when used with a microchannel structure, the heat removal can be carried out particularly efficiently by enlarging the contact area. In other words, the fin structure is constructed such that a distance between two first areas is covered by a second area when the arrangement is viewed perpendicular to the first and second levels, respectively. The distance between the two first regions is smaller than the length of the second region. This also applies conversely for a distance between two second regions and the length of a first region. The dimensions of the first and second regions are preferably the same here. Also, preferably, the dimensions of the first and second inclined portions are the same. According to a further embodiment of the lamellar structure, the first angle α and the second angle β and / or the third angle γ and the fourth angle δ are the same size. This means that the at least one first region and the at least one second region are arranged in planes extending parallel to one another. In this way, a particularly uniform structure is created, which has an advantageous effect on the heat transfer.

In another embodiment of the lamellar structure, the first, the second, the first obliquely extending and / or the second obliquely extending region are straight, wavy or drawing-hammock-shaped or each region has any other desired shape or combinations thereof. Due to these design possibilities, the areas can each be adapted specifically to the requirements of the respective applications with regard to heat dissipation.

According to a further embodiment of the lamellar structure, a central depression is provided in the first and / or second region, which is preferably adapted to a microchannel structure, in particular to a first region of a microchannel structure described above, or to a wingpipe structure is. With this embodiment, the lamellar structure is adapted in a particularly advantageous manner to the microchannel structure and the wing tube structure, so that a contact for heat exchange between lamellar structure and microchannel / wing tube structure extends as far as possible over the entire width of the microcrane. NWFlügelrohr structure and / or the lamellar structure results. The heat exchanger is further supported by the fact that the recess is provided as a breakthrough or as a flat shape design. In the case of a flat design, the depression is formed in the lamellar material without breaking through the lamellar surface. This provides a certain size of contact area. In a breakthrough, the contact area is reduced to the edge of the aperture, which is connected to the micro-channel structure or the wing tube structure. A component assembly according to the invention consists of at least two microchannel structures, in particular the microchannel structures described above, or at least one wingpipe structure and a first According to the invention lamellar structure, wherein the two micro-channel structures or the wing tube structures are at least partially connected to each other via the lamellar structure, and wherein the micro-channel structures or wing tube structures preferably parallel to each other. The component composite produced in this way has the advantages of the above microchannel structure and / or the above lamellar structure. In this regard, reference is made to the corresponding statements.

The component assembly in the two embodiments according to the invention can be summarized as follows: According to a first embodiment, the component assembly consists of a plurality of microchannel structures, each having a plurality of mutually parallel microchannels defining a first region of the microchannel structure which has an approximately rectangular cross-sectional shape having a greater width compared to a height, and two laterally extending from a surface surrounding the first region from a height-determining sidewall outwardly extending wings, which are parallel to a longitudinal axis of the first region and a lamellar structure, comprising: at least a first region in a first plane, which provides a first connection surface for the first microchannel structure, at least one second region in a second plane, preferably one second verbin provides for the second microchannel structure, wherein in the first and second regions a central depression is provided, which is adapted to the microchannel structure in the first region, at least a first oblique region having a first end at the first region and with an opposite second end disposed on the second region, and at least one second inclined region disposed with a first end at the first region or at a further adjacent first region and at an opposite second end at the second region is, wherein the at least one first oblique region on a first side with the first region a first angle α less than 90 ° and at one of the first side opposite second side with the second region includes a second angle ß smaller than 90 °, and the at least a second oblique region on a first side with the first Be rich or the further first region a third angle γ smaller than 90 ° and at one of the first side opposite second side with the second region includes a fourth angle δ smaller than 90 °, wherein the two micro-channel structures connected to each other via the lamellar structure are and parallel to each other, wherein the lamellar structure has a width which corresponds to at least one width of the micro-channel structure and the lamella structure is in contact with the micro-channel structure over the entire width of the micro-channel structure.

According to the other embodiment, the component assembly consists of a plurality of elongate, straight-running wing tube structures, each having a central tube with a round, curvilinear or rectangular cross-section and two oppositely arranged and laterally extending outwardly from the central tube Having wings that are parallel to a longitudinal axis of the central tube, and a lamellar structure comprising the following features: at least a first region in a first plane providing a first connection surface for the first wing tube structure, at least one second region in a second plane providing a second connection surface for the second wing tube structure, wherein in the first and second regions At least one first inclined region, which is arranged with a first end on the first region and with an opposite second end on the second region, and at least one second oblique region, which is arranged with a first end on the first region or a further, adjacent, first region and with an opposite second end on the second region, wherein the at least one first oblique region on a first side with the ers - th range a first angle α less than 90 ° and at one of the first en side opposite second side with the second region includes a second angle ß smaller than 90 °, and the at least one second oblique region on a first side with the first region or the other first region a third angle γ smaller than 90 ° and at one of The first side opposite the second side with the second region includes a fourth angle δ smaller than 90 °, wherein the two wing tube structures are connected to each other via the lamellar structure and parallel to each other and the lamellar structure has at least one width, the one Width of the wing tube structure corresponds and the lamellar structure is in contact with the wing tube structure over the entire width of the wing tube structure. According to a preferred embodiment, the component assembly has a plurality of microchannel or wing tube structures, in particular the microchannel structures described above, whose first regions are preferably parallel to one another, each microchannel structure at least partially overlapping the respective adjacent microchannel structure a lamellar structure according to the invention is connected. In this way can be stacked any number of microchannel tube or wing structures for use in a subsequent heat exchanger to each other with a respective I _^ lamellae structure is provided between the microchannel structures. The lamellar structure is preferably attached to the microchannel structures or wingpipe structures, for example by soldering, welding, gluing. In accordance with a further preferred embodiment of the present invention, the component assembly has the plurality of elongate rectilinear wing tube structures in a meandering course parallel to each other and liquid-conducting connected in series with each other, so that a liquid inlet with an inlet and a liquid outlet with an outlet of the meandering course the wing tube structures is connectable. This preferred niäanderformige arrangement forms the basis for an efficient and liquid-saving household of coolant, which is used in the composite and later heat exchanger. For the central tube of the elongated, straight-running wing tube structures forms in each case at one end in a curved end or Connection area without wing, the fluid connection to the adjacent elongated rectilinear wing tube structure. Preferably, a smaller volume of cooling fluid is needed by the individual bent connection areas to supply the wing tube structures than is the case with a first and a second distributor tube in combination with the microchannel structures.

A heat exchanger according to the invention comprises a first manifold for supplying a fluid and a second manifold for discharging a fluid and a component assembly according to the invention, wherein the microchannels of each microchannel structure at a first end in flow communication with the first manifold and at a second end in flow communication with the second distribution pipe stand. With regard to the advantages, reference is made to the above statements on the microchannel structure according to the invention and the lamellar structure according to the invention.

A further heat exchanger according to the invention comprises a feed tube for supplying a fluid and a discharge tube for discharging a fluid and a component assembly having at least two wing tube structures connected via a preferred lamellar structure as described above, wherein the central tubes of the wing tube structures in the flow direction with each other are connected to provide a flow connection between the supply pipe and the discharge pipe. The heat exchanger with wing tube structures uses known design principles of a heat exchanger of this type. Advantageously, the lamellar structure extends at least over the entire width of the wing tube, ie transversely to the longitudinal axis of the wing tube. This transverse contact between the wing tube structure or microchannel structure and the lamellar structure extends over the maximum width. Preferably, this contact area is increased by increasing opposing contact surfaces of FlügehOhr- / micro-channel structure and lamellar structure. This applies to contact lines and / or contact surfaces in the area of the wings and / or the tube or the area of the interconnected microchannels. Furthermore, the central tubes of the wing tube structures are sequentially interconnected to provide flow communication between the feed tube and the coolant removal tube. Within this composite, the majority of the elongated rectilinear wing tube structures are arranged parallel to each other in a meandering course. Thus, due to this arrangement, the multiple wing tube structures form an approximately flat surface. The feed pipe is connected to the input and the

Outlet pipe is connected to the exit of the meandering course of the wingpipe structures. According to a preferred embodiment, at least two meandering courses of the wing tube structures are arranged parallel to one another and flat next to each other and are in flow communication with one another. In addition, the wings of the wing tube structures are preferably approximately perpendicular to the arranged by the meandering courses of the wing tube structures plane / levels arranged.

An advantageous manufacturing method for a microchannel structure comprises the step of: extruding a microchannel structure consisting of a plurality of mutually parallel microchannels defining a first region of the microchannel structure, and at least one, preferably two, laterally of a wing extending outwardly from the first area and extending parallel to a longitudinal axis of the first area, preferably made of aluminum. By means of the production method according to the invention, a microchannel structure according to the invention is produced. With regard to the advantages, reference is therefore made to the microchannel structure according to the invention.

An advantageous method of manufacturing a lamellar structure comprises the steps of providing at least a first region that provides a first connection surface for a first microchannel structure or a wingpipe structure, and at least one second region, which preferably has a second connection surface for a second microchannel Then, arranging a first oblique region having a first end at the first region and an opposite second end at the second region such that the at least one first oblique region on a first side with the first region includes a first angle α less than 90 ° and a second angle β of less than 90 ° with the second region at a second side of the first side, and arranging a second oblique region having a first end at the first region or another, vorzu adjacent first region and with an opposite second end at the second region. By means of this production process, the lamellar structure according to the invention can be produced. Therefore, with regard to the corresponding advantages, reference is made to the explanations on the lamellar structure.

According to a further embodiment, the step of arranging the second obliquely extending region takes place in such a way that the second oblique region on a first side with the first region or the further first region has a third angle γ of less than 90 ° and on one of the first side opposite. set second side with the second region includes a fourth angle δ smaller than 90 °.

Further, the step of providing includes providing a plurality of first and second regions, and the steps of disposing the first and second inclined regions are repeated a plurality of times. Further preferably, arranging the first inclined portion is performed so that the first inclined portion is disposed with the first end at the first end of the first portion and the opposite second end at the first end of the second portion, and arranging the second inclined portion is made such that the second inclined portion having the first end at the second end of the adjacent first portion of the plurality of first regions and with the opposite second end at the second end of the second region.

In addition, the manufacturing method of a lamellar structure comprises the further step of providing a central depression in the first and / or second region, which is preferably of a microchannel structure, in particular of a first region of a microchannel structure according to the invention, or a wing tube Structure is adjusted. According to a first alternative, the first and / or the second region may already have a depression for the microchannel structure, in particular for a first region thereof, when the regions are initially provided. If the lamellar structure is composed of individual parts, then the recess can be produced, for example, before the first and / or the second obliquely extending region are arranged. According to a further alternative, corresponding depressions can also be provided later.

In addition, the steps of the manufacturing method of the lamellar structure according to the invention are realized by bending a sheet-metal layer. If the lamellar structure as a whole is produced from a sheet metal layer by bending, then the above-mentioned depression is produced either before or after the bending in the regions which later correspond to the first and / or the second region. It is also conceivable punch out or cut out breakthroughs. A production method of a component assembly comprises the steps of providing at least two microchannel structures or wing tube structures, in particular the microchannel structures described above, and one of the lamella structures described above, then at least partially connecting the two microchannel structures or the Wing tube structures by means of the lamellar structure, for example by means of soldering, welding or gluing the lamellar structure.

According to one embodiment, the step of providing in the manufacturing method of the component composite comprises providing a plurality of microchannel / wingpipe structures and fin structures, and the step of connecting comprises at least partially connecting each microchannel structure from the plurality of microchannels Structures with the respective adjacent micro-channel structure or each wing tube structure of the plurality of wing tube structures with the respective adjacent wing tube structure, by means of a respective lamellar structure (120).

A manufacturing method of a heat exchanger according to the invention comprises the steps of providing a first manifold, providing a second manifold and providing a erfmdungsgemäßen component assembly and thereafter connecting the microchannels of each micro-channel structure at a first end to the first manifold and at a second end to the second manifold. Becomes If the heat exchanger is produced from a wing tube structure, then first a supply and an exhaust pipe are provided and connected to the wing tube structures, which have been connected one after the other, ie in series. A condenser according to the invention consists of at least two, preferably at least three, subunits, each with a plurality of elongate, rectilinear wing tube structures, each having a central tube with a round, curvilinear or angular cross-section and two oppositely arranged and laterally extending from the central tube outwardly extending wings that are parallel to a longitudinal axis of the central tube, and a lamellar structure, comprising: at least a first region in a first plane having a first contact zone for the first wing tube Strukrur provides at least a second region in a second plane, which provides a second contact zone for the second wing tube structure, wherein in the first and second region a central recess is provided, which is adapted to a shape of the tube of the wing tube structure, at least a first An inclined portion disposed at a first end at the first portion and at an opposite second end at the second portion, and at least a second inclined portion provided with a first end at the first portion or at a further adjacent first portion and an opposing second end is arranged on an adjacent second region or on the second region, wherein two wing tube structures are connected to each other via the lamellar structure and parallel to each other, so that the wings of a subunit are arranged in parallel planes, and the Lamella structure has at least one width corresponding to a width of the wing tube structure, and the lamellar structure over the width of the wing tube structure with the wing tube structure in contact, wherein the subunits are arranged side by side and in the operation of the Condenser a flow direction over the La me The condenser further comprises a supply tube for supplying a fluid, which is connected to a first end of the plurality of wing tube structures of at least one of the subunits and a discharge tube for discharging a fluid connected to a second end of the wing tube structures opposite at least one of the subunits, the inner diameter of the central tube of the wing tube structure being at least 3 mm, the outer diameter of the central tube of the wing tube Structure is at least 4 mm and a width of the wing tube structure is preferably <25 mm.

A condenser or condenser is generally a device in which a fluid flowing inside the central tube of the flywheel structure is transferred from the gaseous state of aggregation to the liquid state of matter (condensation). In heat engines and refrigeration systems, condensers serve to liquefy the exhaust steam or the vaporous refrigerant. This enables a closed cycle process in these plants. An advantage of the condenser according to the invention is the particularly compact structure and the particularly efficient removal of heat by means of the wing tube structure in combination with the lamellar structure and the specific structure and dimensions. In an advantageous embodiment, the condenser therefore has at most six subunits.

It is also preferred that a distance between two wing tube structures of the same subunit is between 10 and 12 mm. In a further advantageous embodiment, the average distance between two successive first and / or second regions of the lamellar structure is 3 to 9 mm. Furthermore, the distance between central tubes of adjacent subunits is preferably 25 to 35 mm, preferably measured from tube center to tube center. Alone with each of these features alone a particularly compact design of the condenser can be achieved. These features in combination therefore result in a particularly advantageous and efficient embodiment of the condenser.

Finally, it is preferable that a width of the condenser perpendicular to the flow direction of the air flowing over the fin structure of the condenser 200 to 250 mm, a height of the condenser is perpendicular to the flow direction over the lamellar structure of the condenser flowing air 100 to 150 mm, and a condenser depth in the flow direction of the air flowing through the condenser slat structure is 80 to 150 mm. As a result of these dimensions, the condenser can also be used, for example, in household appliances such as a tumble dryer.

An evaporator according to the present invention comprises, preferably exactly, two elongated straight-sided wing tube structures, each having a plurality of central tube sections with a circular, curvilinear or angular cross-section and two oppositely disposed and laterally from the central tube section have outwardly extending wings that are parallel to a longitudinal axis of the central tube section with the wings of a respective wing tube structure arranged in the same plane, and the evaporator further comprises a lamellar structure, comprising: at least one first region in a first plane providing a first contact zone for the first wing tube structure, at least one second region in a second plane providing a second contact zone for the second wing tube structure, wherein a central depression in the first and second regions is adapted to a shape of the tube of the wing tube structure, at least a first inclined portion, which is arranged with a first end at the first region and with an opposite second end at the second region, and at least one second obliquely extending region having a first end at the first region or a further, adjacent, first region and with an opposite second end is arranged on an adjacent second region or on the second region, wherein the two wing tube structures are connected to each other via the lamellar structure and parallel to each other and the lamellar structure has at least one width corresponding to a width of the wing tube structure ent - speaks, and the lamellar structure over the width of the wing tube structure with the wing tube structure as well as with a plurality of pipe sections of the respective wing tube structure in contact, wherein in the operation of the evaporator, a flow direction of a flowing over the lamellar structure of the evaporator air is aligned approximately at right angles to the lamellar structure, and the outer diameter of the central tube of the wing tube structure is 6 to 8 mm, wherein a wall thickness of 0.5 mm and a width of the wing tube structure is 25 to 30 mm.

An evaporator is generally a device in which a fluid flowing inside the central tube of the wing tube structure is transferred from the liquid state to the gaseous state. An advantage of the evaporator according to the invention, as well as the condenser according to the invention, is the particularly compact design. In an advantageous embodiment, the condenser therefore has exactly two wing tube structures.

Each of the two wing tube structures includes a plurality of tube sections with wings. The tube sections with wings of a respective wing tube structure are arranged so that the wings are arranged in a plane. This distinguishes the evaporator according to the invention, for example, from the condenser according to the invention, in which the wings of a wing tube structure are arranged in parallel planes. In order to connect a plurality of tube sections with wings of a wing tube structure with likewise several tube sections with wings of a further wing tube structure, the flap structure preferably comprises a plurality of central depressions, so that a lamella structure in each case a plurality of tube sections with wings of the first and second wing tube structure interconnects.

In an advantageous embodiment, a distance between the wings of the first and the second wing tube structure is about 20 mm. Also preferred is the width of the wing tube structure <30 mm. In this way, a particularly compact construction of the evaporator can be achieved. Preferably, there is at least in part a cavity between the vanes of the wing tube structure and the lamellar structure provided with a means for resisting thawing. In this way, the effectiveness of the evaporator can be further improved.

Hereinafter, a detailed embodiment of the present invention will be described with reference to the drawings. In the drawings, like reference numerals designate like components. 4. Brief description of the drawings

Show it:

Figure 1 is a perspective view of a micro-channel structure according to the state of

technology

Figure 2 shows the micro-channel structure of Fig. 1 in cross section

Figure 3 is a perspective view of a lamellar structure according to the state of

Technology,

FIG. 4 shows the lamellar structure from FIG. 3 in cross section,

FIG. 5 shows a perspective view of a component composite comprising a plurality of microchannel structures and lamellar structures according to the prior art,

FIG. 6 shows the component composite from FIG. 5 in a side view,

7 shows a perspective view of an embodiment of a microchannel structure according to the invention, FIG.

FIG. 8 shows the microchannel structure from FIG. 7 in cross section,

Figure 9 is a perspective view of a preferred embodiment of a

Lamellar structure according to the present invention,

FIG. 10 shows a cross-section of the lamella structure from FIG. 9,

FIGS. 11 and 12 show a perspective view of a component assembly comprising microchannel structures and lamellar structures according to an embodiment of the present invention,

Figure 13 is a perspective view of a preferred embodiment of a

Heat exchanger according to the present invention, Figure 14 shows a detail of the heat exchanger of FIG. 13 in side view and

FIG. 15 shows a detail of the heat exchanger from FIGS. 14 and 13 for illustrating a connection of a first region to a distributor tube.

FIG. 16 shows a further preferred embodiment of a component composite with a

Wing tube structure and a lamellar structure, Figure 17 shows a preferred embodiment of a further lamellar structure,

FIG. 18 shows a side view of the lamella structure from FIG. 17,

Figure 19 shows a further preferred embodiment of a lamellar structure with

Contact surfaces to an adjacent wing tube, not shown,

FIG. 20 shows a side view of a preferred embodiment of a component composite consisting of a lamellar structure and a wing tube structure,

FIG. 21 shows a further side view of the preferred component composite according to FIG

20

FIG. 22 shows a perspective view of the component composite according to FIG. 21,

FIG. 23 shows an enlarged perspective view of a detail from the component assembly according to FIG. 22,

FIG. 24 shows a perspective view of a preferred heat exchanger according to the invention with a preferred component composite comprising wing tube structures and lamellar structures arranged therebetween,

Figure 25 is a first perspective view of a preferred according to the invention

condenser,

Figure 26 is a second perspective view of the invention preferred

condenser, FIG. 27 shows a side view of the preferred liquefier according to the invention,

FIG. 28 shows an end view of the preferred liquefier according to the invention,

Figure 29 is a first perspective view of a erfmdungsgemäß preferred

evaporator,

FIG. 30 shows a side view of the preferred evaporator according to the invention,

Figure 31 is a second perspective view of the invention preferred

Vaporizer and

FIG. 32 shows an exploded view of the preferred evaporator according to the invention.

5. Detailed description of a preferred embodiment

A microchannel structure according to the invention can be used, for example, in a heat exchanger of a motor vehicle, for example in an air conditioning system of a motor vehicle. Furthermore, the microchannel structure is used in all high-performance devices which must ensure the most efficient possible heat transfer in the least possible space available.

Referring to FIGS. 7 and 8, a microchannel structure 100 according to a preferred embodiment consists of four microchannels 104 which together define a first region 102 with a fluid flow direction. The microchannels 104 preferably have a diameter of at most 1 mm. Four microchannels 104 are arranged side by side, with the two middle microchannels having a substantially rectangular cross-sectional shape. As a result, the first region 102 as a whole has an approximate rectangular cross-sectional shape. The two microchannels 104 on the outside have rounded edges 108. In particular, the rounded edges 108 serve to improve the flow through a heat transfer medium in conjunction with vanes 106 explained below, so that, for example, a flow can be as laminar as possible and a stall at the first region 102 can be avoided. On a surface surrounding the first region 102, there are further provided two vanes 106 which extend laterally outward and extend parallel to a longitudinal axis of the first region 102. The wings 106 extend substantially over the entire length of the first region 102. This means that the vanes 106 do not extend all the way to the respective end of the first region 102, so that the first region 102 has a connection region 110 at both axial ends. The connection area 110 serves for a connection to a distribution pipe of a heat exchanger ISO or another corresponding device.

From FIG. 8, a particularly advantageous proportionality of the first area 102 to the wings 106 can be recognized. Referring to FIGS. 7 and 8, a total width B _{Ges of} the micro-channel structure 100 is composed of twice the width of a vane 106 and one time a width Bs of the first region 102. The width of the two vanes 106 together corresponds approximately to the width Bs of the first region 106. The ratio of the total width B _{Ges of} the microchannel structure 100 to the width Bs of the first region 102 is therefore approximately 2: 1. The thickness D of the wings 106 is about one quarter of the height Hs of the first region 102.

As can be seen in FIGS. 7 and 8, the vanes 106 are arranged, in particular, centrally at a side wall of the surface surrounding the first region 102, defining a height Hs of the first region 102. In this way and by means of the rounded edges 108, as already explained above, a continuous laminar flow can be ensured to improve the heat transfer. By means of this structure, a surface enlargement of about 40% compared to the structure shown in Figures 1 and 2 can be achieved. This also has a correspondingly advantageous effect on heat dissipation.

Figures 9 and 10 show a preferred embodiment of a fin structure 120 for a microchannel structure 100. The fin structure 120 consists of a straight first region 122 in a first plane and a straight second region 124 in a second plane. The first and second levels are parallel to each other. The first region 122 is connected to the second region 124 via a first straight inclined region 126. The first oblique region 126 includes a first angle α <90 ° with the first region 122. Likewise, the first oblique region 126 includes a second angle β <90 ° with the second region 124. The first angle α and the second angle β are a change angle because they are on opposite sides of the first inclined portion 126 and on opposite sides of the first 122 and second portions 124. Due to the parallel arrangement of the first and the second plane, the first α and the second angle β are the same. Furthermore, the first oblique region 126 has a first inclination direction relative to a plane perpendicular to the first and / or second plane. This vertical plane runs transversely to a direction of fluid flow, as can be seen when using the lamination structure 120 with the microchannel structure 1, 100. The structure resulting from this arrangement increases in comparison to known concertina-shaped or S-shaped structures Use with a micro-channel structure 1, 100 a contact area with the micro-channel structure 1, 100, so that in this way the heat dissipation can be further improved.

To continue the structure, a second straight inclined region 128 is further provided. The second obliquely extending region 128 closes with a further, adjacent, first region 122 a third angle γ <90 ° and with the second region 124 a fourth angle δ <90 °. The third γ and fourth angle δ are again, as already described for the first oblique region 126, alternating angles. With respect to the vertical plane described above, the second inclined portion 128 has a second inclination direction opposite to the first one. In the illustrated embodiment, the second inclination direction is a reflection of the first inclination direction on the vertical plane. Preferably, the dimensions of the first 122 and second regions 124, as well as the first inclined 126 and the second inclined regions 128 are the same. This also applies to all four angles α, β, γ, δ. Still referring to FIGS. 9 and 10, in other words, a plurality of first regions 122 are spaced apart such that the distance between the first regions 122 is smaller than a length of the second regions 124. If the lamellar structure 120 becomes perpendicular from one direction As seen in the first and second planes, a second region 124 overlaps the distance between two first regions 122 and vice versa.

As can likewise be seen in FIGS. 9 and 10, the first 122 and second regions 124 have a depression 130 in the center for receiving the first region 102 of the microchannel structure 100. The first 126 and second regions 128 likewise have corresponding recesses at the contact regions to the first and second regions 122, 124. This results in the central region of the lamellae structure 120 in the recess 130 a height H _LS , the is correspondingly lower than the total height H _{LGes of} the lamellar structure 120.

Since the lamellar structure 120 as a whole has a width B _LGes which approximately corresponds to the width B _{Ges of} the _microchannel structure 100, the protrusions 132 result at the edge regions of the lamellar structure 120. The resulting advantage becomes apparent when the figures 11 and 12 are considered. This shows that the lamellar structure 120 is in contact with the microchannel structure 100 over its entire width. In this way, therefore, the area available for heat dissipation can be increased particularly effectively. Alternatively, it is also conceivable that, when used with a conventional microchannel structure 1, the recess 130 is provided so that the protrusions 132 of two arranged on the respective sides of the micro-channel structure 1 lamellar structures 120th touch and represent corresponding wings. In this case, the width of the recess would be 130 of the lamellar structure 120 correspond to the width of the microchannel structure 1 and a width of the respective projections 132 could each correspond to half the width of the microchannel structure 1 or the depression 130. FIGS. 11 and 12 show a component composite 140 according to an embodiment. The component subassembly 140 consists of three microchannel structures 100, which are connected to one another via two lamellar structures 120. The fin structure 120 is secured between the microchannel structures 100. This can be done, for example, by clamping between the microchannel structures 100 or by other types of attachment, such as soldering to the respective microchannel structure 100. Compared to the known component shown in FIGS. 5 and 6, a surface enlargement of approximately 43% can be achieved with the component assembly 140 according to FIGS. 11 and 12, which results in a correspondingly improved heat transfer.

Finally, FIGS. 13 to 15 show a preferred embodiment of a heat exchanger ISO. The heat exchanger 150 has a first manifold 152 with a first port 1S6 and a second manifold 154 with a second port 158. A fluid is supplied via one of the two ports 1S6, 1S8, while the fluid is discharged again via the respective other port 158, 156.

Between the two distribution pipes 152 and 154, a component composite 140 is arranged. The number of microchannel structures 100 in the component assembly 140 depends on the height of the distribution pipes 152, 154. In particular, FIG. 15 shows that the connection region 110 is used as the vane-free region of the microchannel structure 100 for connection to the respective manifold 152, 154.

A further preferred embodiment of a component composite 140 'is shown in FIG. 16. This component composite 140' consists of a further preferred embodiment of the laminated structure 120 'already described above. This lamellar structure 120 'connects oppositely disposed wing tubes 200. Such wing tubes 200 consist of a central tube 210 with a round, curvilinear or square cross-section. Furthermore, the central tube 210 has, on two mutually opposite sides, in each case a wing 220, which extends in the radial direction from the central tube 210. The radially outwardly extending wings 220 are parallel to the longitudinal axis of the central tube 210 and thus the entire wing tube structure.

At least two wing tube structures 200 arranged parallel to one another are connected to one another via a lamellar structure 120 'arranged therebetween. In this case, the lamellar structure 120 'has the same structural properties as already described above in combination with the microchannel structure 1; 100 have been explained. Accordingly, the first 122 'and second portions 124' in the preferred embodiment of FIG. 16 and in the fin structures 120 'of FIGS. 17 and 18 form one line-like contact to the adjacent wing tube structures 200 ago. The first oblique region 126 'and the second oblique region 128' connect the two opposing mutually straight first and second straight regions 122 'and 124'. In addition, the inclined portions 126 'and 128' connect the two oppositely disposed wings 220 and the central tube 210. Thus, in the same manner as between the above-described fin structure 120 and the micro-channel structure 1; 100, the lamellar structure 120 'has a heat-conducting contact with the wing tube structure 200. In this way, the fin structure 120 'increases the area of the wing structure 200 available for heat exchange. As can be seen from the preferred embodiment of the fin structure 120' in Figure 17, this has in the first straight contact area 12Γ a depression 130 '. This depression 130 'is adapted to the shape of the central tube 210 to receive it in the depression 130'. While in the preferred embodiment of FIG. 17 the depression 130 'is shown as a cut-out region of the straight region 122' of the lamellar structure 120 ', it is also preferable to provide the depression 130' in a planar manner. For this purpose, the straight first region 122 'is not provided in the form of a line-like contact region tapering to a point, but rather as a straight, flat contact region, as shown schematically in FIG. 19. The contact surface 122 'shown there is flat and thus preferably abuts against the central tube 210 and the wings 220 of the wing tube structure. Accordingly, it is also preferable to provide a planar depression (not shown) for the central tube 210 in the straight regions 122 'and 124'.

As can be seen on the basis of the preferred embodiments of the component assembly 140 'according to FIGS. 20-23, a plurality of wing tube structures 200 consisting of the wings 220 and a central tube 210 are arranged parallel to one another. Respective wing tube structures 200 with central tube 210 and wings 220 are connected to one another via the respective interposed lamellar structure 120 'in order to enlarge the heat exchanging surfaces of the wing tube structure. In order to be able to establish a fluid connection between the mutually parallel wing tubes 210, 220, the central tubes 210 are connected to each other via curved tube sections 230 without wings (see FIGS. 20, 21, 23). The component assembly 140 'also includes a supply pipe 156' and an exhaust pipe 158 'in the same way as has been used in the heat exchanger 150 already described above. Accordingly, a cooling medium is introduced into the component assembly by the feed tube 156 'described above, while it is discharged via the discharge pipe 158'.

The wing tube structures 200 interconnected according to the above arrangement form a meander-shaped course. As a result, the wing tube structures 200 arranged parallel to one another approach approximately one plane. According to a preferred embodiment of the present invention, the Wings 220 of the wing tube structures 200 are arranged approximately perpendicular to a plane spanned by the meandering courses of the wing tube structures 200. As a result, it is preferably possible to effectively use the component assembly with only one plane or a plurality of planes arranged parallel to one another in a meander-shaped connected wing tube structures in a heat exchanger.

A preferred embodiment of a heat exchanger ISO 'using at least one of the component assemblies 140' described above is shown in FIG. In this preferred heat exchanger 150 ', a first and a second component composite 140', which is shown for example in FIGS. 21 and 22, are used in a parallel arrangement with respect to one another. These two component assemblies 140 'arranged parallel to one another are in fluid connection, so that a fluid supplied through the feed tube 156' flows through both component assemblies 140 'and then is discharged through the discharge tube 158'. With regard to the preferred embodiment of FIG. 24, it is also preferable to provide these only consisting of one component composite or with more than two component composites 140 '. In the same way as can be seen in Figures 16, 20, 21, 22, 23 and 24, the wings 220 are arranged parallel to a flow direction S. The same applies to the obliquely extending first and second regions 196 '128' of the lamellar structure 120 '. These likewise run parallel to the flow direction S (see FIG. 24).

A manufacturing method for the microchannel structure 100 according to FIGS. 7 and 8 comprises the step of: extruding (step A) a microchannel structure 100 consisting of a plurality of microchannels 104 running parallel to one another and having a first region 102 of the microchannel Define structure 100, and at least one, preferably two, laterally extending from a surface surrounding the first portion 102 outwardly extending wing 106 which is parallel to a longitudinal axis of the first region 102, preferably made of aluminum.

A manufacturing method of a lamination structure 120 according to FIGS. 9 and 10 comprises as a first step the provision (step B) of at least one first region 122, which has a first connection surface for a first microchannel structure 1; 100, and at least one second region 124, which preferably has a second connection surface for a second microchannel structure 1; 100. As a second, subsequent step (step C), a first inclined region 126 is arranged with a first end on the first region 122 and with an opposite second end on the second region 124 such that the at least one first oblique region 126 abuts a first side with the first region 122 includes a first angle α of less than 90 ° and a second angle β of less than 90 ° with the second region 124 on a second side opposite the first side. Furthermore, the production method comprises before, after or at the same time as step C the further step of arranging (step D) a second inclined region 128 with a first end on the first The second oblique region 128 is arranged such that the at least one second obliquely extending region 128 is arranged on a first side with the first region 122 includes a third angle γ smaller than 90 ° and at one of the first side opposite second side with the second region 124 a fourth angle δ smaller than 90 °.

The provisioning (step B) preferably comprises providing a plurality of first 122 and second regions 124, and the steps of arranging (steps C and D) of the first 126 and second oblique regions 128 are repeated several times. In this way, the lamellar structure can be adapted particularly advantageously to a length of the microchannel structure. Arranging (step C) of the first oblique region 126 is effected such that the first oblique region 126 is arranged with the first end at the first end of the first region 122 and with the opposite second end at the first end of the second region 124 becomes. Arranging (step D) of the second oblique region 128 is effected such that the second oblique region 128 with the first end at the second end of the adjacent first region 122 of the plurality of first regions 122 and with the opposite second end on the second End of the second area 124 is arranged.

Furthermore, the step of providing (step E) a central depression 130 is provided in the first 122 and / or the second region 124. The central depression is preferably connected to a microchannel structure 1; 100, in particular to a first region 102 of a microchannel structure according to the invention, adapted. The step of providing the depression 130 may generally occur before or after the provision of the first and second regions, and before or after the first and / or the second oblique regions are arranged. The steps B to E can be realized by bending a sheet metal layer.

A manufacturing method of a component assembly 140 according to FIGS. 11 and 12 or 16, 20, 21, 22 comprises the provision (step F) of at least two microchannel structures 1; 100 according to FIGS. 1 and 2 or 7 and 8 or of at least two wing tube structures 200 and a lamellar structure 120 according to FIGS. 9 and 10. Thereafter, the step is carried out: at least partial joining (step G) of the two microchannel structures 1; 100 or the two wing tube structures 200 by means of the lamellar structure 120, for example by means of soldering, gluing or welding of the lamellar structure 120. The step of providing (step F) comprises providing a plurality of microchannel structures 1; 100 or wing tube structures and fin structures 120 and the step of joining (step G) comprises at least partially joining each microchannel structure 1; 100 of the plurality of microchannel structures 1; 100 with the respective adjacent microchannel structure 100 by means of a respective lamellar structure 120 or each wing tube structure 200 of the plurality of Wing tube structures 200 with the respective adjacent wing tube structure 200 by means of a respective lamellar structure 120.

A manufacturing method of a heat exchanger 150 according to FIGS. 13 to 15 comprises the steps of providing (step H) a first distributor tube 152, providing (step I) a second distributor tube 154 and providing (step J) a component assembly 140 according to FIGS 12. Provision can be made in any order. After providing (steps H, I and J) of all components, the connection (step K) of the microchannels 3 takes place; 104 of each microchannel structure 1; 100 at a first end to the first manifold 152 and at a second end to the second manifold 154th

Alternatively, a manufacturing method of a heat exchanger according to Figure 24 comprises the steps of providing (step H) a supply pipe 156 'for supplying a fluid and providing (step I) a discharge pipe 158' for discharging a fluid, providing (step J) a component assembly described above with a plurality of wing tube structures, and thereafter connecting (step K) the central tubes of the wing tube structures 200 in sequence to provide flow communication between the feed tube and the drain tube and around the plurality of elongated rectilinear wing tube structures 200 be arranged in a meandering course parallel to each other, so that the supply pipe is connected to an input and the discharge pipe to an outlet of the meandering course of the wing tube structures 200.

Referring now to Figs. 25-28, a preferred embodiment of a condenser 200 is shown. A condenser or condenser is generally a device in which a fluid flowing in the interior of the central tube of the wing tube structure is converted from the gaseous state of aggregation into the liquid state of matter (condensation). In heat engines and refrigeration plants, condensers serve to liquefy the exhaust steam or the vaporous refrigerant. This enables a closed cycle process in these plants.

The condenser 200 consists of four subunits 202, 204, 206 and 208, each having a plurality of elongated rectilinear wing tube structures 210. Each wing tube structure 210 has a central tube 212 with a round cross-section and two oppositely disposed and laterally extending from the central tube 212 outwardly extending wings 214. The wings 214 extend parallel to a longitudinal axis of the central tube 212. Further, each subunit 202, 204, 206, and 208 includes a louver structure 220. The louver structure 220 has at least a first region in a first plane that is a first Contact zone for the first wing tube structure 210 provides, and at least a second region in a second plane which provides a second contact zone for the second wing tube structure 210. Provided in the first and second regions is a central depression that conforms to a shape of the tube 212 of the wing tube structure 210. Furthermore, the fin structure 220 has at least one first oblique region, which is arranged with a first end on the first region and with an opposite second end on the second region, and at least one second obliquely extending region, which has a first end on the first Area or another, adjacent, first area and with an opposite second end at an adjacent second area or at the second area is arranged. Two wing tube structures 210 are connected to one another via the lamellar structure 220 and run parallel to one another, so that the wings of a subunit 202, 204, 206 and 208 are arranged in parallel planes. The lamellar structure 220 has at least one width which corresponds to a width of the wing tube structure 210, and is in contact, preferably over the entire width of the wing tube structure 210, with the wing tube structure 210.

The four subunits 202, 204, 206 and 208 are arranged side by side. During operation of the condenser 200, a flow direction of an air flowing over the fin structure 220 of the condenser 200 is aligned approximately perpendicular to the fin structure 220. Further, the condenser 200 includes a supply pipe 230 for supplying a fluid connected to a first end of the plurality of vane structures 210 of each of the subunits 202, 204, 206, and 208, and a discharge pipe 232 for discharging a fluid is connected to a second end opposite the first end of the wing tube structures 210 of each of the subunits 202, 204, 206 and 208.

An inner diameter of the central tube 212 of the wing tube structure 210 is at least 3 mm, wherein the outer diameter of the central tube 212 of the wing tube structure 210 is at least 4 mm and a width of the wing tube structure is <25 mm. A distance between two wing tube structures of the same subunit is for example between 10 and 12 mm and the average distance between two successive first and / or second regions of the lamellar structure is 3 to 9 mm. Further preferably, the distance between central tubes of adjacent subunits 202, 204, 206 and 208 is 25 to 35 mm.

A condenser width at right angles to the flow direction of the air passing over the lamellar structure of the condenser is 200 to 250 mm, a height of the condenser perpendicular to the direction of flow of the air flowing through the condenser lamellar structure is 100 to 150 mm and a condenser depth in the flow direction of the air flowing through the lamellar structure of the condenser is 80 to 150 mm. Due to these dimensions, the condenser can be used particularly efficiently, for example, in household appliances such as a tumble dryer. An advantage of the condenser according to the invention is therefore the particularly compact structure and the particularly efficient removal of heat by means of the wing tube structure in combination with the lamellar structure and the specific structure and dimensions.

Referring now to FIGS. 29 to 32, a preferred evaporator 300 according to the present invention is shown. An evaporator is generally a device in which a fluid flowing inside the central tube of the wing tube structure is transferred from the liquid state to the gaseous state. An advantage of the evaporator according to the invention, as well as the condenser according to the invention, is the particularly compact design.

The vaporizer 300 includes exactly two elongate rectilinear wing tube structures, namely a first 302 and a second wing tube structure 308. Each wing tube structure 302, 308 has a central tube 304, 310 with a circular cross-section and two opposing angeord - Nete and laterally of the central tube 304, 310 outwardly extending wings 306, 312 on. The wings 306, 312 are parallel to a longitudinal axis of the respective central tube 304, 310. Furthermore, the wings 306, 312 of the respective wing tube structure 302, 308 are arranged in the same plane. Each of the two wing tube structures 302, 308 therefore comprises a plurality of tube sections with wings 306, 312. The tube sections with wings 306, 312 of a respective wing tube structure 302, 308 are arranged so that the wings 306, 312 in a plane are arranged. This distinguishes the inventive evaporator, for example, from the condenser according to the invention, in which the wings of a wing tube structure are arranged in parallel planes. In order to connect a plurality of tube sections with wings of a wing tube structure with likewise several tube sections with wings of a further wing tube structure, the lamellar structure 320 explained below comprises a plurality of central depressions 322, so that a lamella structure in each case has a plurality of tube sections with wings the first and second wing tube structure interconnects.

The vaporizer 300 further includes the aforementioned fin structure 320. The fin structure has at least a first region in a first plane that provides a first contact zone for the first winglet structure 302 and at least a second region in a second plane Level, which provides a second contact zone for the second wing tube structure 308. Provided in the first and second regions are a plurality of central depressions 322, which are adapted to a shape of the tube 304, 310 of the wing tube structure 302, 308. In addition, the lamellar structure 320 comprises at least one first obliquely extending region, which is arranged with a first end at the first region and with an opposite second end at the second region, and at least one second obliquely extending region, which has a first end at first area or another, adjacent, first area and disposed at an opposite second end at an adjacent second area or at the second area.

The two wing tube structures 302, 308 are connected to one another via the lamellar structure 320 and run parallel to one another. The lamellar structure 320 has at least one width which corresponds to a width of the tube structure 302, 308. In addition, the louver structure 320 is in contact with the wing tube structure 302, 308 over the width of the wing tube structure 302, 308 and with a plurality of tube sections of the respective wing tube structure 302, 308. During operation of the evaporator 300, a flow direction of an air flowing over the lamellar structure of the evaporator is oriented approximately at right angles to the louver structure.

The outer diameter of the central tube 304, 310 of the wing tube structure 302, 308 is 6 to 8 mm, with a wall thickness of 0.5 mm, and a width of the wing tube structure 302, 308 is 25 to 30 mm. A distance between the wings of the first and second wing tube structures is about 20 mm. The width of a pipe section with wings is <30 mm. In this way, a particularly compact construction of the evaporator can be achieved. Furthermore, at least in part, a cavity may be present between the wings of the airfoil structure and the lamellar structure. This can be provided with a means of resisting thawing. In this way, the effectiveness of the evaporator can be further improved.

LIST OF REFERENCE NUMBERS

1 microchannel structure

3 microchannel

10 lamellar structure

20 component composite

100 micro-channel structure

102 first area

104 microchannel

106 wings

108 edge

110 connection area

120 I _^ lamellae structure

122 first area

124 second area

126 first inclined area

128 second oblique area

Claims

1. Composite component (140) consisting of: a. a plurality of microchannel structures (1; 100), each of which is b. a plurality of mutually parallel microchannels (104) defining a first region (102) of the microchannel structure (100) having an approximately rectangular cross-sectional shape having a greater width (Bs) compared to a height (Bs); Hs), and c. two laterally extending from a surface surrounding the first region (102) from a sidewall (106) extending outwardly of the height (Hs) and extending parallel to a longitudinal axis of the first region (102) and d. a lamellar structure (120), comprising: e. at least a first region (122) in a first plane providing a first interface for the first microchannel structure (1; 100), f. at least one second region (124) in a second plane, preferably providing a second bonding surface for the second microchannel structure (1; 100), wherein a central depression (130) is provided in the first (122) and second regions (124) adapted to the microchannel structure (1; 100) in the first region (102), g. at least one first inclined portion (126) disposed at a first end at the first portion (122) and at an opposite second end at the second portion (124), and h. at least one second oblique region (128) disposed at a first end at the first region (122) or at a further, adjacent, first region (122) and at an opposite second end at the second region (124) where i. the at least one first oblique region (126) on a first side with the first region (122) has a first angle α of less than 90 ° and on one of the first side opposite second side with the second region (124) includes a second angle β smaller than 90 °, and j. the at least one second obliquely extending region (126) on a first side with the first region (122) or the further first region (122) has a third angle γ of less than 90 ° and on a second side opposite the first side the second region (124) includes a fourth angle δ less than 90 °, where k. the two microchannel structures (1; 100) are connected to one another via the lamellar structure (120) and extend parallel to one another, the lamellar structure (120) having a width which is at least one width of the microchannel structure (100) and the lamellar structure (120) is in contact with the microchannel structure (100) over the entire width of the microchannel structure (100).

Component composite (140 ') consisting of: a. a plurality of elongated rectilinear wing tube structures (200), each al. a central tube (210) with a round, curvilinear or angular cross-section and a2. two oppositely disposed and laterally of the central tube

(210) have outwardly extending wings (220) that are parallel to a longitudinal axis of the central tube (210), and b. a lamellar structure (120 ') comprising: b1. at least a first region (122 ') in a first plane that provides a first connection surface for the first winglet structure (200), b2. at least one second region (124 ') in a second plane providing a second connection surface for the second winglet structure (200), wherein in the first (122') and second region (124 ') a central depression (130'; ) adapted to a shape of the tube of the wing tube structure (200); b3. at least one first inclined portion (126 ') disposed at a first end at the first portion (122') and at an opposite second end at the second portion (124 '), and

At least one second oblique region (128 ') having a first end at the first region (122') or another, adjacent, first region (122 ') and at an opposite second end at the second region (124'). is arranged, with bS. the at least one first obliquely extending region (126 ') at a first side with the first region (122') has a first angle α of less than 90 ° and a second side opposite the first side with the second region (124 ') second angle β less than 90 °, and b6. the at least one second obliquely extending region (126 ') at a first side with the first region (122') or the further first region (122 ') has a third angle γ smaller than 90 ° and at a second side opposite the first side with the second region (124 ') includes a fourth angle δ smaller than 90 °, wherein c1. the two hoop ear structures (200) are connected to one another via the lamellar structure (120 ') and run parallel to one another and c2. the fin structure (120 ') has at least a width corresponding to a width of the wing tube structure (200), and c3. the dimple structure (120 ') is in contact with the wing tube structure (200) over the entire width of the wing tube structure (200). 3. The component assembly (140) according to claim 1 or 2, in which the lamellar structure (120; 120 ') is fastened to the microchannel structures (1; 100) or the wing tube structures, for example by means of soldering. 4. A composite component according to claim 1, are rounded in the edges (108) of approximately rectangular cross-sectional shape. 5. The composite component of claim 1, wherein the lateral extent of the at least one wing corresponds to approximately one-half the width of the first area.

6. A composite component according to any one of claims 4 to 5, wherein a thickness (D) of the at least one vane (106) corresponds to about one quarter of the height (Hs) of the first region (102).

7. A composite component according to one of the preceding claims, whose microchannel structure or its flight structure (200) is made in one piece by extrusion from aluminum.

8. component assembly according to claim 1 or 2, the lamellar structure of a plurality of first (122;

122 ') and second regions (124; 124') and a plurality of first oblique regions (126; 126 ') and a plurality of second oblique regions (128; 128'), the first oblique region (126; ') is arranged with the first end at the first end of the first region (122, 122') and with the opposite second end at the first end of the second region (124, 124 ') and in the second inclined region (128; 128 ') having the first end at the second end of the adjacent first portion (122; 122') of the plurality of first portions (122; 122 ') and the opposite second end at the second end of the second portion (124; 124 ') is arranged.

9. component assembly according to claim 8, in which the first angle α and the second angle ß and / o of the third angle γ and the fourth angle δ are equal.

10. A composite component according to one of the claims 8 to 9, in which the first, the second, the first oblique and / or the second oblique region are straight, wavy or drawing harmonicaformig or have any other shape or combinations thereof.

11. A composite component according to claim 2, 3 or 7 to 10 in combination with claim 2, in which the plurality of elongated rectilinear wing tube structures (200) arranged in a meandering course parallel to each other and liquid-conducting in series with each other, leaving a fluid inlet with an inlet and a

Liquid outlet with an output of the meandering course of the wing tube structures (200) is connectable.

12. Heat exchanger (ISO) comprising: a. a first manifold (152) for supplying a fluid and a second manifold (154) for discharging a fluid and b. a composite component (140) according to one of the claims 1, 3 to 10 in combination with claim 1, wherein c. the microchannels (104) of each microchannel structure (1; 100) are in fluid communication with the first manifold (152) at a first end and in flow communication with the second manifold (154) at a second end.

13. A heat exchanger (150 ') comprising: a feed tube (156') for supplying a fluid and a discharge tube (158 ') for discharging a fluid and a composite component (140') according to one of the claims 2, 3, 8 in combination with Pa - tentanspruch 2, 9 in combination with the claims 8 and 2 and 10 in combination with the claims 8 and 2 or 9, 8 and 2, in which the central tubes of the wing tube structures (200) are successively interconnected to a flow connection between the feed tube and the discharge tube and in which the plurality of elongated rectilinear wing tube structures (200) are arranged in a meandering course parallel to each other so that the feed tube is provided with an entrance and the discharge tube with an exit of the meandering flight of the wing tube. Structures (200) is connected.

14. Heat exchanger (150 ') according to claim 13, in which at least two meandering profiles of the wing tube structures (200) are arranged parallel to each other and flat side by side and in fluid communication with each other, wherein preferably the wings (220) of the Flügelrohr- structures (200 ) are arranged approximately perpendicular to a plane spanned by the meandering courses of the wing tube structures (200).

15. A manufacturing method of a microchannel structure (100), comprising the step of:

Extruding (A) a microchannel structure (100) comprising a plurality of microchannels (104) extending parallel to one another, which define a first region (102) of the microchannel structure (100), and at least one, preferably two, oneself laterally extending from a surface surrounding the first region (102) outwardly extending wing (106), which runs parallel to a longitudinal axis of the first region (102), preferably made of aluminum.

16. A manufacturing method of a lamellar structure (120) comprising the step of: a. Providing (B) at least a first region (122) providing a first connection surface for a first microchannel structure (1; 100) or a first wing tube structure, and at least one second region (124), preferably a second connection surface for a second microchannel structure (1; 100) or a second wing tube structure, then

Arranging (C) a first inclined portion (126) having a first end at the first portion (122) and an opposite second end at the second portion (124) such that the at least one first inclined portion (126) is at a first Side with the first region (122) a first angle α less than 90 ° and at one of the first side opposite set second side with the second region (124) includes a second angle ß smaller than 90 °, and

Arranging (D) a second oblique region (128) having a first end at the first region (122) or another, preferably adjacent, first region (122) and at an opposite second end at the second region (124). The manufacturing method of a fin structure (120) according to claim 16, wherein the step of arranging (D) the second inclined portion (128) is performed so that the second inclined portion (128) is at a first side with the first portion (122) or the further first region (122) includes a third angle γ of less than 90 ° and, on a second side opposite the first side, with the second region (124) a fourth angle δ of less than 90 °.

The manufacturing method of a fin structure (120) according to claim 17, wherein the step of providing (B) comprises providing a plurality of first (122) and second regions (124) and the steps of arranging (C, D) the first (126) and second oblique regions (128) are repeated several times.

19. The manufacturing method of a fin structure (120) according to claim 18, wherein arranging (C) of the first inclined portion (126) is such that the first inclined portion (126) is connected to the first end at the first end of the first the first region (122) and with the opposite second end at the first end of the second region (124) is arranged and arranging (D) of the second oblique region (128) is carried out so that the second inclined

A portion (128) having the first end at the second end of the adjacent first portion (122) of FIG A plurality of the first regions (122) and with the opposite second end at the second end of the second region (124) is arranged.

20. A manufacturing method of a fin structure (120) according to one of the claims 16 to 19, comprising the further step: d. Providing (E) a central depression (130) in the first (122) and / or second region (124) which is preferably connected to a microchannel structure (1; 100), in particular to a first region (102) of a microchannel structure (1; Structure (100) according to one of claims 1 to 7, or adapted to a wing tube structure.

21. A manufacturing method of a fin structure (120) according to one of the claims 16 to 20, wherein the steps B to E are realized by bending a sheet metal layer. 22. A manufacturing method of a component composite (140) according to one of the claims 1 to 11, comprising: a. Providing (F) at least two microchannel structures (1; 100) or at least two wingpipe structures (200) and a lamellar structure (120), then b. at least partially connecting (G) the two microchannel structures (1; 100) or the two wing tube structures by means of the lamellar structure (120), for example by means of soldering, gluing or welding the lamellar structure (120). 23. The manufacturing method of a component assembly (140) according to claim 22, wherein the step of providing (F) comprises providing a plurality of microchannel structures (1; 100) or wing tube structures (200) and lamellar structures (120) and the The step of bonding (G) comprises at least partially connecting each microchannel structure (1; 100) of the plurality of microchannel structures (1; 100) to the respective adjacent microchannel structure (100) by means of a respective lamellae Structure (120) or each wing tube

Structure (1; 100) of the plurality of wing tube structures (1; 100) with the respectively adjacent wing tube structure (100) by means of a respective lamellar structure (120).

24. A manufacturing method of a heat exchanger (150) according to claim 12 comprising: a. Providing (H) a first manifold (152), b. Providing (I) a second manifold (154), c. Providing (J) a composite component (140) according to one of the claims 1, 3, 4, 5, 6, 7, 8, 9, 10, then d. Connecting (K) the microchannels (3; 104) of each microchannel structure (1; 100) at a first end to the first manifold (152) and at a second end to the second manifold (154).

25. A manufacturing method of a heat exchanger (150) according to claim 13, comprising: a. Providing (H) a supply pipe (156 ') for supplying a fluid and, b. Providing (I) a discharge pipe (158 ') for discharging a fluid, c. Providing (J) a component composite (140) according to one of the claims 2,3,7-11, according to d. Connecting (K) the central tubes of the wing tube structures (200) sequentially with each other to provide flow communication between the feed tube and the discharge tube and to arrange the plurality of elongate rectilinear wing tube structures (200) in a meander shape parallel to each other in that the supply pipe is connected to an inlet and the discharge pipe is connected to an outlet of the course of the wing pipe structures (200).

26. Condenser consisting of i. at least two, preferably at least three, subunits each with a. a plurality of elongate, rectilinear wing tube structures, each al. a central tube with a round, curvilinear or square cross-section and a2. two oppositely disposed and laterally extending from the central tube outwardly extending wings which are parallel to a longitudinal axis of the central tube, and b. a lamellar structure, comprising: b at least a first region in a first plane, which provides a first contact zone for the first wing tube structure, b2. at least one second region in a second plane providing a second contact zone for the second wing tube structure, wherein in the first and second regions a central depression is provided which is adapted to a shape of the tube of the wing tube structure, b3. at least one first oblique region disposed at a first end at the first region and at an opposite second end at the second region, and at b4. at least one second oblique region arranged with a first end at the first region or a further, adjacent, first region and with an opposite second end at an adjacent second region or at the second region, wherein b5. two wing tube structures are connected to each other via the lamellar structure and run parallel to each other, so that the wings of a subunit are arranged in parallel planes, and c1. the lamellar structure has at least a width corresponding to a width of the Flügelrohr- structure, and c2. the lamellar structure is in contact with the wing tube structure across the width of the wing tube structure, the subunits being juxtaposed and, during operation of the condenser, directing a direction of flow of air flowing over the lamellar structure of the condenser approximately perpendicular to the lamellar structure and the liquefier wtiterhin comprises a supply pipe for supplying a fluid, which is connected to a first end of the plurality of the wing tube structures of at least one of the subunits and a discharge pipe to Discharging a fluid connected to a second end of the wing tube structures opposite to the first end of at least one of the subunits, wherein iv. the inner diameter of the central tube of the wing tube structure is at least 3 mm, the outer diameter of the central tube of the wing tube structure is at least 4 mm and a width of the wing tube structure is preferably <25 mm.

27. Condenser according to claim 26, wherein the liquefier has at most six subunits.

28. Condenser according to one of the claims 26 or 27, wherein a distance between two wing tube structures of the same subunit is between 10 and 12 mm.

29. Liquefier according to one of the claims 26 to 28, wherein the average distance between two successive first and / or second regions of the lamellar structure is 3 to 9 mm.

30. A condenser according to any one of claims 26 to 29, wherein the distance between central tubes of adjacent subunits is 25 to 35 mm.

31. Condenser according to one of the claims 26 to 30, wherein a width of the condenser is at right angles to the flow direction of the air flowing through the lamellar structure of the condenser 200 to 250 mm, a height of the condenser perpendicular to the flow direction of the flowing over the lamellar structure of the condenser air 100 to 150 mm and a depth of the condenser in the flow direction of the air flowing through the lamellar structure of the condenser 80 to 150 mm.

32. Evaporator with, preferably exactly, two elongate rectilinear wing tube structures, each al. a plurality of central tube sections with a round, curvilinear or angular cross section and a2. two wings disposed opposite each other and extending laterally outwardly from the central tube section, which are parallel to a longitudinal axis of the central tube section, with the wings of a respective wing tube structure arranged in the same plane, and the evaporator further comprises a lamellar structure comprising: bl. at least a first region in a first plane providing a first contact zone for the first winglet structure, b2. at least one second region in a second plane providing a second contact zone for the second wing tube structure, wherein in the first and second regions a central depression is provided which is adapted to a shape of the tube of the wing tube structure, b3. at least one first oblique region disposed at a first end at the first region and at an opposite second end at the second region, and at b4. at least one second inclined region, which is arranged with a first end at the first region or a further, adjacent, first region and with an opposite second end at an adjacent second region or at the second region, wherein the two hills Structures are connected to each other via the lamellar structure and run parallel to each other and c2. the lamellar structure has at least one width corresponding to a width of the wing tube structure, and c3. the lamellar structure is in contact with the wing tube structure over the width of the wing tube structure as well as with a plurality of tube sections of the respective wing tube structure, wherein dl. during operation of the evaporator, a flow direction of a fluid flowing over the lamellar structure of the evaporator is oriented approximately at right angles to the lamellar structure, and d2. the outer diameter of the central tube of the wing tube structure is 6 to 8 mm, with a wall thickness of 0.5 mm and a width of the wing tube structure is 25 to 30 mm

33. The evaporator of claim 32, wherein a distance between the vanes of the first and second wing tube structure is about 20 mm.

34. An evaporator according to any one of claims 32 to 33, wherein the width of the wing tube structure is ≤ 30 mm.

35. An evaporator according to any one of claims 32 to 35, wherein there is at least in part a cavity between the vanes of the wingpipe structure and the fin structure provided with a means for resisting thawing.