EP3491323B1 - Heat exchanger having a micro-channel structure or wing tube structure - Google Patents

Description

1. Field of the invention

The present invention relates to a component composite comprising a microchannel structure or wing tube structure and a fin structure, a heat exchanger with the component composite and the respective manufacturing methods.

2. Background of the invention

Microchannel structures, for example for heat exchangers, are known in the prior art. An exemplary embodiment of a microchannel structure 1 according to the prior art is shown in the Figures 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 (cf. Fig. 2 ). Therefore, only the outer surface of the microchannel structure is available for heat exchange with a medium flowing around the microchannel structure.

In order to increase the outer surface of the microchannel structure 1, which is available for heat dissipation, the Figures 3 and 4 shown lamella structure 10 is used. The lamella structure 10 has the shape of an accordion with a width B _L and a height H _L . The lamella structure 10 in combination with two microchannel structures 1 running parallel to one another results in a component assembly 20, wherein in a heat exchanger the component assembly 20 can also have a plurality of microchannel structures 1 which are connected to one another via corresponding lamella structures 10. The surface area of the microchannel structure 1 which is available for heat dissipation is thus increased accordingly by the lamella structure 10.

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

A heat exchanger with a wing tube structure is in EN 10 2012 005 513 A1 The heat exchanger for removing heat from a medium has at least one serpentine-shaped wing tube arranged in a housing, the straight wing sections of which are arranged such that the wings of the wing sections enclose an angle in the range of 10° ≤ α ≤ 30° with a flow direction.

WO 2012/142070 A1 describes a component assembly according to the preamble of claim 2 in a heat exchanger with a plurality of tubes which are arranged substantially transversely to a direction of air flow through the heat exchanger and are arranged in a plurality of rows of tubes which extend substantially along the direction of air flow. The heat exchanger further comprises a plurality of webs which are formed substantially integrally with two or more tubes of the plurality of tubes, each web extending between and being connected to adjacent tubes of the plurality of tubes. At least one tube of the plurality of tubes has a cross-section with an aspect ratio of more than 1:1 relative to a substantially horizontal web.

A heat exchanger with microchannel structure goes out EP 2 966 391 A1 The heat exchanger comprises a gas circuit and a coolant circuit enclosed in a vessel, and turbulators or turbulence generators arranged in the coolant circuit between tubes to generate turbulence of the coolant flow in use, which improves the thermal efficiency of the heat exchanger. The turbulators are integrally formed in a single turbulator plate that extends across a plurality of tubes.

Finally, WO 2014/103268 A1 a component assembly according to the preamble of claim 1. This is to provide a heat exchange tube with a water drainage function that facilitates the assembly of a heat exchanger, and also a method for producing a heat exchange tube that facilitates the processing of the heat exchange tube. To solve this problem, a corrugated fin heat exchanger is provided. This is obtained by arranging a plurality of flat heat exchanger tubes arranged parallel to one another in the horizontal direction and between a pair of opposing distribution tubes and connecting corrugated fins between the heat exchanger tubes in which mountain-valley folds are alternately and repeatedly formed. The heat exchanger tubes are equipped with a flat tube body having a passage for a heating medium, a pair of flanges extending at both ends in the direction of the width of the tube body, and cut and raised parts obtained when the two flanges are cut and raised into an inclined shape and provided in a row at an appropriate distance along the longitudinal direction of the tube body. The two cut and raised parts have the same inclination angle and the inclination directions of the two cut and raised parts are asymmetrical at the two ends in the width direction of the pipe body.

The object of the present invention is to provide a component composite consisting of a micro-channel or wing tube structure in combination with a fin structure that is optimized with regard to heat transfer, so that it can also be used in high-performance devices, such as a heat exchanger of a motor vehicle, can be used cost-effectively. Furthermore, it is an object of the present invention to describe a corresponding heat exchanger and the associated manufacturing methods.

3. Summary of the invention

The above object is achieved by a component composite comprising a microchannel structure and a fin structure according to patent claim 1 and a wing tube structure and a fin structure according to patent claim 2, as well as by a heat exchanger according to dependent patent claims 7 and 8. The object is also achieved by a manufacturing method for a microchannel structure according to independent patent claim 9, a manufacturing method for a fin structure according to independent patent claim 10, a manufacturing method for a component composite according to independent patent claim 11, and a manufacturing method for a heat exchanger according to independent patent claims 12 and 13. In addition, the above object is achieved by a condenser according to dependent patent claim 14 and an evaporator according to dependent patent claim 15. Further advantageous embodiments emerge from the following description, the drawings, and the appended patent claims.

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

The first region consists of a plurality of microchannels running parallel to one another, which define a fluid flow direction. Microchannels in the sense of the present invention are channels with a diameter ≤ 1 mm. The first region is usually produced by extrusion, for example from aluminum.

In addition, to increase the surface available for heat dissipation, at least one wing is provided which extends laterally outwards from a surface enveloping the first region. Lateral in this context means that the at least one wing extends transversely to the flow direction or the direction of the microchannels. The at least one wing preferably extends continuously over essentially the entire length of the first region. An advantage of this procedure is that, compared to the known prior art, an alternative solution is created for increasing the surface available for heat dissipation, which is not coupled to stacking several 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 region. In this way, the first region and the at least one wing form a one-piece element, so that an additional connection of the at least one wing to the first region can be omitted.

One advantage is therefore that a larger surface area is provided for heat transfer compared to known microchannel structures, so that the efficiency of the microchannel structure according to the invention is also increased compared to known microchannel structures. A disadvantage to be mentioned is the larger installation space that the microchannel structure according to the invention requires due to the at least one wing for the same number of microchannels.

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 enveloping the first region. In this way, a further increase in the surface area for heat transfer can be achieved.

Furthermore, the first region has an approximately rectangular cross-sectional shape, which has a greater width compared to a height, and the at least one wing extends from the surface enveloping the first region from a side wall that determines the height, preferably in the middle. In the case of two wings arranged opposite one another, one wing extends from a side wall, preferably in the middle. In this way, when the microchannel structure according to the invention is used, for example in a heat exchanger, there is good flow through a heat transfer medium flowing at a right angle to the fluid flow direction.

The above effect is further improved by rounding 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 around the microchannel structure according to the invention and a possible resulting flow separation can be avoided.

In addition, the lateral extension of the at least one wing outwards corresponds to approximately half the width of the first region. Furthermore, a thickness of the at least one wing is preferably equal to a quarter of the height of the first region. With these particularly advantageous proportions, the surface can be increased by up to 40% compared to known microchannel structures or to the first region alone.

An advantageous lamellar structure for a microchannel structure, in particular for a microchannel structure as described above, comprises: at least one first region in a first plane, which provides a first connecting 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 obliquely running 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 running region, which is arranged with a first end on the first region or another, preferably adjacent, first region and with an opposite second end on the second region, wherein the at least one first obliquely running region encloses a first angle α of less than 90° with the first region on a first side and a second angle β of less than 90° with the second region on a second side opposite the first side. The first angle α and the second angle β are therefore alternating angles. In relation to the use with a microchannel structure, in particular with a microchannel structure according to the invention, the contact area with the first region, preferably with the entire microchannel structure, is increased by the first and/or the second region. In this way, the heat from the first area or the microchannel structure can be dissipated better compared to the known lamellar structures.

In one embodiment of the lamella structure, the at least one second obliquely running region forms a third angle γ of less than 90° on a first side with the first region or the further first region, and a fourth angle δ of less than 90° on a second side opposite the first side with the second region. It is also advantageous if the second obliquely running region has a second inclination direction opposite to a first inclination direction of the first obliquely running region in relation to a plane perpendicular to the first and/or second plane. The first and second inclination directions are preferably mirrored on the vertical plane, but this is not a mandatory requirement. An advantage of this embodiment is that there are now at least two obliquely running regions which have different inclination directions and different or identical inclination angles in relation to the vertical plane. In this way, the surface area available for heat dissipation can be further increased when used with a microchannel structure.

According to a further embodiment, the lamella structure has a plurality of first and second regions as well as a plurality of first obliquely running regions and a plurality of second obliquely running regions. In this case, it is particularly preferred if the first obliquely running 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 obliquely running region is arranged with the first end at the second end of the adjacent first region from the plurality of first regions and with the opposite second end at the second end of the second region. This has the advantage that heat dissipation can be particularly efficient when used with a microchannel structure by enlarging the contact area.

In other words, the lamella structure is constructed in such a way that a distance between two first regions is covered by a second region when the arrangement is viewed perpendicular to the first or second plane. The distance between the two first regions is smaller than the length of the second region. This also applies in reverse 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. Likewise, the dimensions of the first and second oblique regions are preferably the same.

According to a further embodiment of the lamella 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 that run parallel to one another. In this way, a particularly uniform structure is created, which has a beneficial effect on heat transfer.

In another embodiment of the lamella structure, the first, the second, the first slanted and/or the second slanted area are straight, wave-shaped or accordion-shaped or these areas each have any other shape or combinations thereof. Due to these design options, the areas can be specifically adapted to the requirements of the respective applications with regard to heat dissipation.

According to a further embodiment of the lamella 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 wing tube structure. With this embodiment, the lamella structure is adapted in a particularly advantageous manner to the microchannel structure and the wing tube structure, so that contact for heat exchange between the lamella structure and the microchannel/wing tube structure is achieved as far as possible over the entire width of the microchannel/wing tube structure and/or the lamella structure. The heat exchanger is further supported by the fact that the depression is provided as an opening or as a flat shape. In a flat shape, the depression is formed in the lamella material without breaking through the lamella surface. This provides a certain size of a contact surface. In the case of a breakthrough, the contact surface is reduced to the edge of the breakthrough, which is connected to the microchannel 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 wing tube structure and an inventive Lamellar structure, wherein the two microchannel structures or the wing tube structures are at least partially connected to one another via the lamellar structure, and wherein the microchannel structures or wing tube structures preferably run parallel to one another. 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 explanations.

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 of which has a plurality of microchannels running parallel to one another, which define a first region of the microchannel structure, which has an approximately rectangular cross-sectional shape, which has a greater width compared to a height, and two wings extending laterally outward from a surface enveloping the first region from a side wall determining the height, which wings run parallel to a longitudinal axis of the first region, and a lamellar structure, which comprises the following features: at least one first region in a first plane, which provides a first connecting surface for the first microchannel structure, at least one second region in a second plane, which preferably provides a second connecting surface for the second microchannel structure, wherein a central recess is provided in the first and second regions, which is adapted to the microchannel structure in the first region, at least one first obliquely running 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 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 obliquely extending region encloses a first angle α of less than 90° with the first region on a first side and a second angle β of less than 90° with the second region on a second side opposite the first side, and the at least one second obliquely extending region encloses a third angle γ of less than 90° with the first region or the further first region on a first side and a fourth angle δ of less than 90° with the second region on a second side opposite the first side, wherein the two microchannel structures are connected to one another via the lamellar structure and run parallel to one another, wherein the lamellar structure has a width which corresponds to at least one width of the microchannel structure and the lamellar structure is in contact with the microchannel structure over the entire width of the microchannel structure.

According to the other embodiment, the component assembly consists of a plurality of elongated, straight-line wing tube structures, each of which has a central tube with a round, curvilinear or rectangular line cross-section and two wings arranged opposite one another and extending laterally outward from the central tube, which run parallel to a longitudinal axis of the central tube, and a lamella structure comprising the following features: at least a first region in a first plane that provides a first connection surface for the first wing tube structure, at least one second region in a second plane that provides a second connection surface for the second wing tube structure, wherein a central recess is provided in the first and second regions that is adapted to a shape of the tube of the wing tube structure, at least one first obliquely running region that 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 running region that 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 obliquely running region encloses a first angle α of less than 90° with the first region on a first side and a second angle β of less than 90° with the second region on a second side opposite the first side, and the at least one second obliquely running region encloses a third angle γ of less than 90° with the first region or the further first region on a first side and a third angle γ of less than 90° with the first side opposite second side with the second region encloses a fourth angle δ of less than 90°, wherein the two wing tube structures are connected to one another via the slat structure and run parallel to one another and the slat structure has at least a width which corresponds to a width of the wing tube structure, and the slat 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, the first regions of which preferably run parallel to one another, with each microchannel structure being at least partially connected to the respective adjacent microchannel structure via a lamella structure according to the invention. In this way, any number of microchannel or wing tube structures can be stacked on top of one another for use in a later heat exchanger, with a respective lamella structure being present between the microchannel structures. The lamella structure is preferably attached to the microchannel structures or wing tube structures, for example by means of soldering, welding, gluing.

According to a further preferred embodiment of the present invention, the component assembly has the majority of the elongated, straight-line wing tube structures in a meandering course parallel to one another and connected to one another in a fluid-conducting manner, so that a fluid inlet can be connected to an inlet and a fluid outlet to an outlet of the meandering course of the wing tube structures. This preferred meandering arrangement forms the basis for an efficient and fluid-saving household of coolant that is used in the component assembly and later heat exchanger. This is because the central tube of the elongated, straight-line wing tube structures forms a curved end or Connection area without wings the fluid connection to the adjacent elongated straight wing tube structure. Preferably, the individual curved connection areas require a smaller volume of cooling fluid to supply the wing tube structures than is the case with a first and a second distribution pipe in combination with the microchannel structures.

A heat exchanger according to the invention comprises a first distributor pipe for supplying a fluid and a second distributor pipe for discharging a fluid, as well as a component assembly according to the invention, wherein the microchannels of each microchannel structure are in flow connection with the first distributor pipe at a first end and in flow connection with the second distributor pipe at a second end. With regard to the advantages, reference is made to the above statements on the microchannel structure according to the invention and on the lamella structure according to the invention.

A further heat exchanger according to the invention comprises a supply pipe for supplying a fluid and a discharge pipe for discharging a fluid as well as a component assembly with at least two wing tube structures connected via a preferred lamella structure according to the above description, wherein the central tubes of the wing tube structures are connected one behind the other in the flow direction in order to provide a flow connection between the supply pipe and the discharge pipe.

The heat exchanger with vane tube structures uses known design principles of a heat exchanger of this type. The fin structure advantageously extends at least over the entire width of the vane tube, i.e. transversely to the longitudinal axis of the vane tube. This transverse contact between the vane tube structure or microchannel structure and the fin structure extends over the maximum width. This contact area is preferably increased by increasing the opposing contact surfaces of the vane tube/microchannel structure and the fin structure. This applies to contact lines and/or contact surfaces in the area of the vanes and/or the tube or the area of the interconnected microchannels. Furthermore, the central tubes of the vane tube structures are connected to one another one after the other in order to provide the flow connection between the supply tube and the discharge tube for coolant. Within this assembly, the majority of the elongated, straight-line vane tube structures are arranged parallel to one another in a meandering course. Thus, due to this meandering arrangement, the multiple vane tube structures span an approximately flat surface. The supply pipe is connected to the inlet and the discharge pipe is connected to the outlet of the meandering course of the wing tube structures. According to a preferred embodiment, at least two meandering courses of the wing tube structures are arranged parallel to each other and flat next to each other and are in flow connection with each other. In addition, the wings of the wing tube structures are preferably approximately perpendicular to the plane/planes spanned by the meandering courses of the wing tube structures.

An advantageous manufacturing method for a microchannel structure comprises the step of extruding a microchannel structure consisting of a plurality of microchannels running parallel to one another, which define a first region of the microchannel structure, and at least one, preferably two, wings extending laterally outward from a surface enveloping the first region, which wings run parallel to a longitudinal axis of the first region, preferably made of aluminum. A microchannel structure according to the invention is produced by means of the manufacturing method according to the invention. With regard to the advantages, reference is therefore made to the microchannel structure according to the invention.

An advantageous manufacturing method of a lamella structure comprises the steps of: providing at least one first region which provides a first connecting surface for a first microchannel structure or a wing tube structure, and at least one second region which preferably provides a second connecting surface for a second microchannel structure or a second wing tube structure, then arranging a first obliquely running region with a first end on the first region and with an opposite second end on the second region such that the at least one first obliquely running region forms a first angle α of less than 90° with the first region on a first side and a second angle β of less than 90° with the second region on a second side opposite the first side, and arranging a second obliquely running region with a first end on the first region or another, preferably adjacent, first region and with an opposite second end on the second region. The lamella structure according to the invention can be manufactured using this manufacturing method. Therefore, with regard to the corresponding advantages, reference is made to the explanations regarding the lamella structure.

According to a further embodiment, the step of arranging the second obliquely running region is carried out such that the second obliquely running region encloses a third angle γ of less than 90° with the first region or the further first region on a first side and a fourth angle δ of less than 90° with the second region on a second side opposite the first side.

Furthermore, the step of providing comprises providing a plurality of first and second regions and the steps of arranging the first and second obliquely running regions are repeated several times. Furthermore, the arranging of the first obliquely running region is preferably carried out such that the first obliquely running 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 arranging of the second obliquely running region is carried out such that the second obliquely running region is arranged with the first end at the second end of the adjacent first region from the plurality of first regions and with the opposite second end at the second end of the second region.

In addition, the method for producing a lamella structure comprises the further step of providing a central depression 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 according to the invention, or a wing tube structure. According to a first alternative, the first and/or the second region can already have a depression for the microchannel structure, in particular for a first region thereof, when the regions are initially provided. If the lamella structure is assembled from individual parts, the depression can be created, for example, before the arrangement of the first and/or the second obliquely running region. According to a further alternative, corresponding depressions can also be provided later.

In addition, the steps of the method of manufacturing the lamella structure according to the invention are carried out by bending a sheet metal layer. If the lamella structure is manufactured entirely from a sheet metal layer by bending, the above-mentioned depression is created either before or after bending in the areas that later correspond to the first and/or the second area. It is also conceivable to punch or cut out openings.

A manufacturing method of a component composite 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 lamella structure, for example by soldering, welding or gluing the lamella structure.

According to one embodiment, the step of providing in the manufacturing process of the component assembly comprises providing a plurality of microchannel/wing tube structures and lamella structures and the step of connecting comprises at least partially connecting each microchannel structure from the plurality of microchannel structures to the respective adjacent microchannel structure or each wing tube structure from the plurality of wing tube structures to the respective adjacent wing tube structure by means of a respective lamella structure (120).

A manufacturing method of a heat exchanger according to the invention comprises the steps of: providing a first distributor pipe, providing a second distributor pipe and providing a component assembly according to the invention and then connecting the microchannels of each microchannel structure at a first end to the first distributor pipe and at a second end to the second distributor pipe. the heat exchanger is made of a wing tube structure, then a supply pipe and a discharge pipe are first provided and connected to the wing tube structures, which have previously been connected one after the other - i.e. in series.

A condenser according to the invention consists of at least two, preferably at least three, subunits, each with a plurality of elongated, straight-line wing tube structures, each of which has a central tube with a round, curvilinear or angular line cross-section and two wings arranged opposite one another and extending laterally outwards from the central tube, which run parallel to a longitudinal axis of the central tube, and a lamella structure which comprises the following features: at least one first region in a first plane which provides a first contact zone for the first wing tube structure, at least one second region in a second plane which provides a second contact zone for the second wing tube structure, wherein a central recess is provided in the first and second regions which is adapted to a shape of the tube of the wing tube structure, at least one first obliquely running 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 running region which is arranged with a first end on the first region or a further, adjacent first region and with an opposite second end arranged on an adjacent second region or on the second region, wherein two wing tube structures are connected to one another via the lamella structure and run parallel to one another, so that the blades of a sub-unit are arranged in parallel planes, and the lamella structure has at least one width that corresponds to a width of the wing tube structure, and the lamella structure is in contact with the wing tube structure across the width of the wing tube structure, wherein the sub-units are arranged next to one another and, during operation of the condenser, a flow direction of air flowing over the lamella structure of the condenser is aligned approximately at right angles to the lamella structure, and the condenser further comprises a supply pipe for supplying a fluid, which is connected to a first end of the plurality of wing tube structures of at least one of the sub-units, and a discharge pipe for discharging a fluid, which is connected to a second end of the wing tube structures of at least one of the sub-units opposite the first end, wherein 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.

A condenser or condenser is generally a device in which a fluid flowing inside the central tube of the wing tube structure is converted from the gaseous state to the liquid state (condensation). In heat engines and refrigeration systems, condensers are used to liquefy the exhaust steam or the vaporous refrigerant. This enables a closed cycle process in these systems.

An advantage of the condenser according to the invention is the particularly compact design and the particularly efficient removal of heat by means of the wing tube structure in combination with the fin structure and the specific design and dimensioning. In an advantageous embodiment, the condenser therefore has a maximum of six sub-units.

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 consecutive first and/or second regions of the lamella structure is 3 to 9 mm. The distance between central tubes of adjacent subunits is also preferably 25 to 35 mm, preferably measured from tube center to tube center. With each of these features alone, a particularly compact design of the condenser can be achieved. These features in combination therefore lead to a particularly advantageous and efficient embodiment of the condenser.

Finally, it is preferred that the width of the condenser perpendicular to the flow direction of the air flowing over the lamella structure of the condenser is 200 to 250 mm, the height of the condenser perpendicular to the flow direction of the air flowing over the lamella structure of the condenser is 100 to 150 mm and the depth of the condenser in the flow direction of the air flowing over the lamella structure of the condenser is 80 to 150 mm. These dimensions mean that the condenser can also be used in household appliances such as a tumble dryer.

An evaporator according to the present invention comprises, preferably precisely, two elongated rectilinear wing tube structures, each having a plurality of central tube sections with a round, curvilinear or angular line cross-section and two wings arranged opposite one another and extending laterally outwards from the central tube section, which wings run parallel to a longitudinal axis of the central tube section, wherein the wings of a respective wing tube structure are arranged in the same plane, and the evaporator further comprises a fin structure comprising the following features: at least one first region in a first plane, which provides a first contact zone for the first wing tube structure, at least one second region in a second plane, which provides a second contact zone for the second wing tube structure, wherein a central recess is provided in the first and second regions, which is adapted to a shape of the tube of the wing tube structure, at least one first obliquely running 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 running region, having a first end at the first region or another adjacent first region and having 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 one another via the lamella structure and run parallel to one another, and the lamella structure has at least a width which corresponds to a width of the wing tube structure, and the lamella structure is in contact with the wing tube structure and with several tube sections of the respective wing tube structure over the width of the wing tube structure, wherein during operation of the evaporator a flow direction of air flowing over the lamella structure of the evaporator is aligned approximately at right angles to the lamella structure, and the outer diameter of the central tube of the wing tube structure is 6 to 8 mm, wherein a wall thickness is 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 vane tube structure is converted from the liquid state to the gaseous state. One advantage of the evaporator according to the invention, as with the condenser according to the invention, is its particularly compact design. In an advantageous embodiment, the condenser therefore has exactly two vane tube structures.

Each of the two vane tube structures comprises a plurality of tube sections with vanes. The tube sections with vanes of a respective vane tube structure are arranged such that the vanes are arranged in one plane. This distinguishes the evaporator according to the invention from the condenser according to the invention, for example, in which the vanes of a vane tube structure are arranged in parallel planes. In order to connect several tube sections with vanes of a vane tube structure to several tube sections with vanes of another vane tube structure, the lamella structure preferably comprises a plurality of central depressions, so that a lamella structure connects several tube sections with vanes of the first and second vane tube structures to one another.

In an advantageous embodiment, a distance between the blades of the first and second blade tube structure is approximately 20 mm. The width of the blade tube structure is also preferably ≤ 30 mm. In this way, a particularly compact design of the evaporator can be achieved.

Preferably, between the vanes of the vane tube structure and the fin structure, at least partially, there is a cavity provided with a means to resist thawing. In this way, the effectiveness of the evaporator can be further improved.

A detailed embodiment of the present invention will now be described with reference to the drawings. In the drawings, like reference numerals designate like components.

4. Brief description of the drawings

Figur 1

eine perspektivische Ansicht einer Mikrokanal-Struktur gemäß Stand der Technik

Figur 2

die Mikrokanal-Struktur aus Fig. 1 im Querschnitt

Figur 3

eine perspektivische Ansicht einer Lamellen-Struktur gemäß Stand der Technik,

Figur 4

die Lamellen-Struktur aus Fig. 3 im Querschnitt,

Figur 5

eine perspektivische Ansicht eines Bauteilverbunds bestehend aus mehreren Mikrokanal-Strukturen und Lamellen-Strukturen gemäß Stand der Technik,

Figur 6

den Bauteilverbund aus Fig. 5 in einer seitlichen Ansicht,

Figur 7

eine perspektivische Ansicht einer Ausführungsform einer erfindungsgemäß bevorzugten Mikrokanal-Struktur,

Figur 8

die Mikrokanal-Struktur aus Fig. 7 im Querschnitt,

Figur 9

eine perspektivische Ansicht einer bevorzugten Ausführungsform einer Lamellen-Struktur gemäß der vorliegenden Erfindung,

Figur 10

einen Querschnitt der Lamellen-Struktur aus Fig. 9,

Figuren 11 und 12

eine perspektivische Ansicht eines Bauteilverbunds bestehend aus Mikrokanal-Strukturen und Lamellen-Strukturen gemäß einer Ausfuhrungsform der vorliegenden Erfindung,

Figur 13

eine perspektivische Ansicht einer bevorzugten Ausführungsform eines Wärmetauschers gemäß der vorliegenden Erfindung,

Figur 14

einen Ausschnitt des Wärmetauschers aus Fig. 13 in Seitenansicht und

Figur 15

einen Ausschnitt des Wärmetauschers aus Fig. 14 und 13 zur Verdeutlichung eines Anschlusses eines ersten Bereichs an ein Verteilerrohr.

Figur 16

eine weitere bevorzugte Ausführungsform eines Bauteilverbunds mit einer Flügelrohr-Struktur und einer Lamellen-Struktur,

Figur 17

eine bevorzugte Ausführungsform einer weiteren Lamellen-Struktur,

Figur 18

eine Seitenansicht der Lamellen-Struktur aus Figur 17,

Figur 19

eine weitere bevorzugte Ausführungsform einer Lamellen-Struktur mit Kontaktflächen zu einem angrenzenden nicht gezeigten Flügelrohr,

Figur 20

eine Seitenansicht einer bevorzugten Ausführungsform eines Bauteilverbunds bestehend aus einer Lamellen-Struktur und einer Flügelrohr-Struktur,

Figur 21

eine weitere Seitenansicht des bevorzugten Bauteilverbunds gemäß Figur 20,

Figur 22

eine perspektivische Ansicht des Bauteilverbunds gemäß Figur 21,

Figur 23

eine vergrößerte perspektivische Ansicht eines Ausschnitts aus dem Bauteilverbund gemäß Figur 22,

Figur 24

eine perspektivische Ansicht eines erfindungsgemäß bevorzugten Wärmetauschers mit einem bevorzugten Bauteilverbund bestehend aus Flügelrohr-Strukturen und dazwischen angeordneten Lamellen-Strukturen,

Figur 25

eine erste perspektivische Ansicht eines erfindungsgemäß bevorzugten Verflüssigers,

Figur 26

eine zweite perspektivische Ansicht des erfindungsgemäß bevorzugten Verflüssigers,

Figur 27

eine Seitenansicht des erfindungsgemäß bevorzugten Verflüssigers,

Figur 28

eine Endansicht des erfindungsgemäß bevorzugten Verflüssigers,

Figur 29

eine erste perspektivische Ansicht eines erfindungsgemäß bevorzugten Verdampfers,

Figur 30

eine Seitenansicht des erfindungsgemäß bevorzugten Verdampfers,

Figur 31

eine zweite perspektivische Ansicht des erfindungsgemäß bevorzugten Verdampfers und

Figur 32

eine Explosionsansicht des erfindungsgemäß bevorzugten Verdampfers.

Show it:

Figure 1

a perspective view of a microchannel structure according to the prior art

Figure 2

the microchannel structure Fig.1 in cross section

Figure 3

a perspective view of a lamella structure according to the prior art,

Figure 4

the lamellar structure Fig.3 in cross section,

Figure 5

a perspective view of a component composite consisting of several microchannel structures and lamellar structures according to the state of the art,

Figure 6

the component assembly Fig.5 in a side view,

Figure 7

a perspective view of an embodiment of a preferred microchannel structure according to the invention,

Figure 8

the microchannel structure Fig.7 in cross section,

Figure 9

a perspective view of a preferred embodiment of a lamella structure according to the present invention,

Figure 10

a cross-section of the lamellar structure Fig.9 ,

Figures 11 and 12

a perspective view of a component assembly consisting of microchannel structures and lamellar structures according to an embodiment of the present invention,

Figure 13

a perspective view of a preferred embodiment of a heat exchanger according to the present invention,

Figure 14

a section of the heat exchanger Fig. 13 in side view and

Figure 15

a section of the heat exchanger Fig. 14 and 13 to illustrate a connection of a first area to a distribution pipe.

Figure 16

a further preferred embodiment of a component composite with a wing tube structure and a lamella structure,

Figure 17

a preferred embodiment of another lamella structure,

Figure 18

a side view of the slatted structure Figure 17 ,

Figure 19

a further preferred embodiment of a lamella structure with contact surfaces to an adjacent wing tube, not shown,

Figure 20

a side view of a preferred embodiment of a component assembly consisting of a lamella structure and a wing tube structure,

Figure 21

another side view of the preferred component assembly according to Figure 20 ,

Figure 22

a perspective view of the component assembly according to Figure 21 ,

Figure 23

an enlarged perspective view of a section of the component assembly according to Figure 22 ,

Figure 24

a perspective view of a heat exchanger preferred according to the invention with a preferred component assembly consisting of wing tube structures and fin structures arranged between them,

Figure 25

a first perspective view of a preferred condenser according to the invention,

Figure 26

a second perspective view of the condenser preferred according to the invention,

Figure 27

a side view of the condenser preferred according to the invention,

Figure 28

an end view of the preferred condenser according to the invention,

Figure 29

a first perspective view of an evaporator preferred according to the invention,

Figure 30

a side view of the evaporator preferred according to the invention,

Figure 31

a second perspective view of the evaporator preferred according to the invention and

Figure 32

an exploded view of the evaporator preferred 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, such as in an air conditioning system of a motor vehicle. The microchannel structure is also used in any high-performance devices that must ensure the most efficient heat transfer possible in the smallest possible space available.

Referring to the Figures 7 and 8 According to a preferred embodiment, a microchannel structure 100 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 next to one another, with the two middle microchannels having a substantially rectangular cross-sectional shape. The first region 102 therefore has an approximately rectangular cross-sectional shape overall. The two microchannels 104 on the outer sides have rounded edges 108. In particular, the rounded edges 108 serve to improve the flow through a heat transfer medium in conjunction with the wings 106 explained below, so that, for example, the flow can be as laminar as possible and flow separation in the first region 102 can be avoided.

On a surface enveloping the first region 102, two wings 106 are also provided, which extend laterally outward and run parallel to a longitudinal axis of the first region 102. The wings 106 extend essentially over the entire length of the first region 102. This means that the wings 106 do not extend all the way to the respective end of the first region 102, so that the first region 102 has a connecting region 110 at both axial ends. The connecting region 110 serves for a connection to a distribution pipe of a heat exchanger 150 or another corresponding device.

Out of Fig.8 a particularly advantageous proportionality of the first area 102 to the wings 106 can be seen. According to the Figures 7 and 8 a total width B total _of the microchannel structure 100 is made up of twice the width of a wing 106 and once the width B _S of the first region 102. The width of the two wings 106 together corresponds approximately to the width Bs of the first region 106. The ratio of the total width B _{total of} the microchannel structure 100 to the width B _S of the first region 102 is therefore approximately 2:1. The thickness D of the wings 106 is approximately a quarter of the height H _S of the first region 102.

As in the Figures 7 and 8 As can be seen, the wings 106 are arranged in particular centrally on a side wall of the surface surrounding the first region 102, which defines a height H _S 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 heat transfer. By means of this structure, a surface enlargement of approximately 40% is possible compared to the Figures 1 and 2 shown structure can be achieved. This also has a correspondingly beneficial effect on heat dissipation.

The Figures 9 and 10 show a preferred embodiment of a lamellar structure 120 for a microchannel structure 100. The lamellar 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 planes are parallel to one another. The first region 122 is connected to the second region 124 via a first straight inclined region 126. The first inclined region 126 encloses a first angle α < 90° with the first region 122. Likewise, the first inclined region 126 encloses a second angle β < 90° with the second region 124. The first angle α and the second angle β are alternating angles since they are present on opposite sides of the first inclined region 126 and on opposite sides of the first 122 and the second region 124. Due to the parallel arrangement of the first and second planes, the first α and the second angle β are equal. Furthermore, the first obliquely extending region 126 has a first inclination direction relative to a plane perpendicular to the first and/or second plane. This perpendicular plane runs transversely to a fluid flow direction, which becomes apparent when using the lamella structure 120 with the microchannel structure 1, 100. The structure resulting from this arrangement increases the size of the fluid flow in comparison to known accordion-shaped or S-shaped structures. Use with a microchannel structure 1, 100 a contact area with the microchannel structure 1, 100, so that in this way the heat dissipation can be further improved.

In order to continue the structure, a second straight, slanted region 128 is also provided. The second slanted region 128 forms a third angle γ < 90° with another, adjacent, first region 122 and a fourth angle δ < 90° with the second region 124. The third γ and fourth angle δ are again, as already described for the first slanted region 126, alternating angles. In relation to the vertical plane described above, the second slanted region 128 has a second inclination direction that is opposite to the first. In the embodiment shown, 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 slanted region 126 and the second slanted region 128 are the same. This also applies to all four angles α, β, γ, δ.

Further referring to the Figures 9 and 10 In other words, a plurality of first regions 122 are spaced apart from one another such that the distance between the first regions 122 is smaller than a length of the second regions 124. If the lamella structure 120 is viewed from a direction perpendicular to the first and second planes, then a second region 124 overlaps the distance between two first regions 122 and vice versa.

As also in the Figures 9 and 10 As can be seen, the first 122 and second regions 124 have a recess 130 in the middle for receiving the first region 102 of the microchannel structure 100. The first 126 and second regions 128 also have corresponding recesses in the contact areas with the first and second regions 122, 124. This results in a height H _LS in the middle region of the lamella structure 120 at the recess 130, which is correspondingly lower than the total height H _LGes of the lamella structure 120.

Since the lamellar structure 120 has a total width B _LGes which corresponds approximately to the width B _Ges of the microchannel structure 100, the projections 132 are formed at the edge regions of the lamellar structure 120. The resulting advantage becomes apparent when the Figures 11 and 12 be considered. It can be seen that the lamella structure 120 is in contact with the microchannel structure 100 over its entire width. In this way, 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 in such a way that the projections 132 of two lamella structures 120 arranged on the respective sides of the microchannel structure 1 touch each other and thus represent corresponding wings. In this case, the width of the recess would be 130 of the lamella 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 recess 130.

In the Figures 11 and 12 a component assembly 140 is shown according to an embodiment. The component assembly 140 consists of three microchannel structures 100, which are connected to one another via two lamella structures 120. The lamella structure 120 is fastened between the microchannel structures 100. This can be done, for example, by clamping between the microchannel structures 100 or by other types of fastening such as soldering to the respective microchannel structure 100. In comparison to the Figures 5 and 6 The known component assembly 20 shown can be combined with the component assembly 140 according to the Figures 11 and 12 A surface increase of approx. 43% can be achieved, which results in a correspondingly improved heat transfer.

The Figures 13 to 15 finally show a preferred embodiment of a heat exchanger 150. The heat exchanger 150 has a first distributor pipe 152 with a first connection 156 and a second distributor pipe 154 with a second connection 158. A fluid is supplied via one of the two connections 156, 158, while the fluid is discharged again via the other connection 158, 156.

A component assembly 140 is arranged between the two distributor pipes 152 and 154. The number of microchannel structures 100 in the component assembly 140 depends on the height of the distributor pipes 152, 154. In particular Fig. 15 shows that the connection region 110 is used as a wingless region of the microchannel structure 100 for connection to the respective distribution pipe 152, 154.

A further preferred embodiment of a component assembly 140' is shown Figure 16 This component assembly 140' consists of a further preferred embodiment of the lamella structure 120' already described above. This lamella structure 120' connects wing tubes 200 arranged opposite one another. Such wing tubes 200 consist of a central tube 210 with a round, curved or angular line cross-section. Furthermore, the central tube 210 has a wing 220 on each of two opposite sides, which extends in the radial direction from the central tube 210. The wings 220 extending radially outward run parallel to the longitudinal axis of the central tube 210 and thus of the entire wing tube structure.

At least two wing tube structures 200 arranged parallel to one another are connected to one another via a lamella structure 120' arranged between them. The lamella structure 120' has the same structural properties as have already been explained above in combination with the microchannel structure 1; 100. Accordingly, the first 122' and second regions 124' in the preferred embodiment of the Figure 16 and in the lamellar structures 120' of the Figures 17 and 18 a linear contact with the neighboring wing tube structures 200. The first obliquely running region 126' and the second obliquely running region 128' connect the two first and second straight regions 122' and 124', which run opposite one another in a straight line. In addition, the obliquely running regions 126' and 128' connect the two wings 220 arranged opposite one another and the central tube 210. In the same way as between the lamella structure 120 described above and the microchannel structure 1; 100, the lamella structure 120' thus establishes a heat-conducting contact with the wing tube structure 200. In this way, the lamella structure 120' increases the area of the wing structure 200 available for heat exchange.

As can be seen from the preferred embodiment of the lamella structure 120' in Figure 17 can be seen, it has a recess 130' in the first straight contact area 121'. This recess 130' is adapted to the shape of the central tube 210 in order to receive it in the recess 130'. While in the preferred embodiment of the Figure 17 the depression 130' is shown as a cut-out area from the straight area 122' of the lamella structure 120', it is also preferred to provide the depression 130' in a planar manner. For this purpose, the straight first area 122' is not provided as a tapered line-like contact area, but as a straight planar contact area, as shown in Figure 19 is shown schematically. The contact surface 122' shown there is flat and thus preferably rests against the central tube 210 and the wings 220 of the wing tube structure. Accordingly, it is also preferred to provide a flat recess (not shown) for the central tube 210 in the straight areas 122' and 124'.

As can be seen from the preferred embodiments of the component assembly 140' according to the Figures 20-23 can be seen, a plurality of wing tube structures 200 consisting of the wings 220 and a central tube 210 are arranged parallel to one another. Neighboring wing tube structures 200 with a central tube 210 and wings 220 are connected to one another via the respective intermediate lamella structure 120' in order to enlarge the heat-exchanging surfaces of the wing tube structure. In order to be able to create a fluid connection between the wing tubes 210, 220 arranged parallel to one another, the central tubes 210 are connected to one another via bent tube sections 230 without wings (see Figures 20 , 21 , 23 ). The component assembly 140' also comprises a supply pipe 156' and a discharge pipe 158' in the same way as was used in the heat exchanger 150 already described above. Accordingly, a cooling medium is introduced into the component assembly through the previously described supply pipe 156', while it is discharged via the discharge pipe 158'.

The wing tube structures 200 connected to one another according to the above arrangement form a meandering course. As a result, the wing tube structures 200 arranged parallel to one another approximately span a 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, the component assembly with only one plane or a plurality of planes of meanderingly connected wing tube structures arranged parallel to one another can preferably be used effectively in a heat exchanger.

A preferred embodiment of a heat exchanger 150' using at least one of the component assemblies 140' described above is shown in Figure 24 In this preferred heat exchanger 150', a first and a second component assembly 140', which, for example, in the Figures 21 and 22 shown, in parallel arrangement to each other. These two component assemblies 140' arranged parallel to each other are in fluid communication, so that a fluid supplied through the supply pipe 156' flows through both component assemblies 140' and is then discharged through the drain pipe 158'. With regard to the preferred embodiment of the Figure 24 it is also preferred to provide them only consisting of one component composite or with more than two component composites 140'. In the same way as in the Figures 16 , 20 , 21, 22 , 23 and 24 As can be seen, the blades 220 are arranged parallel to a flow direction S. The same applies to the obliquely running first and second regions 196'128' of the lamella structure 120'. These also run parallel to the flow direction S (see Figure 24 ).

A manufacturing method for the microchannel structure 100 according to the Figures 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, which define a first region 102 of the microchannel structure 100, and at least one, preferably two, wings 106 extending laterally outward from a surface enveloping the first region 102, which wings run parallel to a longitudinal axis of the first region 102, preferably made of aluminum.

A manufacturing method of a lamella structure 120 according to the Figures 9 and 10 comprises, as a first step, the provision (step B) of at least one first region 122, which provides a first connection surface for a first microchannel structure 1; 100, and at least one second region 124, which preferably provides a second connection surface for a second microchannel structure 1; 100. As a second, subsequent step (step C), the arrangement of a first obliquely running region 126 with a first end on the first region 122 and with an opposite second end on the second region 124 takes place such that the at least one first obliquely running region 126 encloses a first angle α of less than 90° with the first region 122 on a first side and a second angle β of less than 90° with the second region 124 on a second side opposite the first side. Furthermore, the manufacturing method comprises, before, after or at the same time as step C, the further step of arranging (step D) a second obliquely running region 128 with a first end on the first Region 122 or a further, preferably adjacent, first region 122 and with an opposite second end at the second region 124. The second obliquely running region 128 is arranged such that the at least one second obliquely running region 128 encloses a third angle γ of less than 90° with the first region 122 on a first side and a fourth angle δ of less than 90° with the second region 124 on a second side opposite the first side.

The provision (step B) preferably comprises the provision of a plurality of first 122 and second regions 124, and the steps of arranging (steps C and D) the first 126 and second obliquely running region 128 are repeated several times. In this way, the lamellar structure can be particularly advantageously adapted to a length of the microchannel structure. The arrangement (step C) of the first obliquely running region 126 is carried out such that the first obliquely running 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. The arrangement (step D) of the second obliquely running region 128 is carried out such that the second obliquely running region 128 is arranged with the first end at the second end of the adjacent first region 122 from the plurality of first regions 122 and with the opposite second end at the second end of the second region 124.

Furthermore, the step of providing (step E) a central depression 130 in the first 122 and/or second region 124 is provided. The central depression is preferably adapted to a microchannel structure 1; 100, in particular to a first region 102 of a microchannel structure according to the invention. The step of providing the depression 130 can generally take place before or after the provision of the first and second regions and before or after the arrangement of the first and/or the second obliquely running region. Steps B to E can be implemented by bending a sheet metal layer.

A manufacturing process of a component composite 140 according to the Figures 11 and 12 or 16 , 20 , 21, 22 comprises providing (step F) at least two microchannel structures 1; 100 according to the Figures 1 and 2 or 7 and 8 or of at least two wing tube structures 200 and a lamella structure 120 according to the Figures 9 and 10 . This is followed by the step of at least partially connecting (step G) the two microchannel structures 1; 100 or the two wing tube structures 200 by means of the lamella structure 120, for example by soldering, gluing or welding the lamella structure 120. The step of providing (step F) comprises providing a plurality of microchannel structures 1; 100 or wing tube structures and lamella structures 120 and the step of connecting (step G) comprises at least partially connecting each microchannel structure 1; 100 from the plurality of microchannel structures 1; 100 to the respective adjacent microchannel structure 100 by means of a respective lamella structure 120 or each wing tube structure 200 from the plurality of Wing tube structures 200 with the respective adjacent wing tube structure 200 by means of a respective lamella structure 120.

A manufacturing method of a heat exchanger 150 according to the Figures 13 to 15 comprises the steps: providing (step H) a first distributor pipe 152, providing (step I) a second distributor pipe 154 and providing (step J) a component assembly 140 according to the Figures 11 and 12 . The provision can take place in any order. After the provision (steps H, I and J) of all components, the connection (step K) of the microchannels 3; 104 of each microchannel structure 1; 100 takes place at a first end to the first distributor pipe 152 and at a second end to the second distributor pipe 154.

Alternatively, a manufacturing method of a heat exchanger according to Figure 24 the steps: 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 then connecting (step K) the central pipes of the wing tube structures 200 one after the other to provide a flow connection between the supply pipe and the discharge pipe and to arrange the plurality of elongated, rectilinear wing tube structures 200 in a meandering course parallel to one another, so that the supply pipe is connected to an inlet and the discharge pipe is connected to an outlet of the meandering course of the wing tube structures 200.

Now referring to the Fig. 25 to 28 a preferred embodiment of a condenser 200 is shown. A condenser or condenser is generally a device in which a fluid flowing inside the central tube of the wing tube structure is converted from the gaseous state to the liquid state (condensation). In heat engines and refrigeration systems, condensers are used to liquefy the exhaust steam or the vaporous refrigerant. This enables a closed cycle process in these systems.

The condenser 200 consists of four sub-units 202, 204, 206 and 208, each with a plurality of elongated, straight-line vane tube structures 210. Each vane tube structure 210 has a central tube 212 with a round cross-section and two vanes 214 arranged opposite one another and extending laterally outward from the central tube 212. The vanes 214 run parallel to a longitudinal axis of the central tube 212.

Furthermore, each subunit 202, 204, 206 and 208 comprises a lamella structure 220. The lamella structure 220 has at least a first region in a first plane that provides a first contact zone for the first wing tube structure 210, and at least a second region in a second plane which provides a second contact zone for the second wing tube structure 210. A central depression is provided in the first and second regions, which is adapted to a shape of the tube 212 of the wing tube structure 210. Furthermore, the lamella structure 220 has at least one first obliquely running 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 running 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 an adjacent second region or on the second region.

Two wing tube structures 210 are connected to one another via the slat structure 220 and run parallel to one another, so that the wings of a sub-unit 202, 204, 206 and 208 are arranged in parallel planes. The slat structure 220 has at least a width that corresponds to a width of the wing tube structure 210 and is in contact with the wing tube structure 210, preferably over the entire width of the wing tube structure 210.

The four subunits 202, 204, 206 and 208 are arranged next to one another. During operation of the condenser 200, a flow direction of air flowing over the fin structure 220 of the condenser 200 is aligned approximately at right angles to the fin structure 220. The condenser 200 further comprises a supply pipe 230 for supplying a fluid, which is connected to a first end of the plurality of vane tube structures 210 of each of the subunits 202, 204, 206 and 208, and a discharge pipe 232 for discharging a fluid, which is connected to a second end of the vane tube structures 210 of each of the subunits 202, 204, 206 and 208, opposite the first end.

An inner diameter of the central tube 212 of the wing tube structure 210 is at least 3 mm, 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 consecutive first and/or second regions of the lamella structure is 3 to 9 mm. Furthermore, the distance between central tubes of adjacent subunits 202, 204, 206 and 208 is preferably 25 to 35 mm.

The width of the condenser perpendicular to the flow direction of the air flowing over the condenser's lamella structure is 200 to 250 mm, the height of the condenser perpendicular to the flow direction of the air flowing over the condenser's lamella structure is 100 to 150 mm and the depth of the condenser in the flow direction of the air flowing over the condenser's lamella structure is 80 to 150 mm. These dimensions make the condenser particularly efficient for use in household appliances such as a tumble dryer.

An advantage of the condenser according to the invention is therefore the particularly compact design and the particularly efficient removal of heat by means of the wing tube structure in combination with the fin structure and the specific design and dimensioning.

Now referring to the Fig. 29 to 32 a preferred evaporator 300 according to the invention is shown. An evaporator is generally a device in which a fluid flowing inside the central tube of the wing tube structure is converted from the liquid state to the gaseous state. An advantage of the evaporator according to the invention, as with the condenser according to the invention, is the particularly compact structure.

The evaporator 300 comprises exactly two elongated, straight-line 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 round line cross-section and two wings 306, 312 arranged opposite one another and extending laterally outward from the central tube 304, 310. The wings 306, 312 run 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 vane tube structures 302, 308 therefore comprises a plurality of tube sections with vanes 306, 312. The tube sections with vanes 306, 312 of a respective vane tube structure 302, 308 are arranged such that the vanes 306, 312 are arranged in one plane. This distinguishes the evaporator according to the invention from the condenser according to the invention, for example, in which the vanes of a vane tube structure are arranged in parallel planes. In order to connect several tube sections with vanes of a vane tube structure to several tube sections with vanes of another vane tube structure, the lamella structure 320 explained further below comprises a plurality of central depressions 322, so that a lamella structure connects several tube sections with vanes of the first and second vane tube structures to one another.

The evaporator 300 further comprises the above-mentioned fin structure 320. The fin structure has at least a first region in a first plane, which provides a first contact zone for the first vane tube structure 302, and at least a second region in a second plane, which provides a second contact zone for the second vane tube structure 308. A plurality of central depressions 322 are provided in the first and second regions, which are adapted to a shape of the tube 304, 310 of the vane tube structure 302, 308. In addition, the fin structure 320 comprises at least a 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 a second obliquely extending region, which is arranged with a first end at the first region or another, adjacent, first region. and having an opposite second end disposed at an adjacent second region or at the second region.

The two vane tube structures 302, 308 are connected to one another via the louvre structure 320 and run parallel to one another. The louvre structure 320 has at least one width that corresponds to a width of the vane tube structure 302, 308. In addition, the louvre structure 320 is in contact with the vane tube structure 302, 308 and with several tube sections of the respective vane tube structure 302, 308 across the width of the vane tube structure 302, 308. When the evaporator 300 is in operation, a flow direction of air flowing over the louvre structure of the evaporator is aligned approximately at right angles to the louvre structure.

The outer diameter of the central tube 304, 310 of the vane tube structure 302, 308 is 6 to 8 mm, with a wall thickness of 0.5 mm and a width of the vane tube structure 302, 308 being 25 to 30 mm. A distance between the vanes of the first and second vane tube structure is approximately 20 mm. The width of a tube section with vanes is ≤ 30 mm. In this way, a particularly compact design of the evaporator can be achieved. Furthermore, a cavity can be present at least partially between the vanes of the vane tube structure and the fin structure. This can be provided with a means that resists thawing. In this way, the effectiveness of the evaporator can be further improved.

List of reference symbols

1

Microchannel structure

3

Microchannel

10

Lamellar structure

20

Component composite

100

Microchannel structure

102

first area

104

Microchannel

106

wing

108

edge

110

Connection area

120

Lamellar structure

122

first area

124

second area

126

first sloping area

128

second sloping area

130

deepening

132

head Start

140

Component composite

150

Heat exchanger

152

first distribution pipe

154

second distribution pipe

156

first connection

158

second connection

HM

Height of the microchannel structure 1

BM

Width of the microchannel structure 1

HL

Height of the slat structure 10

BL

Width of the slat structure 10

HS

Height of the first area 102

BS

Width of the first area 102

D

Thickness of wings 106

BGes

Total width of the microchannel structure 100

HLS

Height of the slat structure 120 in the first area 102

HLGes

Total height of the slat structure 120

BLGes

Total width of the slat structure 120

α

first angle

β

second angle

γ

third angle

δ

fourth angle

200

Condenser

202

first subunit

204

second subunit

206

third subunit

208

fourth subunit

210

Wing tube structure

212

central pipe

214

wing

220

Lamellar structure

230

Supply pipe

232

Discharge pipe

300

Evaporator

302

first wing tube structure

304

central tube of the first wing tube structure

306

Wing of the central tube of the first wing tube structure

308

second wing tube structure

310

central tube of the second wing tube structure

312

Wing of the central tube of the second wing tube structure

320

Lamellar structure

322

deepening

Claims (15)

1. Component compound (140) comprised of:

   a. a plurality of micro channel structures (1; 100), each of which

   b. having a plurality of micro channels (104) running parallel to one another, defining a first portion (102) of the micro channel structure (100), having an approximately rectangular cross section which has a larger width (Bs) in comparison with a height (Hs), and

   c. two wings (106) laterally running to the outside from a surface wrapping the first portion (102) from a side wall determining the height (Hs), and

   d. a lamellar structure (120) comprising the following features:

   e. at least a first portion (122) of the lamellar structure (120) in a first plane, with the first portion (122) providing a first connecting surface for the first micro channel structure (1; 100),

   f. at least a second portion (124) of the lamellar structure (120) in a second plane, with the second portion (124) providing a second connecting surface for the second micro channel structure (1; 100),

   g. at least a first transversely running portion (126), which is arranged with a first end at the first portion (122) of the lamellar structure (120) and with an opposite second end at the second portion (124) of the lamellar structure (120), and

   h. at least a second transversely running portion (128), which is arranged with a first end at the first portion (122) of the lamellar structure (120) or a further, adjacent first portion (122) of the lamellar structure (120), and with an opposite second end at the second portion (124) of the lamellar structure (120), with

   i. the two micro channel structures (1; 100) being connected with one another via the lamellar structure (120) and running parallel to one another, with the lamellar structure (120) having a width corresponding to at least a width of the micro channel structure (100) and with the lamellar structure (120) being in contact with the micro channel structure (100) over the complete width of the micro channel structure (100), and

   the component compound (140) is characterized in that

   j. the wings (106) running to the outside extend parallel to a longitudinal axis of the first portion (102) and

   k. a central recess (130) is provided in the first (122) and the second portion (124) of the lamellar structure (120), the recess being adapted to the micro channel structure (1; 100) in the first portion (102) of the micro channel structure (1; 100), with

   l. the at least one first transversely running portion (126) enclosing a first angle α smaller than 90° at a first side with the first portion (122) of the lamellar structure (120) and enclosing a second angle β smaller than 90° at a second side, opposite to the first side, with the second portion (124) of the lamellar structure (120), and with

   m. the at least one second transversely running portion (126) enclosing a third angle γ smaller than 90° at a first side with the first portion (122) of the lamellar structure (120) or with the further first portion (122) of the lamellar structure (120) as well as a fourth angle δ smaller than 90° at a second side, opposite to the first side, with the second portion (124) of the lamellar structure (120).
2. Component compound (140') comprised of:

   a. a plurality of elongated straight running wing tube structures (200), each of which having

   a1. a central tube (210) with a round, curvilinear or angled tube cross section as well as

   a2. two wings (220) laterally running to the outside from the central tube (210) and being arranged opposite one another, with the wings running parallel to a longitudinal axis of the central tube (210), and

   the component compound (140') is characterized in that it comprises:

   b. a lamellar structure (120') having the following features:

   b1. at least one first portion (122') of the lamellar structure (120') in a first plane, with the first portion (122') providing a first connecting surface for the first wing tube structure (200),

   b2. at least one second portion (124') of the lamellar structure (120') in a second plane, with the second portion (124') providing a second connecting surface for the second wing tube structure (200), with a central recess (130') being provided in the first (122') and second portion (124') of the lamellar structure (120') which is adapted to a shape of the tube of the wing tube structure (200),

   b3. at least one first transversely running portion (126'), which is arranged with a first end at the first portion (122') of the lamellar structure (120') and with an opposite second end at the second portion (124') of the lamellar structure (120'), and

   b4. at least one second transversely running portion (128'), which is arranged with a first end at the first portion (122') of the lamellar structure (120') or a further, adjacent first portion (122') of the lamellar structure (120') and with an opposite second end at the second portion (124') of the lamellar structure (120'), with

   b5. the at least one first transversely running portion (126') enclosing a first angle α smaller than 90° at a first side with the first portion (122') of the lamellar structure (120') and a second angle β smaller than 90° at a second side opposite to the first side with the second portion (124') of the lamellar structure (120'), and with

   b6. the at least one second transversely running portion (126') enclosing a third angle γ smaller than 90° at a first side with the first portion (122') of the lamellar structure (120') or the further first portion (122') of the lamellar structure (120') as well as a fourth angle δ smaller than 90° at a second side opposite to the first side with the second portion (124') of the lamellar structure (120'), with

   c1. the two wing tube structures (200) being connected with one another by means of the lamellar structure (120') and extending parallel to one another as well as with

   c2. the lamellar structure (120') having at least a width corresponding to a width of the wing tube structure (200), and

   c3. the lamellar structure (120') being in contact with the wing tube structure (200) over the complete width of the wing tube structure (200).
3. Component compound (140) according to claim 1 or 2 in which the lamellar structure (120; 120') is fastened to the micro channel structures (1; 100) or the wing tube structures, e.g. by means of soldering.
4. Component compound according to one of the preceding claims, the micro channel structure or the wing tube structure (200) of which is produced as one piece by means of extrusion out of aluminum.
5. Component compound according to claim 1 or 2, the lamellar structure of which comprises a plurality of first (122; 122') and second portions (124; 124') as well as a plurality of first transversely running portions (126; 126') and a plurality of second transversely running portions (128; 128'), with the first transversely running portion (126; 126') being arranged with the first end at the first end of the first portion (122; 122') and with the opposite second end at the first end of the second portion (124; 124') and in which the second transversely running portion (128; 128') is arranged with the first end at the second end of the adjacent first portion (122; 122') from the plurality of first portions (122; 122') and with the opposite second end at the second end of the second portion (124; 124').
6. Component compound according to claim 2, 3 or 4 to 5 in combination with claim 2, in which the plurality of elongated straight running wing tube structures (200) is arranged in a meander like course parallel to one another and connected consecutively with one another while conducting liquids, so that a liquid supply is connectable with an intake and a liquid discharge is connectable with an outlet of the meander like course of the wing tube structures (200).
7. Heat exchanger (150) comprising:

   a. a first distributor tube (152) for supplying a fluid and a second distributor tube (154) for discharging a fluid as well as

   b. a component compound (140) according to one of the claims 1, 3 to 5 in combination with claim 1, with

   c. the micro channels (104) of each micro channel structure (1; 100) being in flow connection with the first distributor tube (152) at a first end and at a second end in flow connection with the second distributor tube (154).
8. Heat exchanger (150') comprising:

   a. a supply tube (156') for supplying a fluid and a discharge tube (158') for discharging a fluid as well as

   b. a component compound (140') according to one of the claims 2, 3, 5 in combination with claim 2, in which

   c. the central tubes of the wing tube structures (200) are subsequently connected with one another, so as to provide a flow connection between the supply tube and the discharge tube and in which the plurality of elongated straight running wing tube structures (200) is arranged in a meander like course parallel to one another, so that the supply tube is connected with an inlet and the discharge tube is connected with an outlet of the meander like course of the wing tube structures (200).
9. Manufacturing method of a micro channel structure (100) for a component compound (140) according to claim 1, comprising the step:

   a. extruding (A) a micro channel structure (100) consisting of a plurality of micro channels (104) running parallel to one another, defining a first portion (102) of the micro channel structure (100) and consisting of at least one, preferably two, wings (106) extending laterally from a surface wrapping the first portion (102), the wing (106) running parallel to a longitudinal axis of the first portion (102), preferably of aluminum.
10. Manufacturing method of a lamellar structure (120) for a component compound (140; 140') according to one of the claims 1 or 2, comprising the step:

    a. providing (B) at least one first portion (122) which provides a first connecting surface for a first micro channel structure (1; 100) or a first wing tube structure, and at least one second portion (124) which preferably provides a second connecting surface for a second micro channel structure (1; 100) or a second wing tube structure, after that

    b. arranging (C) a first transversely running portion (126) with a first end at the first portion (122) and with an opposite second end at the second portion (124) such that the at least one first transversely running portion (126) encloses a first angle α smaller than 90° at a first side with the first portion (122) and a second angle β smaller than 90° at a second side opposite the first side with the second portion (124), and

    c. arranging (D) a second transversely running portion (128) with a first end at the first portion (122) or a further, preferably adjacent, first portion (122) and with an opposite second end at the second portion (124).
11. Manufacturing method of a component compound (140) according to one of the claims 1 to 6, comprising:

    a. providing (F) at least two micro channel structures (1; 100) or at least two wing tube structures (200) and a lamellar structure (120), after that

    b. at least partly connecting (G) the two micro channel 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).
12. Manufacturing method of a heat exchanger (150) according to claim 7, comprising:

    a. providing (H) a first distributor tube (152),

    b. providing (I) a second distributor tube (154),

    c. providing (J) a component compound (140) according to one of the claims 1, 3, 4, 5, after that

    d. connecting (K) the micro channels (3; 104) of each micro channel structure (1; 100) at a first end with the first distributor tube (152) and at a second end with the second distributor tube (154).
13. Manufacturing method of a heat exchanger (150) according to claim 8 comprising:

    a. providing (H) a supply tube (156') for supplying a fluid and

    b. providing (I) a discharge tube (158') for discharging a fluid,

    c. providing (J) a component compound (140) according to one of the claims 2, 3, 4-6, after that

    d. connecting (K) the central tubes of the wing tube structures (200) subsequently with each other in order to provide a flow connection between the supply tube and the discharge tube and to arrange the plurality of elongated straight running wing tube structures (200) in a meander-like course parallel to one another so that the supply tube is connected with an inlet and the discharge tube is connected with an outlet of the meander-like course of the wing tube structure (200).
14. Liquefier (200) consisting of

    i. at least two, preferably three, component compounds (140') according to claim 2 as sub-units (202, 204, 206, 208), each having

    a. a plurality of elongated, straight running wing tube structures (210) and

    b. a lamellar structure (220) wherein two wing tube structures (210) are connected with one another by means of the lamellar structure (220) and run parallel to one another, so that the wings (214) of a sub-unit (202, 204, 206, 208) are arranged in parallel planes, wherein

    ii. the sub-units (202, 204, 206, 208) are arranged next to each other and in operation of the liquefier, a flow direction of an air streaming over the lamellar structure (220) of the liquefier is aligned approximately rectangular to the lamellar structure (220), and the liquefier (200) further comprises

    iii. a supply tube (230) for supplying a fluid which is connected with a first end of the plurality of wing tube structures (210) of at least one sub-unit (202, 204, 206, 208), as well as a discharge tube (232) for discharging a fluid, which is connected with a second end, opposite to the first end, of the wing tube structures (210) of at least one of the sub-units (202, 204, 206, 208), wherein

    iv. the inner diameter of the central tube (212) of the wing tube structure is at least 3 mm, 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 (210) is preferably ≤ 25 mm.
15. Evaporator (300) with a component compound (140') according to claim 2, which comprises, preferably exactly, two elongated straight running wing tube structures (302, 308), with the wings (306, 312) of a respective wing tube structure (302, 308) being arranged in the same plane, as well as a lamellar structure (320), and

    a. the lamellar structure (320) is in contact with the wing tube (302, 308) as well as with a number of tube sections of the respective wing tube structure (302, 308) over the width of the wing tube structure (302, 308), wherein

    b. in operation of the evaporator (300), a flow direction of a fluid streaming over the lamellar structure (320) of the evaporator (300) is aligned approximately rectangular to the lamellar structure (320), and

    c. 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 being 0.5 mm and a width of the wing tube structure (302, 308) being 25 to 30 mm.

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