US20150027676A1 - Craft outer skin heat exchanger and method for manufacturing a craft outer skin heat exchanger - Google Patents
Craft outer skin heat exchanger and method for manufacturing a craft outer skin heat exchanger Download PDFInfo
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- US20150027676A1 US20150027676A1 US14/497,753 US201414497753A US2015027676A1 US 20150027676 A1 US20150027676 A1 US 20150027676A1 US 201414497753 A US201414497753 A US 201414497753A US 2015027676 A1 US2015027676 A1 US 2015027676A1
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- Prior art keywords
- heat transfer
- heat exchanger
- transfer module
- heat
- curvature
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- 238000004519 manufacturing process Methods 0.000 title claims description 22
- 238000000034 method Methods 0.000 title claims description 9
- 238000012546 transfer Methods 0.000 claims abstract description 312
- 238000001816 cooling Methods 0.000 description 16
- 239000012080 ambient air Substances 0.000 description 14
- 239000000446 fuel Substances 0.000 description 9
- 239000000463 material Substances 0.000 description 7
- 239000011159 matrix material Substances 0.000 description 5
- 239000002826 coolant Substances 0.000 description 4
- 125000006850 spacer group Chemical group 0.000 description 3
- 238000013459 approach Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
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- 241000251730 Chondrichthyes Species 0.000 description 1
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 239000003570 air Substances 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000002500 effect on skin Effects 0.000 description 1
- 239000011151 fibre-reinforced plastic Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
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- 230000005855 radiation Effects 0.000 description 1
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F21/00—Constructions of heat-exchange apparatus characterised by the selection of particular materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F7/00—Elements not covered by group F28F1/00, F28F3/00 or F28F5/00
- F28F7/02—Blocks traversed by passages for heat-exchange media
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F2280/00—Mounting arrangements; Arrangements for facilitating assembling or disassembling of heat exchanger parts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/4935—Heat exchanger or boiler making
Definitions
- the invention relates to a craft outer skin heat exchanger, to the use of such an outer skin heat exchanger in an aircraft, and to a method for manufacturing such a craft outer skin heat exchanger.
- Fuel cell systems enable low-emission, highly efficient generation of electric current. For this reason, efforts are currently made to use fuel cell systems to generate electrical energy in various mobile applications, such as for example in automotive engineering or aeronautics. It is, for example, conceivable in an aircraft to replace the generators, which are currently used to supply power on board and are driven by main engines or the auxiliary power unit (APU), with a fuel cell system. A fuel cell system, moreover, might also be used to supply the aircraft with emergency power and replace the ram air turbine (RAT) hitherto used as an emergency power system.
- RAT ram air turbine
- a fuel cell during operation generates thermal energy which has to be removed from the fuel cell with the aid of a cooling system in order to prevent overheating of the fuel cell.
- a fuel cell system installed in an aircraft for example for the on-board power supply, therefore has to be designed in such a way that it is capable of meeting a high demand of electrical energy.
- a fuel cell that has a high capacity for generating electrical energy also generates a large amount of thermal energy and therefore has a high cooling requirement.
- a large number of further technical devices are provided, which generate heat and have to be cooled in order to guarantee reliable operation.
- these technical devices include, inter alia, the air conditioning unit and the electronic control components of the aircraft.
- WO 2010/105744 A2 It is further known from WO 2010/105744 A2 to provide a cooler for an aircraft cooling system, which comprises a matrix body designed to form a section of the aircraft outer skin.
- a plurality of coolant channels which extend from a first surface of the matrix body to a second surface of the matrix body and allow a flow of coolant through the matrix body.
- An object on which the invention is based is to specify a heat exchanger which is suitable for use as a craft outer skin heat exchanger in any desired section of the craft outer skin, and a method for manufacturing such a heat exchanger.
- a heat exchanger comprises a plurality of heat transfer modules.
- the heat transfer modules are arranged side by side so as to define a multilayer body of the heat exchanger.
- the heat transfer modules are arranged such that side surfaces of heat transfer module bodies of adjacent heat transfer modules face each other.
- the side surfaces of the heat transfer module bodies preferably form the main surfaces of the heat transfer module bodies, i.e., the surfaces of the heat transfer module bodies having the largest area.
- the heat transfer module bodies may further comprise an inner surface which is adapted to form a section of an inner surface of the heat exchanger and an outer surface which is adapted to form a section of an outer surface of the heat exchanger.
- the heat transfer module bodies may be in the form of a flat pipe having a very small thickness (the distance between the side surfaces), a small height (the distance between the inner surface and the outer surface), but a comparatively great length (the distance between end faces of the heat transfer module bodies).
- the heat transfer module bodies may be manufactured in an extrusion process and may be of any desired material which allows the use of the heat exchanger as a craft outer skin section.
- the material used to manufacture the heat transfer module bodies has good heat transfer properties.
- Each heat transfer module is provided with at least one heat transfer medium channel designed to allow a flow of a heat-carrying medium therethrough.
- the heat-carrying medium flowing through the heat transfer medium channel may be any desired liquid or gaseous fluid which is adapted to discharge heat from a heat generating component.
- the heat exchanger When the heat exchanger is installed in a craft, in particular an aircraft, the heat exchanger may form a part of a cooling system for cooling a heat generating component on board the craft.
- the cooling system may comprise a conveying unit, such as a pump, so as to convey the heat-carrying medium through the heat transfer medium channels of the heat exchanger.
- At least one portion of the multilayer body of the heat exchanger is provided with a curvature which is designed so as to allow the heat exchanger to be used as a curved outer skin section of a craft. That to say, the multilayer body of the heat exchanger is provided with a curvature to a curvature of a craft outer skin section the heat exchanger is intended to form.
- curvature in the context of the present application designates a quantitative parameter which is inverse to a curvature radius and which may be measured in 1/m.
- Adjacent heat transfer modules of the at least one portion of the multilayer body are arranged with a tilt angle of their central axes towards each other such that each heat transfer module is aligned towards the center of a local osculating circle defined by an outer surface of the heat exchanger.
- a cross-sectional shape of a heat transfer module body of the heat transfer modules and/or a sequence of the heat transfer modules in the heat exchanger multilayer body may be selected so as to adjust the curvature of the heat exchanger multilayer body as desired.
- the heat transfer modules of the heat exchanger multilayer body may have identical or different heat transfer module bodies.
- the modular design of the heat exchanger allows a tailoring of the shape, i.e., the curvature of the heat exchanger as desired so as to enable the heat exchanger to be employed as a craft outer skin heat exchanger in any desired section of the craft outer skin, while using only a limited number of different heat transfer modules.
- the heat exchanger may be installed as a craft outer skin heat exchanger in any desired section of the craft outer skin.
- the heat exchanger multilayer body of the heat exchanger may comprise heat transfer modules having a heat transfer module body with a rectangular cross-section.
- the heat exchanger multilayer body preferably further comprises at least one heat transfer module having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger.
- Heat transfer modules having a heat transfer module body a cross-sectional shape of which tapers in a direction from an outer surface to an inner surface of the heat transfer module body may be employed in a heat exchanger with a convex curvature
- heat transfer modules having a heat transfer module body with a frustro-conical cross section which tapers in a direction from an inner surface to an outer surface of the heat transfer module body may be employed in a heat exchanger with a concave curvature.
- the cross-sectional shape of the heat transfer module bodies of the heat transfer modules in the heat exchanger multilayer body may vary in a direction parallel to a curvature axis of the heat exchanger.
- the variation of the cross-sectional shape should, however, not result in significant change of the flow rate of the heat-carrying medium along the heat transfer medium channels provided in the heat transfer modules.
- the heat exchanger multilayer body of the heat exchanger may be defined exclusively by heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger so as to obtain a heat exchanger with a strong curvature, i.e., a small curvature radius around a curvature axis.
- heat transfer modules having a heat transfer module body with a rectangular cross-section and heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger in the heat transfer module body, a heat exchanger with a slight curvature, i.e., a large curvature radius around a curvature axis may be obtained.
- a tapering angle may correspond to the tilt angle of the central axis the heat transfer module towards the central axis of an adjacent heat transfer module.
- side faces of adjacent heat transfer modules are oriented parallel to each other.
- Heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger with a large tapering angle can be used for manufacturing a heat exchanger with a strong curvature, i.e., a small curvature radius around a curvature axis.
- heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger with a small tapering angle can be used for manufacturing a heat exchanger with a slight curvature, i.e., a large curvature radius around a curvature axis.
- the at least one heat transfer medium channel provided in the heat transfer modules preferably is designed to allow a flow of a heat-carrying medium therethrough in a direction parallel to a curvature axis of the heat exchanger.
- the heat transfer medium channels preferably extend in a direction parallel to a longitudinal axis of the aircraft and hence parallel to the direction of flow of the ambient air over the aircraft outer skin in flight operation of the aircraft.
- a heat transfer medium may be supplied to the heat transfer medium channels via a supply manifold and discharged from the heat transfer medium channels via a discharge manifold.
- the heat-carrying medium flow through the heat transfer medium channels may be unidirectional or bidirectional.
- the heat exchanger may be designed so as to allow at least one diversion by 180° of the heat-carrying medium flow through the heat transfer medium channels so that the heat-carrying medium flow meanders through the heat exchanger multilayer body.
- the heat transfer modules employed in the heat exchanger may also comprise more than one heat transfer medium channel. These heat transfer medium channels may be arranged on top of each other in a direction along an axis of the heat transfer modules, i.e., in a direction substantially parallel to the side surfaces and substantially perpendicular to the inner and outer surfaces of the heat transfer module bodies of the heat transfer modules and extend parallel to a curvature axis of the heat exchanger.
- a heat transfer medium channel adjacent to the outer surface of a heat transfer module body of a heat transfer module then advantageously serves to guide heat-carrying medium transferring heat from a heat-generating device on board the craft, which has a relatively high cooling power demand, while a heat transfer medium channel adjacent to the inner surface of a heat transfer module body of a heat transfer module advantageously is assigned to heat-carrying medium transferring heat from heat-generating devices on board the craft, which have a lower cooling power demand.
- the heat transfer module body of at least one heat transfer module may have an inner surface which is adapted to form a section of an inner surface of the heat exchanger and which has a curvature which is adjusted to the curvature of an inner surface of the craft outer skin section the heat exchanger is intended to form. If the craft outer skin section and hence the heat exchanger has a convex curvature, the inner surface of the heat transfer module body preferably has a slight concave curvature. If the craft outer skin section and hence the heat exchanger has a concave curvature, the inner surface of the heat transfer module body preferably has a slight convex curvature.
- the heat transfer module body of at least one heat transfer module may have an outer surface which is adapted to form a section of an outer surface of the heat exchanger and which has a curvature which is adjusted to the curvature of an outer surface of the craft outer skin section the heat exchanger is intended to form.
- the outer surface of the heat transfer module body preferably has a slight convex curvature.
- the outer surface of the heat transfer module body preferably has a slight concave curvature.
- a curvature radius of the inner surface of the heat transfer module is smaller than the curvature radius of the outer surface of the heat transfer module body.
- At least one heat transfer module may comprise a rib which forms a protruding section of an outer surface of the heat exchanger multilayer body.
- the rib extends in a direction parallel to a curvature axis of the heat exchanger.
- the rib preferably extend in a direction parallel to a longitudinal axis of the aircraft and hence parallel to the direction of flow of the ambient air over the aircraft outer skin in flight operation of the aircraft.
- the rib enhances the cooling performance of the heat exchanger and protects the multilayer body and in particular its outer surface from external influences.
- the rib increases the aerodynamic drag caused by the heat exchanger when installed in a craft, in particular an aircraft.
- the rib may be formed integral with the heat transfer module body of the heat transfer module. Further, the rib may be composed of the same material as the heat transfer module body of the heat transfer module, but also of a different material. For example, the rib may be produced from a metal or plastic material, preferably a fiber-reinforced plastic material. The rib may be integrally formed with the heat transfer module body of the heat transfer module in an extrusion process. The rib may have a substantially triangular cross-section. Further, the rib may have a rounded tip.
- the heat exchanger may comprise heat transfer modules which are disposed immediately adjacent to each other.
- at least two adjacent heat transfer modules in the multilayer body of the heat exchanger may be separated from each other by a separating element.
- the separating element preferably is composed of a material with good thermal transfer characteristics.
- the separating element may have isolating characteristics.
- the separating element may be used as a spacer between heat transfer modules in the multilayer body of the heat exchanger.
- the separating element may be designed and arranged so as to prevent the entry of ambient air in the space between two adjacent heat transfer modules.
- the heat exchanger then has the function of a surface heat exchanger and causes only low aerodynamic losses when employed in a craft, in particular an aircraft.
- the heat exchanger may comprise a separating element which is generally U-shaped and has two substantially parallel legs extending between side surfaces of the heat transfer module bodies of adjacent heat transfer modules. Further, the separating element may comprise a connecting bar extending between the legs in a direction parallel to a curvature axis of the heat exchanger. The connecting bar prevents the entry of ambient air in the space between two adjacent heat transfer modules and allows the formation of a smooth outer surface of the heat exchanger. An outer surface of the connecting bar may extend parallel to the outer surfaces of the heat transfer module bodies of the adjacent heat transfer modules separated from each other by the separating element and may be flat or curved, as desired.
- the heat exchanger may comprise a separating element including airside fins extending between side surfaces of the heat transfer module bodies of adjacent heat transfer modules.
- the airside fins may be offset fins or louvered fins and may be designed in accordance with the heat transfer requirements of the heat exchanger.
- the separating element may comprise sharp-edged fine grooves which, when the heat exchanger is installed in a craft, in particular an aircraft, are oriented parallel to flow lines of the ambient air flowing over the outer surface of craft, when the craft is moving.
- Such a surface structure brings about a so-called “shark skin effect,” i.e., it brings about a reduction of the frictional drag caused by the heat exchanger.
- the heat exchanger is in particular suitable for use in an aircraft.
- An aircraft cooling system thus may comprise at least one heat exchanger as described above which may be integrated into the aircraft outer skin, preferably in a lower region of aircraft fuselage so as to protect the heat exchanger from solar radiation.
- a plurality of heat transfer modules is arranged side by side so as to define a multilayer body of the heat exchanger, wherein each heat transfer module is provided with at least one heat transfer medium channel designed to allow a flow of a heat-carrying medium therethrough, wherein at least one portion of the multilayer body of the heat exchanger is provided with a curvature which is designed so as to allow the heat exchanger to be used as a curved outer skin section of a craft, and wherein adjacent heat transfer modules of the at least one portion of the multilayer body are arranged with a tilt angle of their central axes towards each other such that each heat transfer module is aligned towards the center of a local osculating circle defined by an outer surface of the heat exchanger.
- the heat transfer modules are arranged side by side in a manufacturing form and fixed relative to one another, while being arranged in the manufacturing form.
- a biasing force may be applied to the heat transfer modules arranged side by side the in a direction substantially perpendicular to side surfaces of the heat transfer module bodies of the heat transfer modules until the heat transfer modules are fixed relative to one another.
- FIGS. 1A to 1D show illustrations of four different embodiments of a heat transfer module designed to form a layer of a heat exchanger multilayer body
- FIG. 2 shows an illustration of a heat exchanger having a multilayer body after manufacturing and before integration into a craft outer skin
- FIG. 3 shows a cross-sectional view of a heat exchanger having a multilayer body when integrated into a craft outer skin
- FIG. 4 shows a cross-sectional view of an alternative heat exchanger when integrated into a craft outer skin
- FIG. 5 shows a three-dimensional view of the alternative heat exchanger according to FIG. 4 .
- FIG. 6 shows an illustration of a heat exchanger when accommodated in a manufacturing form during its manufacturing process.
- FIGS. 1A to 1D show four different embodiments of heat transfer modules 10 , 20 , 30 , 40 , each of which may form a layer of a multilayer body 102 , 202 , 302 of a heat exchanger 100 , 200 , 300 as, for example, shown in one of FIGS. 2 to 5 .
- Each heat exchanger multilayer body 102 , 202 , 302 comprises a plurality of heat transfer modules 10 , 20 , 30 , 40 as shown in FIGS. 1A to 1D .
- only one type of heat transfer modules 10 , 20 , 30 , 40 might be employed in the heat exchanger multilayer body 102 , 202 , 302 .
- heat exchanger multilayer body 102 , 202 , 302 with at least two different types of heat transfer modules 10 , 20 , 30 , 40 as shown in FIG. 1A , 1 B, 1 C or 1 D.
- the heat transfer module 10 shown in FIG. 1A comprises a heat transfer module body 10 a and a rib or fin 12 which is formed integrally with the heat transfer module body 10 a .
- the rib or fin 12 and the heat transfer module body 10 a also may be formed as separate components which are connected to one another so as to form the heat transfer module 10 shown in FIG. 1A .
- the heat transfer module body 10 a of the heat transfer module 10 has a generally rectangular cross-section and is provided with four heat transfer medium channels 14 .
- the heat transfer medium channels 14 also have a generally rectangular cross-section and are designed to allow a flow of heat transfer medium therethrough. Specifically, the heat transfer medium channels 14 are designed so as to allow the heat transfer medium to flow through the heat transfer module body 10 a of the heat transfer module 10 in a direction perpendicular to an axis A of the of the heat transfer module 10 .
- the heat transfer module body 10 a of the heat transfer module 10 further comprises two substantially parallel side surfaces 16 as well as an inner surface 18 .
- the inner surface 18 of the heat transfer module body 10 a is disposed opposite from the rib or fin 12 and may either be flat, as shown in FIG. 1A , or may be provided with a desired curvature.
- the inner surface 18 of the heat transfer module body 10 a forms a section of an inner surface 104 , 204 , 304 of the heat exchanger 100 , 200 , 300 .
- the rib or fin 12 forms a protruding section of an outer surface 106 , 206 , 306 of the heat exchanger 100 , 200 , 300 .
- the rib or fin 12 has a substantially triangular cross-section, i.e., a cross-section which tapers in a direction parallel to the axis A of the heat transfer module 10 from a base of the rib or fin 12 which is disposed adjacent to the heat transfer module body 10 a to a tip of the rib or fin 12 which is disposed distal from the heat transfer module body 10 a .
- the tip of the rib or fin 12 has a rounded shape.
- the heat transfer module 20 of FIG. 1B differs from the heat transfer module 10 shown in FIG. 1A in that it does not have a rib or fin attached to or formed integrally with a heat transfer module body 20 a .
- the heat transfer module body 20 a of the heat transfer module 20 has a generally rectangular cross-section and is provided with four heat transfer medium channels 24 , which also have a generally rectangular cross-section.
- the heat transfer module body 20 a of the heat transfer module 20 comprises two substantially parallel side surfaces 26 as well as an inner surface 28 , wherein the inner surface 28 of the heat transfer module body 20 a is adapted to form a section of an inner surface 104 , 204 , 304 of a heat exchanger 100 , 200 , 300 , when the heat transfer module 20 is installed in the heat exchanger multilayer body 102 , 202 , 302 .
- the inner surface 28 may either be flat, as shown in FIG. 1B , or may be provided with a curvature.
- the heat transfer module body 20 a of the heat transfer module 20 further comprises an outer surface 22 which is disposed opposite from the inner surface 28 .
- the outer surface 22 of the heat transfer module body 20 a forms a section of an outer surface 106 , 206 , 306 of the heat exchanger 100 , 200 , 300 .
- the outer surface 22 may either be flat, as shown in FIG. 1B , and extend substantially parallel to the inner surface 28 , or may be provided with a curvature.
- the heat transfer module 30 of FIG. 1C generally corresponds to the heat transfer module 20 shown in FIG. 1B , its heat transfer module body 30 a , however, has a cross-sectional shape tapering towards the center of an osculating circle defined by an outer surface 106 , 206 , 306 of a heat exchanger 100 , 200 , 300 including the heat transfer module 30 .
- each of the heat transfer medium channels 34 also has a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface 106 , 206 , 306 of the heat exchanger 100 , 200 , 300 including the heat transfer module 30 .
- Two side surfaces 36 of the heat transfer module body 30 a are inclined so as to approach each other in a direction parallel to the axis A of the heat transfer module 30 from the outer surface 32 to the inner surface 38 of the heat transfer module body 30 a .
- the side surfaces 36 may be inclined so as to define a tapering angle of the cross-sectional shape of the heat transfer module body 30 a of approximately 1 to 2°, in particular 1.6°.
- the inner surface 38 of the heat transfer module body 30 a is adapted to form a section of the inner surface 104 , 204 , 304 of a heat exchanger 100 , 200 , 300 , when the heat transfer module 30 is installed in the heat exchanger multilayer body 102 , 202 , 302 of the heat exchanger 100 , 200 , 300 .
- the inner surface 38 has a concave shape.
- the outer surface 32 of the heat transfer module body 30 a is disposed opposed from the inner surface 38 and is adapted to form a section of an outer surface 106 , 206 , 306 of the heat exchanger 100 , 200 , 300 , when the heat transfer module 30 is installed in the heat exchanger multilayer body 102 , 202 , 302 of the heat exchanger 100 , 200 , 300 .
- the outer surface 32 has a convex shape. It is, however, also conceivable to provide the heat transfer module body 30 a of the heat transfer module 30 with flat inner and outer surfaces 38 , 32 , or with a convex inner surface 38 and a concave outer surface 32 .
- the heat transfer module 40 as shown in FIG. 1D generally corresponds to the heat transfer module 10 as shown in FIG. 1A , its heat transfer module body 40 a , however, has a cross-sectional shape tapering towards the center of an osculating circle defined by an outer surface 106 , 206 , 306 of a heat exchanger 100 , 200 , 300 including the heat transfer module 40 .
- each of the heat transfer medium channels 44 also has a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface 106 , 206 , 306 of the heat exchanger 100 , 200 , 300 including the heat transfer module 40 .
- Two side surfaces 46 of the heat transfer module body 40 a are inclined so as to approach each other in a direction parallel to the axis A of the heat transfer module 40 from the outer surface 42 to the inner surface 48 of the heat transfer module body 40 a .
- the side surfaces 46 may be inclined so as to define a tapering angle of the cross-sectional shape of the heat transfer module body 40 a of approximately 1 to 2°, in particular 1.6°.
- the inner surface 48 of the heat transfer module body 40 a has a concave shape. It is, however, also conceivable to provide the heat transfer module body 40 a of the heat transfer module 40 with a flat or a convex inner surface 38 .
- the heat exchanger 100 shown in FIG. 2 comprises a multilayer body 102 formed of two different types of heat transfer modules 40 , 30 , namely eleven heat transfer modules 40 as shown in FIG. 1D and ten heat transfer modules 30 as shown in FIG. 1C .
- the different heat transfer modules 40 , 30 are arranged such that the side surfaces 46 of a heat transfer module 40 face the side surfaces 36 of two adjacent heat transfer module 30 and vice versa.
- the heat transfer modules 40 , 30 thus define alternating layers of the multilayer body 102 .
- adjacent heat transfer modules 40 , 30 of the multilayer body 102 are arranged with a tilt angle of their central axes A towards each other such that each heat transfer module 30 , 40 is aligned towards the center of a local osculating circle defined by the outer surface 106 of the heat exchanger 100 .
- a multilayer body 102 of the heat exchanger 100 is defined which is curved around a curvature axis C.
- the curvature radius of the multilayer body 102 depends on the shape of the heat transfer module bodies 40 a , 30 a .
- a minimum curvature radius of the multilayer body 102 of 500 mm can be obtained by employing in the multilayer body 102 heat transfer modules 40 , 30 having heat transfer module bodies 40 a , 30 a , the side surfaces 46 , 36 of which define a tapering angle of the cross sectional shape of the heat transfer module body 40 a of approximately 1.6°.
- the heat transfer medium channels 44 , 34 of the heat transfer modules 40 , 30 allow a flow of heat transfer medium through the heat transfer module bodies 10 a , 30 a of the heat transfer modules 10 , 30 in a direction parallel to the curvature axis C of the of the heat exchanger 100 .
- the curvature radius of the heat exchanger 100 thus can be tailored by suitably adapting the cross-sectional shape of the heat transfer module bodies 40 a , 30 a of the heat transfer modules 40 , 30 . It is, however, also conceivable to tailor the curvature radius of the heat exchanger 100 by installing different types of heat transfer modules, i.e., heat transfer modules, the heat transfer module bodies of which have different cross-sectional shapes in the multilayer body 102 of the heat exchanger 100 .
- heat transfer modules 10 instead of heat transfer modules 40 , heat transfer modules 10 , the heat transfer module bodies 10 a of which have a rectangular cross-sectional shape, can be employed so as to increase the curvature radius of the heat exchanger 100 .
- heat transfer modules 40 may be replaced by heat transfer modules 10 .
- heat transfer modules 30 of the heat exchanger 100 may be replaced by heat transfer modules 20 so as to increase the curvature radius of the heat exchanger 100 .
- the multilayer body 102 further comprises a plurality of separating elements 50 .
- a cross-sectional view of a separating element 50 in the direction of the curvature axis C is shown in the detail view incorporated in FIG. 2 .
- the separating elements 50 are provided in between the alternating heat transfer modules 40 , 30 and thus serve as spacers for spacing adjacent heat transfer modules 40 , 30 apart from each other.
- Each of the separating elements 50 is generally U-shaped and comprises two substantially parallel legs 52 which extend between the side surfaces 46 , 36 of the heat transfer module bodies 40 a , 30 a of adjacent heat transfer modules 40 , 30 .
- the legs 52 of the separating elements 50 may have a cross-sectional shape tapering towards the center of an osculating circle defined by the outer surface 106 of the heat exchanger 100 .
- the legs 52 of the separating elements 50 may have a cross-sectional shape tapering towards the center of an osculating circle defined by the outer surface 106 of the heat exchanger 100 .
- a connecting bar 53 extends between the legs 52 of each separating element 50 in a direction parallel to the curvature axis C of the heat exchanger 100 and has an outer surface which is designed to form a smooth section of an outer surface of the multilayer body 102 .
- the outer surface of the multilayer body 102 is formed by a periodical sequence of the outer surface of a connecting bar of a separating element 50 , a rib or fin 12 of a heat transfer module 40 , a connecting bar of a further separating element 50 , and the outer surface 32 of a heat transfer modules 30 .
- the connecting bars 53 of the separating elements 50 prevents the entry of ambient air in the space between two adjacent heat transfer modules 30 , 40 .
- the heat exchanger 100 has the function of a surface heat exchanger and causes only low aerodynamic losses when employed in a craft, in particular an aircraft.
- the outer surface 32 of the heat transfer modules 30 has a convex shape which is adjusted to the desired curvature radius of the outer surface 106 of the heat exchanger 100 around the curvature axis C.
- the outer surface of the connecting bars 53 of the separating elements 50 may be provided with a convex curvature which is adjusted to the desired curvature radius of the outer surface 106 of the heat exchanger 100 around the curvature axis C.
- inner surfaces of the legs 52 of the separating elements 50 may be provided with a concave curvature which is adjusted to the desired curvature radius of the inner surface 104 of the heat exchanger 100 around the curvature axis C.
- the multilayer body 102 of the heat exchanger 100 may also be provided with separating elements 250 ′ which are employed in the heat exchanger 300 of FIGS. 4 and 5 and which will be described in more detail below.
- the heat exchanger 100 as shown in FIG. 2 further comprises two connecting elements 60 .
- Each of the connecting elements 60 has a substantially L-shaped cross section and comprises a first leg 62 and a second leg 64 .
- the first leg 62 of each connecting element 60 forms an outermost layer of the multilayer body 102 .
- the second leg 64 extends substantially perpendicular from the first leg 62 .
- the connecting elements 60 are adapted to be connected to an outer skin of a craft in an aerodynamically favorable manner in such a way that the heat exchanger 100 is integrated into the craft outer skin so as to form a section thereof.
- FIG. 3 shows a further heat exchanger 200 having a multilayer body 202 , when integrated into a craft outer skin 210 so as to form a section thereof.
- Connecting elements 260 are provided which serve to integrate the heat exchanger 200 into the craft outer skin 210 in an aerodynamically favorable manner.
- the multilayer body 202 of the heat exchanger 200 comprises six heat transfer modules 40 as shown in FIG. 1D , one heat transfer module 10 as shown in FIG. 1A , four heat transfer modules 20 as shown in FIG. 1B and three heat transfer modules 30 as shown in FIG. 1C .
- a heat transfer module 20 or 30 as shown in FIG. 1B or FIG. 1C alternates with a heat transfer module 40 as shown in FIG.
- the curvature of the heat exchanger 200 can be tailored as desired so as to adapt it to the shape and in particular the curvature of the craft outer skin into which the heat exchanger 200 is to be integrated. Specifically, the curvature of the heat exchanger 200 matches the curvature of the craft outer skin so as to reduce aerodynamic losses caused by the heat exchanger as low as possible.
- the heat exchanger 200 of FIG. 3 also is provided with separating elements 50 in between the alternating heat transfer modules 10 , 20 , 30 , 40 and also in between the two outermost heat transfer modules 20 , 40 and the connecting elements 260 .
- the connecting bars 53 of the separating elements 50 each are provided with an outer surface which is designed to form a smooth section of an outer surface of the multilayer body 202 .
- the alternative heat exchanger 300 of FIGS. 4 and 5 which forms a section of a craft outer skin 310 , differs from the heat exchanger 200 shown in FIG. 3 only in that it comprises, instead of separating elements 50 , separating elements 250 ′ including airside fins.
- the separating elements 250 ′ allow cooling medium, in particular ambient air, to enter the spaces between adjacent heat transfer modules 10 , 20 , 30 , 40 and to thus support the heat transfer from a heat transfer medium flowing through the heat transfer channels 14 , 24 , 34 , 44 of heat transfer modules 10 , 20 , 30 , 40 to the cooling medium.
- the heat exchangers 100 , 200 , 300 described above are in particular suitable for integration into an aircraft outer skin and may be used in an aircraft to supply cooling energy to heat generating components on board the aircraft.
- the heat exchangers 100 , 200 , 300 shown in FIGS. 2 to 4 have a convex curvature an thus are adapted to form a section of an aircraft outer skin having a convex curvature, for example in the region of a tail of the aircraft.
- the heat exchangers might also be provided with a concave curvature so as to be suitable to form a section of an aircraft outer skin having a concave curvature.
- the heat transfer module bodies of the heat transfer modules may have a convex inner surface and a concave outer surface.
- heat exchangers having a varying curvature may be obtained.
- a heat exchanger may be obtained having a first section with a convex curvature and a second section having a concave curvature.
- heat transfer medium flowing through the heat transfer channels 14 , 24 , 34 , 44 provided in the heat transfer module bodies 10 a , 20 a , 30 a , 40 a of the heat transfer modules 10 , 20 , 30 , 40 is cooled by heat transfer to the ambient air flowing over the outer surface of the heat exchanger multilayer body 102 , 202 , 302 , in particular during flight operation of the aircraft.
- the heat exchanger 100 , 200 , 300 is installed in the aircraft such that the ribs or fins 12 extend in a direction parallel to a direction of the flow of ambient air over the aircraft outer skin during flight operation of the aircraft.
- the ribs or fins 12 enhance the cooling performance of the heat exchanger 100 , 200 , 300 , but increase the aerodynamic drag caused by the heat exchanger 100 , 200 , 300 .
- the cooling performance of the heat exchanger 100 , 200 , 300 can further be enhanced by providing the heat exchanger 100 , 200 , 300 with separating elements 250 ′ which allow ambient air flowing over the aircraft outer skin during flight operation of the aircraft to enter the spaces provided in the heat exchanger multilayer body 102 , 202 , 302 between adjacent heat transfer modules 10 , 20 , 30 , 40 and to thus directly discharge heat from the heat transfer medium flowing through the heat transfer channels 14 , 24 , 34 , 44 of heat transfer modules 10 , 20 , 30 , 40 .
- Separating elements 250 ′ allowing ambient air to enter the spaces provided in the heat exchanger multilayer body 102 , 202 , 302 between adjacent heat transfer modules 10 , 20 , 30 , 40 , however, also increase the aerodynamic losses caused by the heat exchanger 100 , 200 , 300 .
- FIG. 6 shows a manufacturing form 400 used for manufacturing a heat exchanger 100 , 200 , 300 .
- a plurality of layers comprising heat transfer modules 10 , 20 , 30 and/or 40 and separating elements 50 , 250 and/or 250 ′ are accommodated in the manufacturing form 400 .
- the type and the sequence of heat transfer modules 10 , 20 , 30 and/or 40 in the manufacturing form 400 are selected such that a curvature of the heat exchanger 100 , 200 or 300 is obtained which matches the curvature of the section of the craft outer skin the heat exchanger 100 , 200 , 300 is intended to form.
- the plurality of layers is fixed relative to one another.
- the manufacturing form 400 is provided with a support 410 for supporting the layers of heat transfer modules 10 , 20 , 30 , 40 in line with the curvature of the section of the outer skin of the craft, the heat exchanger 100 , 200 or 300 is intended to form.
- the manufacturing form 400 comprises a movable element 420 which is pre-stressed by use of two spiral springs 430 and which serves to apply a biasing force to the heat transfer modules 10 , 20 , 30 , 40 in a direction substantially perpendicular to the side surfaces 16 , 26 , 36 , 46 of the heat transfer module bodies 10 a , 20 a , 30 a , 40 a of the heat transfer modules 10 , 20 , 30 , 40 until the heat transfer modules 10 , 20 , 30 , 40 are fixed relative to one another.
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Abstract
A heat exchanger comprising a plurality of heat transfer modules disposed side by side so as to define a multilayer body of the heat exchanger. Each heat transfer module has at least one heat transfer medium channel configured to allow a flow of a heat-carrying medium therethrough. At least one portion of the multilayer body of the heat exchanger has a curvature configured to allow the heat exchanger to be used as a curved outer skin section of a craft. Adjacent heat transfer modules of the at least one portion of the multilayer body are arranged with a tilt angle of their central axes towards each other such that each heat transfer module is aligned towards the center of a local osculating circle defined by an outer surface of the heat exchanger.
Description
- This application is a continuation of International Application PCT/EP2013/056702 filed Mar. 28, 2013, designating the United States and published on Oct. 10, 2013 as WO 2013/149936. This application also claims the benefit of the U.S. Provisional Application No. 61/620,474, filed on Apr. 5, 2012, and of the European patent application No. 12002472.4, filed on Apr. 5, 2012, the entire disclosures of which are incorporated herein by way of reference.
- The invention relates to a craft outer skin heat exchanger, to the use of such an outer skin heat exchanger in an aircraft, and to a method for manufacturing such a craft outer skin heat exchanger.
- Fuel cell systems enable low-emission, highly efficient generation of electric current. For this reason, efforts are currently made to use fuel cell systems to generate electrical energy in various mobile applications, such as for example in automotive engineering or aeronautics. It is, for example, conceivable in an aircraft to replace the generators, which are currently used to supply power on board and are driven by main engines or the auxiliary power unit (APU), with a fuel cell system. A fuel cell system, moreover, might also be used to supply the aircraft with emergency power and replace the ram air turbine (RAT) hitherto used as an emergency power system.
- Besides electrical energy, a fuel cell during operation generates thermal energy which has to be removed from the fuel cell with the aid of a cooling system in order to prevent overheating of the fuel cell. A fuel cell system installed in an aircraft, for example for the on-board power supply, therefore has to be designed in such a way that it is capable of meeting a high demand of electrical energy. A fuel cell that has a high capacity for generating electrical energy, however, also generates a large amount of thermal energy and therefore has a high cooling requirement. Moreover, on board of a craft, especially an aircraft, a large number of further technical devices are provided, which generate heat and have to be cooled in order to guarantee reliable operation. For example in an aircraft, these technical devices include, inter alia, the air conditioning unit and the electronic control components of the aircraft.
- In the aeronautic field, efforts are therefore being made to employ outer skin heat exchangers in aircraft cooling systems in order to remove heat from devices on board the aircraft which are to be cooled into the surroundings of the aircraft. DE 10 2008 026 536 A1 and US 2011/0146957 A1, for example, describe a heat exchanger which is directly integrated into the aircraft outer skin. The heat exchanger comprises a cooling circuit allowing a flow of a heat-carrying fluid therethrough, which is embedded in an aircraft outer skin so as to be thermally coupled to the ambient air.
- It is further known from WO 2010/105744 A2 to provide a cooler for an aircraft cooling system, which comprises a matrix body designed to form a section of the aircraft outer skin. In the matrix body of the cooler, there is provided a plurality of coolant channels which extend from a first surface of the matrix body to a second surface of the matrix body and allow a flow of coolant through the matrix body.
- An object on which the invention is based is to specify a heat exchanger which is suitable for use as a craft outer skin heat exchanger in any desired section of the craft outer skin, and a method for manufacturing such a heat exchanger.
- A heat exchanger according to the invention comprises a plurality of heat transfer modules. The heat transfer modules are arranged side by side so as to define a multilayer body of the heat exchanger. Specifically, in the multilayer body of the heat exchanger the heat transfer modules are arranged such that side surfaces of heat transfer module bodies of adjacent heat transfer modules face each other. The side surfaces of the heat transfer module bodies preferably form the main surfaces of the heat transfer module bodies, i.e., the surfaces of the heat transfer module bodies having the largest area. The heat transfer module bodies may further comprise an inner surface which is adapted to form a section of an inner surface of the heat exchanger and an outer surface which is adapted to form a section of an outer surface of the heat exchanger.
- For example, the heat transfer module bodies may be in the form of a flat pipe having a very small thickness (the distance between the side surfaces), a small height (the distance between the inner surface and the outer surface), but a comparatively great length (the distance between end faces of the heat transfer module bodies). The heat transfer module bodies may be manufactured in an extrusion process and may be of any desired material which allows the use of the heat exchanger as a craft outer skin section. Preferably, the material used to manufacture the heat transfer module bodies has good heat transfer properties.
- Each heat transfer module is provided with at least one heat transfer medium channel designed to allow a flow of a heat-carrying medium therethrough. The heat-carrying medium flowing through the heat transfer medium channel may be any desired liquid or gaseous fluid which is adapted to discharge heat from a heat generating component. When the heat exchanger is installed in a craft, in particular an aircraft, the heat exchanger may form a part of a cooling system for cooling a heat generating component on board the craft. The cooling system may comprise a conveying unit, such as a pump, so as to convey the heat-carrying medium through the heat transfer medium channels of the heat exchanger.
- At least one portion of the multilayer body of the heat exchanger is provided with a curvature which is designed so as to allow the heat exchanger to be used as a curved outer skin section of a craft. That to say, the multilayer body of the heat exchanger is provided with a curvature to a curvature of a craft outer skin section the heat exchanger is intended to form. The term “curvature” in the context of the present application designates a quantitative parameter which is inverse to a curvature radius and which may be measured in 1/m.
- Adjacent heat transfer modules of the at least one portion of the multilayer body are arranged with a tilt angle of their central axes towards each other such that each heat transfer module is aligned towards the center of a local osculating circle defined by an outer surface of the heat exchanger. A cross-sectional shape of a heat transfer module body of the heat transfer modules and/or a sequence of the heat transfer modules in the heat exchanger multilayer body, may be selected so as to adjust the curvature of the heat exchanger multilayer body as desired. The heat transfer modules of the heat exchanger multilayer body may have identical or different heat transfer module bodies.
- The modular design of the heat exchanger allows a tailoring of the shape, i.e., the curvature of the heat exchanger as desired so as to enable the heat exchanger to be employed as a craft outer skin heat exchanger in any desired section of the craft outer skin, while using only a limited number of different heat transfer modules. Hence, the heat exchanger may be installed as a craft outer skin heat exchanger in any desired section of the craft outer skin.
- The heat exchanger multilayer body of the heat exchanger may comprise heat transfer modules having a heat transfer module body with a rectangular cross-section. To provide the heat exchanger multilayer body of the heat exchanger with the desired curvature, the heat exchanger multilayer body preferably further comprises at least one heat transfer module having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger. Heat transfer modules having a heat transfer module body a cross-sectional shape of which tapers in a direction from an outer surface to an inner surface of the heat transfer module body may be employed in a heat exchanger with a convex curvature, while heat transfer modules having a heat transfer module body with a frustro-conical cross section which tapers in a direction from an inner surface to an outer surface of the heat transfer module body may be employed in a heat exchanger with a concave curvature.
- The cross-sectional shape of the heat transfer module bodies of the heat transfer modules in the heat exchanger multilayer body may vary in a direction parallel to a curvature axis of the heat exchanger. The variation of the cross-sectional shape should, however, not result in significant change of the flow rate of the heat-carrying medium along the heat transfer medium channels provided in the heat transfer modules. The heat exchanger multilayer body of the heat exchanger may be defined exclusively by heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger so as to obtain a heat exchanger with a strong curvature, i.e., a small curvature radius around a curvature axis. By employing heat transfer modules having a heat transfer module body with a rectangular cross-section and heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger in the heat transfer module body, a heat exchanger with a slight curvature, i.e., a large curvature radius around a curvature axis may be obtained.
- In a heat transfer module having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger a tapering angle may correspond to the tilt angle of the central axis the heat transfer module towards the central axis of an adjacent heat transfer module. As a result, side faces of adjacent heat transfer modules are oriented parallel to each other. Heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger with a large tapering angle can be used for manufacturing a heat exchanger with a strong curvature, i.e., a small curvature radius around a curvature axis. Contrary thereto, heat transfer modules having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle defined by the outer surface of the heat exchanger with a small tapering angle can be used for manufacturing a heat exchanger with a slight curvature, i.e., a large curvature radius around a curvature axis.
- The at least one heat transfer medium channel provided in the heat transfer modules preferably is designed to allow a flow of a heat-carrying medium therethrough in a direction parallel to a curvature axis of the heat exchanger. When the heat exchanger is installed in a craft so as to form a section of the craft outer skin, ambient air flowing over the craft outer skin serves to discharge heat from the heat-carrying medium flowing through the heat transfer medium channel provided in the heat transfer modules. When the heat exchanger is installed in an aircraft, the heat transfer medium channels preferably extend in a direction parallel to a longitudinal axis of the aircraft and hence parallel to the direction of flow of the ambient air over the aircraft outer skin in flight operation of the aircraft. A heat transfer medium may be supplied to the heat transfer medium channels via a supply manifold and discharged from the heat transfer medium channels via a discharge manifold. The heat-carrying medium flow through the heat transfer medium channels may be unidirectional or bidirectional. If desired, the heat exchanger may be designed so as to allow at least one diversion by 180° of the heat-carrying medium flow through the heat transfer medium channels so that the heat-carrying medium flow meanders through the heat exchanger multilayer body.
- If desired, the heat transfer modules employed in the heat exchanger may also comprise more than one heat transfer medium channel. These heat transfer medium channels may be arranged on top of each other in a direction along an axis of the heat transfer modules, i.e., in a direction substantially parallel to the side surfaces and substantially perpendicular to the inner and outer surfaces of the heat transfer module bodies of the heat transfer modules and extend parallel to a curvature axis of the heat exchanger. A heat transfer medium channel adjacent to the outer surface of a heat transfer module body of a heat transfer module then advantageously serves to guide heat-carrying medium transferring heat from a heat-generating device on board the craft, which has a relatively high cooling power demand, while a heat transfer medium channel adjacent to the inner surface of a heat transfer module body of a heat transfer module advantageously is assigned to heat-carrying medium transferring heat from heat-generating devices on board the craft, which have a lower cooling power demand.
- The heat transfer module body of at least one heat transfer module may have an inner surface which is adapted to form a section of an inner surface of the heat exchanger and which has a curvature which is adjusted to the curvature of an inner surface of the craft outer skin section the heat exchanger is intended to form. If the craft outer skin section and hence the heat exchanger has a convex curvature, the inner surface of the heat transfer module body preferably has a slight concave curvature. If the craft outer skin section and hence the heat exchanger has a concave curvature, the inner surface of the heat transfer module body preferably has a slight convex curvature.
- Similarly, the heat transfer module body of at least one heat transfer module may have an outer surface which is adapted to form a section of an outer surface of the heat exchanger and which has a curvature which is adjusted to the curvature of an outer surface of the craft outer skin section the heat exchanger is intended to form. If the craft outer skin section and hence the heat exchanger has a convex curvature, the outer surface of the heat transfer module body preferably has a slight convex curvature. If the craft outer skin section and hence the heat exchanger has a concave curvature, the outer surface of the heat transfer module body preferably has a slight concave curvature. Preferably, a curvature radius of the inner surface of the heat transfer module is smaller than the curvature radius of the outer surface of the heat transfer module body.
- At least one heat transfer module may comprise a rib which forms a protruding section of an outer surface of the heat exchanger multilayer body. Preferably, the rib extends in a direction parallel to a curvature axis of the heat exchanger. When the heat exchanger is installed in an aircraft, the rib preferably extend in a direction parallel to a longitudinal axis of the aircraft and hence parallel to the direction of flow of the ambient air over the aircraft outer skin in flight operation of the aircraft. The rib enhances the cooling performance of the heat exchanger and protects the multilayer body and in particular its outer surface from external influences. The rib, however, increases the aerodynamic drag caused by the heat exchanger when installed in a craft, in particular an aircraft.
- The rib may be formed integral with the heat transfer module body of the heat transfer module. Further, the rib may be composed of the same material as the heat transfer module body of the heat transfer module, but also of a different material. For example, the rib may be produced from a metal or plastic material, preferably a fiber-reinforced plastic material. The rib may be integrally formed with the heat transfer module body of the heat transfer module in an extrusion process. The rib may have a substantially triangular cross-section. Further, the rib may have a rounded tip.
- The heat exchanger may comprise heat transfer modules which are disposed immediately adjacent to each other. In another embodiment of the heat exchanger at least two adjacent heat transfer modules in the multilayer body of the heat exchanger may be separated from each other by a separating element. The separating element preferably is composed of a material with good thermal transfer characteristics. Alternatively, the separating element may have isolating characteristics. In general, the separating element may be used as a spacer between heat transfer modules in the multilayer body of the heat exchanger. As a spacer, the separating element may be designed and arranged so as to prevent the entry of ambient air in the space between two adjacent heat transfer modules. The heat exchanger then has the function of a surface heat exchanger and causes only low aerodynamic losses when employed in a craft, in particular an aircraft.
- The heat exchanger may comprise a separating element which is generally U-shaped and has two substantially parallel legs extending between side surfaces of the heat transfer module bodies of adjacent heat transfer modules. Further, the separating element may comprise a connecting bar extending between the legs in a direction parallel to a curvature axis of the heat exchanger. The connecting bar prevents the entry of ambient air in the space between two adjacent heat transfer modules and allows the formation of a smooth outer surface of the heat exchanger. An outer surface of the connecting bar may extend parallel to the outer surfaces of the heat transfer module bodies of the adjacent heat transfer modules separated from each other by the separating element and may be flat or curved, as desired.
- Alternatively or additionally thereto, the heat exchanger may comprise a separating element including airside fins extending between side surfaces of the heat transfer module bodies of adjacent heat transfer modules. The airside fins may be offset fins or louvered fins and may be designed in accordance with the heat transfer requirements of the heat exchanger. When the heat exchanger is installed in a craft, in particular an aircraft, a separating element of this kind allows ambient air to enter the space between two adjacent heat transfer modules and to thus enhance the cooling capacity of the heat exchanger. So as to keep the additional aerodynamic drag caused by the design of the separating element as low as possible, the separating element may comprise sharp-edged fine grooves which, when the heat exchanger is installed in a craft, in particular an aircraft, are oriented parallel to flow lines of the ambient air flowing over the outer surface of craft, when the craft is moving. Such a surface structure brings about a so-called “shark skin effect,” i.e., it brings about a reduction of the frictional drag caused by the heat exchanger.
- The heat exchanger is in particular suitable for use in an aircraft. An aircraft cooling system thus may comprise at least one heat exchanger as described above which may be integrated into the aircraft outer skin, preferably in a lower region of aircraft fuselage so as to protect the heat exchanger from solar radiation.
- In a method for manufacturing a heat exchanger a plurality of heat transfer modules is arranged side by side so as to define a multilayer body of the heat exchanger, wherein each heat transfer module is provided with at least one heat transfer medium channel designed to allow a flow of a heat-carrying medium therethrough, wherein at least one portion of the multilayer body of the heat exchanger is provided with a curvature which is designed so as to allow the heat exchanger to be used as a curved outer skin section of a craft, and wherein adjacent heat transfer modules of the at least one portion of the multilayer body are arranged with a tilt angle of their central axes towards each other such that each heat transfer module is aligned towards the center of a local osculating circle defined by an outer surface of the heat exchanger.
- Preferably, the heat transfer modules are arranged side by side in a manufacturing form and fixed relative to one another, while being arranged in the manufacturing form.
- A biasing force may be applied to the heat transfer modules arranged side by side the in a direction substantially perpendicular to side surfaces of the heat transfer module bodies of the heat transfer modules until the heat transfer modules are fixed relative to one another.
- Preferred embodiments of the invention are now explained in more detail with reference to the appended schematic drawings, of which
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FIGS. 1A to 1D show illustrations of four different embodiments of a heat transfer module designed to form a layer of a heat exchanger multilayer body, -
FIG. 2 shows an illustration of a heat exchanger having a multilayer body after manufacturing and before integration into a craft outer skin, -
FIG. 3 shows a cross-sectional view of a heat exchanger having a multilayer body when integrated into a craft outer skin, -
FIG. 4 shows a cross-sectional view of an alternative heat exchanger when integrated into a craft outer skin, -
FIG. 5 shows a three-dimensional view of the alternative heat exchanger according toFIG. 4 , and -
FIG. 6 shows an illustration of a heat exchanger when accommodated in a manufacturing form during its manufacturing process. -
FIGS. 1A to 1D show four different embodiments ofheat transfer modules multilayer body heat exchanger FIGS. 2 to 5 . Each heatexchanger multilayer body heat transfer modules FIGS. 1A to 1D . If desired, only one type ofheat transfer modules exchanger multilayer body exchanger multilayer body heat transfer modules FIG. 1A , 1B, 1C or 1D. - The
heat transfer module 10 shown inFIG. 1A comprises a heattransfer module body 10 a and a rib orfin 12 which is formed integrally with the heattransfer module body 10 a. The rib orfin 12 and the heattransfer module body 10 a, however, also may be formed as separate components which are connected to one another so as to form theheat transfer module 10 shown inFIG. 1A . The heattransfer module body 10 a of theheat transfer module 10 has a generally rectangular cross-section and is provided with four heattransfer medium channels 14. The heattransfer medium channels 14 also have a generally rectangular cross-section and are designed to allow a flow of heat transfer medium therethrough. Specifically, the heattransfer medium channels 14 are designed so as to allow the heat transfer medium to flow through the heattransfer module body 10 a of theheat transfer module 10 in a direction perpendicular to an axis A of the of theheat transfer module 10. - The heat
transfer module body 10 a of theheat transfer module 10 further comprises two substantially parallel side surfaces 16 as well as aninner surface 18. Theinner surface 18 of the heattransfer module body 10 a is disposed opposite from the rib orfin 12 and may either be flat, as shown inFIG. 1A , or may be provided with a desired curvature. When theheat transfer module 10 is installed in a heatexchanger multilayer body inner surface 18 of the heattransfer module body 10 a forms a section of aninner surface heat exchanger fin 12 forms a protruding section of anouter surface heat exchanger FIG. 1A , the rib orfin 12 has a substantially triangular cross-section, i.e., a cross-section which tapers in a direction parallel to the axis A of theheat transfer module 10 from a base of the rib orfin 12 which is disposed adjacent to the heattransfer module body 10 a to a tip of the rib orfin 12 which is disposed distal from the heattransfer module body 10 a. The tip of the rib orfin 12 has a rounded shape. - The
heat transfer module 20 ofFIG. 1B differs from theheat transfer module 10 shown inFIG. 1A in that it does not have a rib or fin attached to or formed integrally with a heattransfer module body 20 a. Again, the heattransfer module body 20 a of theheat transfer module 20 has a generally rectangular cross-section and is provided with four heattransfer medium channels 24, which also have a generally rectangular cross-section. The heattransfer module body 20 a of theheat transfer module 20 comprises two substantially parallel side surfaces 26 as well as aninner surface 28, wherein theinner surface 28 of the heattransfer module body 20 a is adapted to form a section of aninner surface heat exchanger heat transfer module 20 is installed in the heatexchanger multilayer body inner surface 28 may either be flat, as shown inFIG. 1B , or may be provided with a curvature. - The heat
transfer module body 20 a of theheat transfer module 20 further comprises anouter surface 22 which is disposed opposite from theinner surface 28. When theheat transfer module 20 is installed in aheat exchanger outer surface 22 of the heattransfer module body 20 a forms a section of anouter surface heat exchanger inner surface 28, theouter surface 22 may either be flat, as shown inFIG. 1B , and extend substantially parallel to theinner surface 28, or may be provided with a curvature. - The
heat transfer module 30 ofFIG. 1C generally corresponds to theheat transfer module 20 shown inFIG. 1B , its heattransfer module body 30 a, however, has a cross-sectional shape tapering towards the center of an osculating circle defined by anouter surface heat exchanger heat transfer module 30. Correspondingly, each of the heattransfer medium channels 34 also has a cross-sectional shape tapering towards the center of the osculating circle defined by theouter surface heat exchanger heat transfer module 30. Two side surfaces 36 of the heattransfer module body 30 a are inclined so as to approach each other in a direction parallel to the axis A of theheat transfer module 30 from theouter surface 32 to theinner surface 38 of the heattransfer module body 30 a. The side surfaces 36 may be inclined so as to define a tapering angle of the cross-sectional shape of the heattransfer module body 30 a of approximately 1 to 2°, in particular 1.6°. - The
inner surface 38 of the heattransfer module body 30 a is adapted to form a section of theinner surface heat exchanger heat transfer module 30 is installed in the heatexchanger multilayer body heat exchanger inner surface 38 has a concave shape. Theouter surface 32 of the heattransfer module body 30 a is disposed opposed from theinner surface 38 and is adapted to form a section of anouter surface heat exchanger heat transfer module 30 is installed in the heatexchanger multilayer body heat exchanger outer surface 32 has a convex shape. It is, however, also conceivable to provide the heattransfer module body 30 a of theheat transfer module 30 with flat inner andouter surfaces inner surface 38 and a concaveouter surface 32. - The
heat transfer module 40 as shown inFIG. 1D generally corresponds to theheat transfer module 10 as shown inFIG. 1A , its heattransfer module body 40 a, however, has a cross-sectional shape tapering towards the center of an osculating circle defined by anouter surface heat exchanger heat transfer module 40. Correspondingly, each of the heattransfer medium channels 44 also has a cross-sectional shape tapering towards the center of the osculating circle defined by theouter surface heat exchanger heat transfer module 40. Two side surfaces 46 of the heattransfer module body 40 a are inclined so as to approach each other in a direction parallel to the axis A of theheat transfer module 40 from theouter surface 42 to theinner surface 48 of the heattransfer module body 40 a. The side surfaces 46 may be inclined so as to define a tapering angle of the cross-sectional shape of the heattransfer module body 40 a of approximately 1 to 2°, in particular 1.6°. Theinner surface 48 of the heattransfer module body 40 a has a concave shape. It is, however, also conceivable to provide the heattransfer module body 40 a of theheat transfer module 40 with a flat or a convexinner surface 38. - The
heat exchanger 100 shown inFIG. 2 comprises amultilayer body 102 formed of two different types ofheat transfer modules heat transfer modules 40 as shown inFIG. 1D and tenheat transfer modules 30 as shown inFIG. 1C . In themultilayer body 102 of theheat exchanger 100 according toFIG. 2 , the differentheat transfer modules heat transfer module 40 face the side surfaces 36 of two adjacentheat transfer module 30 and vice versa. Theheat transfer modules multilayer body 102. Specifically, adjacentheat transfer modules multilayer body 102 are arranged with a tilt angle of their central axes A towards each other such that eachheat transfer module outer surface 106 of theheat exchanger 100. Thus, amultilayer body 102 of theheat exchanger 100 is defined which is curved around a curvature axis C. - The curvature radius of the
multilayer body 102 depends on the shape of the heattransfer module bodies multilayer body 102 of 500 mm can be obtained by employing in themultilayer body 102heat transfer modules transfer module bodies transfer module body 40 a of approximately 1.6°. The heattransfer medium channels heat transfer modules transfer module bodies heat transfer modules heat exchanger 100. - The curvature radius of the
heat exchanger 100 thus can be tailored by suitably adapting the cross-sectional shape of the heattransfer module bodies heat transfer modules heat exchanger 100 by installing different types of heat transfer modules, i.e., heat transfer modules, the heat transfer module bodies of which have different cross-sectional shapes in themultilayer body 102 of theheat exchanger 100. For example, in theheat exchanger 100 ofFIG. 2 , instead ofheat transfer modules 40,heat transfer modules 10, the heattransfer module bodies 10 a of which have a rectangular cross-sectional shape, can be employed so as to increase the curvature radius of theheat exchanger 100. Of course, all or only a selected number ofheat transfer modules 40 may be replaced byheat transfer modules 10. Similarly, all or a selected number ofheat transfer modules 30 of theheat exchanger 100 may be replaced byheat transfer modules 20 so as to increase the curvature radius of theheat exchanger 100. - In the embodiment of a
heat exchanger 100 shown inFIG. 2 , themultilayer body 102 further comprises a plurality of separatingelements 50. A cross-sectional view of a separatingelement 50 in the direction of the curvature axis C is shown in the detail view incorporated inFIG. 2 . The separatingelements 50 are provided in between the alternatingheat transfer modules heat transfer modules elements 50 is generally U-shaped and comprises two substantiallyparallel legs 52 which extend between the side surfaces 46, 36 of the heattransfer module bodies heat transfer modules transfer module bodies heat transfer modules legs 52 of the separatingelements 50 may have a cross-sectional shape tapering towards the center of an osculating circle defined by theouter surface 106 of theheat exchanger 100. By employingseparating elements 50 havinglegs 52 with a cross-sectional shape tapering towards the center of an osculating circle defined by theouter surface 106 of theheat exchanger 100 smaller curvature radii of theheat exchanger 100 can be achieved, than by employingseparating elements 50 havinglegs 52 with a rectangular cross-section. It is, however, also conceivable to provide all or a selected number of separatingelements 50 withlegs 52 having a rectangular cross-section so as to tailor the curvature radius of theheat exchanger 100 as desired. - A connecting
bar 53 extends between thelegs 52 of each separatingelement 50 in a direction parallel to the curvature axis C of theheat exchanger 100 and has an outer surface which is designed to form a smooth section of an outer surface of themultilayer body 102. Specifically, the outer surface of themultilayer body 102 is formed by a periodical sequence of the outer surface of a connecting bar of a separatingelement 50, a rib orfin 12 of aheat transfer module 40, a connecting bar of afurther separating element 50, and theouter surface 32 of aheat transfer modules 30. The connecting bars 53 of the separatingelements 50 prevents the entry of ambient air in the space between two adjacentheat transfer modules heat exchanger 100 has the function of a surface heat exchanger and causes only low aerodynamic losses when employed in a craft, in particular an aircraft. - As described above, the
outer surface 32 of theheat transfer modules 30 has a convex shape which is adjusted to the desired curvature radius of theouter surface 106 of theheat exchanger 100 around the curvature axis C. Like theouter surface 32 of theheat transfer modules 30, also the outer surface of the connectingbars 53 of the separatingelements 50 may be provided with a convex curvature which is adjusted to the desired curvature radius of theouter surface 106 of theheat exchanger 100 around the curvature axis C. Further, like theinner surfaces heat transfer modules legs 52 of the separatingelements 50 may be provided with a concave curvature which is adjusted to the desired curvature radius of theinner surface 104 of theheat exchanger 100 around the curvature axis C. - As an alternative to the separating
elements 50 shown inFIG. 2 , themultilayer body 102 of theheat exchanger 100 may also be provided with separatingelements 250′ which are employed in theheat exchanger 300 ofFIGS. 4 and 5 and which will be described in more detail below. - The
heat exchanger 100 as shown inFIG. 2 further comprises two connectingelements 60. Each of the connectingelements 60 has a substantially L-shaped cross section and comprises afirst leg 62 and asecond leg 64. Thefirst leg 62 of each connectingelement 60 forms an outermost layer of themultilayer body 102. Thesecond leg 64 extends substantially perpendicular from thefirst leg 62. The connectingelements 60 are adapted to be connected to an outer skin of a craft in an aerodynamically favorable manner in such a way that theheat exchanger 100 is integrated into the craft outer skin so as to form a section thereof. -
FIG. 3 shows afurther heat exchanger 200 having amultilayer body 202, when integrated into a craftouter skin 210 so as to form a section thereof.Connecting elements 260 are provided which serve to integrate theheat exchanger 200 into the craftouter skin 210 in an aerodynamically favorable manner. Themultilayer body 202 of theheat exchanger 200 comprises sixheat transfer modules 40 as shown inFIG. 1D , oneheat transfer module 10 as shown inFIG. 1A , fourheat transfer modules 20 as shown inFIG. 1B and threeheat transfer modules 30 as shown inFIG. 1C . In the layer sequence of themultilayer body 202, aheat transfer module FIG. 1B orFIG. 1C alternates with aheat transfer module 40 as shown inFIG. 1D and once with aheat transfer module 10 as shown inFIG. 1A . As already discussed above, by appropriately selecting the type and the sequence of heat transfer modules in themultilayer body 202 of theheat exchanger 200, the curvature of theheat exchanger 200 can be tailored as desired so as to adapt it to the shape and in particular the curvature of the craft outer skin into which theheat exchanger 200 is to be integrated. Specifically, the curvature of theheat exchanger 200 matches the curvature of the craft outer skin so as to reduce aerodynamic losses caused by the heat exchanger as low as possible. - The
heat exchanger 200 ofFIG. 3 also is provided with separatingelements 50 in between the alternatingheat transfer modules heat transfer modules elements 260. The connecting bars 53 of the separatingelements 50 each are provided with an outer surface which is designed to form a smooth section of an outer surface of themultilayer body 202. - The
alternative heat exchanger 300 ofFIGS. 4 and 5 , which forms a section of a craftouter skin 310, differs from theheat exchanger 200 shown inFIG. 3 only in that it comprises, instead of separatingelements 50, separatingelements 250′ including airside fins. The separatingelements 250′ allow cooling medium, in particular ambient air, to enter the spaces between adjacentheat transfer modules heat transfer channels heat transfer modules - The
heat exchangers heat exchangers FIGS. 2 to 4 have a convex curvature an thus are adapted to form a section of an aircraft outer skin having a convex curvature, for example in the region of a tail of the aircraft. The heat exchangers, however, might also be provided with a concave curvature so as to be suitable to form a section of an aircraft outer skin having a concave curvature. If desired, the heat transfer module bodies of the heat transfer modules may have a convex inner surface and a concave outer surface. Further, be appropriately selecting the shape of the heat transfer module bodies of the heat transfer modules and/or the sequence of the heat transfer modules, heat exchangers having a varying curvature may be obtained. For example, a heat exchanger may be obtained having a first section with a convex curvature and a second section having a concave curvature. - When the
heat exchanger heat transfer channels transfer module bodies heat transfer modules exchanger multilayer body heat exchanger fins 12 extend in a direction parallel to a direction of the flow of ambient air over the aircraft outer skin during flight operation of the aircraft. The ribs orfins 12 enhance the cooling performance of theheat exchanger heat exchanger - The cooling performance of the
heat exchanger heat exchanger elements 250′ which allow ambient air flowing over the aircraft outer skin during flight operation of the aircraft to enter the spaces provided in the heatexchanger multilayer body heat transfer modules heat transfer channels heat transfer modules elements 250′ allowing ambient air to enter the spaces provided in the heatexchanger multilayer body heat transfer modules heat exchanger -
FIG. 6 shows amanufacturing form 400 used for manufacturing aheat exchanger heat transfer modules elements manufacturing form 400. The type and the sequence ofheat transfer modules manufacturing form 400 are selected such that a curvature of theheat exchanger heat exchanger manufacturing form 400, the plurality of layers is fixed relative to one another. - As shown in
FIG. 6 , themanufacturing form 400 is provided with asupport 410 for supporting the layers ofheat transfer modules heat exchanger manufacturing form 400 comprises amovable element 420 which is pre-stressed by use of twospiral springs 430 and which serves to apply a biasing force to theheat transfer modules transfer module bodies heat transfer modules heat transfer modules - As is apparent from the foregoing specification, the invention is susceptible of being embodied with various alterations and modifications which may differ particularly from those that have been described in the preceding specification and description. It should be understood that I wish to embody within the scope of the patent warranted hereon all such modifications as reasonably and properly come within the scope of my contribution to the art.
Claims (16)
1. A heat exchanger comprising:
a plurality of heat transfer modules arranged side by side defining a multilayer body of the heat exchanger,
each heat transfer module being provided with at least one heat transfer medium channel configured to allow a flow of a heat-carrying medium therethrough,
at least one portion of the multilayer body of the heat exchanger being provided with a curvature which is configured to allow the heat exchanger to be used as a curved outer skin section of a craft, and
adjacent heat transfer modules of said at least one portion of the multilayer body being arranged with a tilt angle of their central axes towards each other such that each heat transfer module is aligned towards a center of a local osculating circle defined by an outer surface of the heat exchanger.
2. The heat exchanger according to claim 1 , wherein the heat exchanger multilayer body comprises at least one heat transfer module having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle.
3. The heat exchanger according to claim 2 , wherein, in a heat transfer module having a heat transfer module body with a cross-sectional shape tapering towards the center of the osculating circle, a tapering angle corresponds to the tilt angle of the central axis of the heat transfer module towards the central axis of an adjacent heat transfer module.
4. The heat exchanger according to claim 1 , wherein the at least one heat transfer medium channel provided in the heat transfer modules is configured to allow a flow of a heat-carrying medium therethrough in a direction parallel to a curvature axis of the heat exchanger.
5. The heat exchanger according to claim 1 , wherein the heat transfer module body of at least one heat transfer module has an inner surface adapted to form a section of an inner surface of the heat exchanger and has a curvature adjusted to the curvature of an inner surface of the craft outer skin section the heat exchanger is intended to form.
6. The heat exchanger according to claim 1 , wherein the heat transfer module body of at least one heat transfer module has an outer surface adapted to form a section of an outer surface of the heat exchanger and has a curvature adjusted to the curvature of an outer surface of the craft outer skin section the heat exchanger is intended to form, wherein a curvature radius of the inner surface of the heat transfer module body is smaller than a curvature radius of the outer surface of the heat transfer module body.
7. The heat exchanger according to claim 1 , wherein at least one heat transfer module comprises a rib forming a protruding section of an outer surface of the heat exchanger multilayer body.
8. The heat exchanger according to claim 7 , wherein the rib is formed integral with the heat transfer module body of the heat transfer module.
9. The heat exchanger according to claim 7 , wherein the rib has a substantially conical cross-section.
10. The heat exchanger according to claim 7 , wherein the rib is provided with a rounded tip.
11. The heat exchanger according to claim 1 , wherein at least two adjacent heat transfer modules in the multilayer body of the heat exchanger are separated from each other by a separating element.
12. The heat exchanger according to claim 11 , wherein the heat exchanger comprises a separating element which is generally U-shaped and has two substantially parallel legs extending between side surfaces of the heat transfer module bodies of adjacent heat transfer modules and a connecting bar extending between the legs in a direction parallel to a curvature axis of the heat exchanger.
13. The heat exchanger according to claim 11 , wherein the heat exchanger comprises a separating element including airside fins extending between side surfaces of the heat transfer module bodies of adjacent heat transfer modules.
14. A method for manufacturing a heat exchanger, comprising the steps:
arranging a plurality of heat transfer modules side by side so as to define a multilayer body of the heat exchanger,
providing each heat transfer module with at least one heat transfer medium channel designed to allow a flow of a heat-carrying medium therethrough,
providing at least one portion of the multilayer body of the heat exchanger with a curvature configured so as to allow the heat exchanger to be used as a curved outer skin section of a craft, and wherein adjacent heat transfer modules of said at least one portion of the multilayer body are arranged with a tilt angle of their central axes towards each other such that each heat transfer module is aligned towards the center of a local osculating circle defined by an outer surface of the heat exchanger.
15. The method according to claim 14 , including the step of arranging the heat transfer modules side by side in a manufacturing form and fixing the heat transfer modules relative to one another, while they are being arranged in the manufacturing form.
16. The method according to claim 15 , including the step of applying a biasing force to the heat transfer modules arranged side by side the in a direction substantially perpendicular to side surfaces of the heat transfer module bodies of the heat transfer modules until the heat transfer modules are fixed relative to one another.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US14/497,753 US20150027676A1 (en) | 2012-04-05 | 2014-09-26 | Craft outer skin heat exchanger and method for manufacturing a craft outer skin heat exchanger |
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
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US201261620474P | 2012-04-05 | 2012-04-05 | |
EP12002472.4 | 2012-04-05 | ||
EP12002472 | 2012-04-05 | ||
PCT/EP2013/056702 WO2013149936A1 (en) | 2012-04-05 | 2013-03-28 | Craft outer skin heat exchanger and method for manufacturing a craft outer skin heat exchanger |
US14/497,753 US20150027676A1 (en) | 2012-04-05 | 2014-09-26 | Craft outer skin heat exchanger and method for manufacturing a craft outer skin heat exchanger |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/EP2013/056702 Continuation WO2013149936A1 (en) | 2012-04-05 | 2013-03-28 | Craft outer skin heat exchanger and method for manufacturing a craft outer skin heat exchanger |
Publications (1)
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US20150027676A1 true US20150027676A1 (en) | 2015-01-29 |
Family
ID=49300026
Family Applications (1)
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US14/497,753 Abandoned US20150027676A1 (en) | 2012-04-05 | 2014-09-26 | Craft outer skin heat exchanger and method for manufacturing a craft outer skin heat exchanger |
Country Status (4)
Country | Link |
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US (1) | US20150027676A1 (en) |
EP (1) | EP2834149A1 (en) |
CN (1) | CN104245510B (en) |
WO (1) | WO2013149936A1 (en) |
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US20130331019A1 (en) * | 2010-11-16 | 2013-12-12 | Airbus Operations Gmbh | Aircraft outer skin heat exchanger, aircraft cooling system and method for operating an aircraft outer skin heat exchanger |
US20130333857A1 (en) * | 2011-02-22 | 2013-12-19 | Airbus Operations Sas | Heat exchanger incorporated into a wall of an aircraft |
US20190204012A1 (en) * | 2018-01-04 | 2019-07-04 | Hamilton Sundstrand Corporation | Curved heat exchanger |
US20190212074A1 (en) * | 2018-01-08 | 2019-07-11 | Hamilton Sundstrand Corporation | Method for manufacturing a curved heat exchanger using wedge shaped segments |
US10443436B2 (en) | 2016-07-01 | 2019-10-15 | General Electric Company | Modular annular heat exchanger |
US10807723B2 (en) * | 2018-11-02 | 2020-10-20 | The Boeing Company | Integrated liquid heat exchanger and outflow valve systems and methods |
CN114828570A (en) * | 2022-04-22 | 2022-07-29 | 中国电子科技集团公司第二十九研究所 | Small-size covering heat exchanger and heat exchange system |
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US10059435B2 (en) | 2014-12-04 | 2018-08-28 | Parker-Hannifin Corporation | Low drag skin heat exchanger |
CN107966044B (en) * | 2017-11-17 | 2019-10-01 | 珠海格力电器股份有限公司 | A kind of covering heat exchanger, air conditioning system for vehicle and vehicle |
DE102019122426A1 (en) * | 2019-08-21 | 2021-02-25 | Airbus Operations Gmbh | Primary structure arrangement for an aircraft outer skin heat exchanger, aircraft with a primary structure arrangement and method for attaching an aircraft outer skin heat exchanger |
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US20130331019A1 (en) * | 2010-11-16 | 2013-12-12 | Airbus Operations Gmbh | Aircraft outer skin heat exchanger, aircraft cooling system and method for operating an aircraft outer skin heat exchanger |
US10011362B2 (en) * | 2010-11-16 | 2018-07-03 | Airbus Operations Gmbh | Aircraft outer skin heat exchanger, aircraft cooling system and method for operating an aircraft outer skin heat exchanger |
US20130333857A1 (en) * | 2011-02-22 | 2013-12-19 | Airbus Operations Sas | Heat exchanger incorporated into a wall of an aircraft |
US9446850B2 (en) * | 2011-02-22 | 2016-09-20 | Airbus Operations Sas | Heat exchanger incorporated into a wall of an aircraft |
US10443436B2 (en) | 2016-07-01 | 2019-10-15 | General Electric Company | Modular annular heat exchanger |
US20190204012A1 (en) * | 2018-01-04 | 2019-07-04 | Hamilton Sundstrand Corporation | Curved heat exchanger |
US10670346B2 (en) * | 2018-01-04 | 2020-06-02 | Hamilton Sundstrand Corporation | Curved heat exchanger |
US20190212074A1 (en) * | 2018-01-08 | 2019-07-11 | Hamilton Sundstrand Corporation | Method for manufacturing a curved heat exchanger using wedge shaped segments |
US10551131B2 (en) * | 2018-01-08 | 2020-02-04 | Hamilton Sundstrand Corporation | Method for manufacturing a curved heat exchanger using wedge shaped segments |
US10807723B2 (en) * | 2018-11-02 | 2020-10-20 | The Boeing Company | Integrated liquid heat exchanger and outflow valve systems and methods |
CN114828570A (en) * | 2022-04-22 | 2022-07-29 | 中国电子科技集团公司第二十九研究所 | Small-size covering heat exchanger and heat exchange system |
Also Published As
Publication number | Publication date |
---|---|
CN104245510B (en) | 2017-01-18 |
EP2834149A1 (en) | 2015-02-11 |
WO2013149936A1 (en) | 2013-10-10 |
CN104245510A (en) | 2014-12-24 |
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