CN104245510A - Craft outer skin heat exchanger and method for manufacturing craft outer skin heat exchanger - Google Patents
Craft outer skin heat exchanger and method for manufacturing craft outer skin heat exchanger Download PDFInfo
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- CN104245510A CN104245510A CN201380022262.1A CN201380022262A CN104245510A CN 104245510 A CN104245510 A CN 104245510A CN 201380022262 A CN201380022262 A CN 201380022262A CN 104245510 A CN104245510 A CN 104245510A
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- 238000004519 manufacturing process Methods 0.000 title claims description 13
- 238000000034 method Methods 0.000 title claims description 11
- 238000010438 heat treatment Methods 0.000 claims description 15
- 238000005452 bending Methods 0.000 claims description 5
- 230000006978 adaptation Effects 0.000 claims description 4
- 238000001816 cooling Methods 0.000 description 21
- 239000012080 ambient air Substances 0.000 description 13
- 239000003795 chemical substances by application Substances 0.000 description 12
- 239000000446 fuel Substances 0.000 description 9
- 239000000463 material Substances 0.000 description 7
- 239000003570 air Substances 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 241000270295 Serpentes Species 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000011151 fibre-reinforced plastic Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000013529 heat transfer fluid Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
A Heat exchanger (100, 200, 300) comprises a plurality of heat transfer modules (10, 20, 30, 40) which are disposed side by side so as to define a multilayer body (102, 202, 302) of the heat exchanger (100, 200, 300), wherein each heat transfer module (10, 20, 30, 40) is provided with at least one heat transfer medium channel (14, 24, 34, 44) designed to allow a flow of a heat-carrying medium therethrough, wherein at least one portion of the multilayer body (102, 202, 302) of the heat exchanger (100, 200, 300) is provided with a curvature which is designed so as to allow the heat exchanger (100, 200, 300) to be used as a curved outer skin section of a craft, and wherein adjacent heat transfer modules (10, 20, 30) of said at least one portion of the multilayer body (102, 202, 302) are arranged with a tilt angle of their central axes (A); towards each other such that each heat transfer module (10, 20, 30, 40) is aligned towards the center of a local osculating circle defined by an outer surface (106, 206, 306) of the heat exchanger (100, 200, 300).
Description
Technical field
The present invention relates to a kind of aircraft outer skin heat exchanger, relate to the purposes of this exterior skin heat exchanger in aircraft and the method related to for the manufacture of this aircraft outer skin heat exchanger.
Background technology
Fuel cell system can anti-emission carburetor, expeditiously generation current.For this reason, efforts be made so that at present and in the various Mobile solution such as such as at automotive enginering or aeronautics and so on, produce electric energy with fuel cell system.Such as, it is contemplated that in aircraft, to utilize fuel cell system to replace electrical generator, electrical generator is used to provide electric power at present on machine and electrical generator is driven by leading engine or auxiliary power unit (APU).In addition, fuel cell system also can be used to provide emergency electric power to aircraft and substitute the ram air turbine (RAT) being still used as Emergency power supply system so far.
Except electric energy, fuel cell produces heat energy at run duration, and this heat energy must remove from fuel cell under the help of cooling system, thus prevents fuel cell overheated.Therefore the fuel cell system be arranged on such as machine power source in aircraft must be designed so that it can meet high electrical energy demands.But the fuel cell had for generation of the high power capacity of electric energy also produces a large amount of heat energy, therefore has high cooling requirement.In addition, on board the aircraft, particularly aboard, provide technical equipment other in a large number, these technical equipment produce heat and must be cooled thus guarantee that failure-free runs.Such as in aircraft, these technical equipment especially comprise air-conditioning unit and the electronic control part of aircraft.
At aviation field, be therefore devoted in aircraft cooling system, to adopt exterior skin heat exchanger, the heat from equipment to be cooled on aircraft to be removed in aircraft surroundings.Such as, DE 10 2,008 026 536 A1 and US 2011/0146957 A1 describes the heat exchanger be directly integrated in aircraft outer skin.This heat exchanger comprises the cooling loop allowing heat transfer fluid to flow through, and it is embedded in aircraft outer skin, thus is connected to ambient air by heat.
Learn further from WO 2010/105744A2 and provide a kind of cooling vessel for aircraft cooling system, it comprises the matrix being designed to form an aircraft outer skin part.In the matrix of cooling vessel, provide and extend to the second surface of matrix from the first surface of matrix and allow cooling system conditioner to flow through multiple coolant passages of matrix.
Summary of the invention
The object that the present invention is based on is to clearly state a kind of heat exchanger and a kind of method for the manufacture of this heat exchanger, and this heat exchanger is suitable for being used as aircraft outer skin heat exchanger in any expectation part of aircraft outer skin.
This object is implemented for the manufacture of the method for heat exchanger with the feature with claim 13 by the heat exchanger with the feature of claim 1.
Heat exchanger according to the present invention comprises multiple heat transfer module.Multiple heat transfer module is arranged side by side to limit the multilayer main body of heat exchanger.Particularly, in the multilayer main body of heat exchanger, heat transfer module is arranged such that the side surface of the heat transfer module main body of adjacent heat transfer module is facing with each other.The side surface of heat transfer module main body is preferably formed the first type surface of heat transfer module main body, i.e. the surface with maximum area of heat transfer module main body.Heat transfer module main body can comprise the inside face of the part being suitable for the inside face forming heat exchanger further and be suitable for the outside face of a part of the outside face forming heat exchanger.
Such as, heat transfer module main body can be the form of flat tube, and it has very little thickness (distance between side surface), little height (distance between inside face with outside face) but relative large length (distance between the end face of heat transfer module main body).Heat transfer module main body can be formed with extrusion process, and can form by allowing material heat exchanger being used as any expectation of aircraft outer skin part.Preferably, the material for the manufacture of heat transfer module main body has good heat transfer property.
Each heat transfer module is provided with at least one heat transfer medium channels being designed to allow heating agent to flow through.The heating agent flowing through heat transfer medium channels can be and is suitable for discharging the liquid state from any expectation of the heat of heat generating components or gaseous fluid.When heat exchanger is installed in aircraft, when being particularly installed in aircraft, heat exchanger can form a part for the cooling system for cooling carry-on heat generating components.Cooling system can comprise delivery unit, such as pump, heating agent is transported through the heat transfer medium channels of heat exchanger.
The multilayer main body of heat exchanger be provided with curvature at least partially, this curvature is designed to allow the bending exterior skin part that heat exchanger is used as aircraft.That is, the multilayer main body of heat exchanger is provided with curvature, and this curvature is suitable for the curvature that heat exchanger is intended to the aircraft outer skin part formed.Term " curvature " represents quantitative parameter in the context of this application, and it is the inverse of radius of curvature and measures with 1/m.
The central axis that the adjacent heat transfer module of at least one part of multilayer main body is arranged to them has inclination angle each other, the center of the local osculating circle (local osculating circle) each heat transfer module all being aimed at limited by the outside face of heat exchanger.The shape of cross section of the heat transfer module main body of heat transfer module and/or the order of heat transfer module in heat exchanger multilayer main body can be selected as the curvature desirably regulating heat exchanger multilayer main body.The heat transfer module of heat exchanger multilayer main body can have identical or different heat transfer module main body.
The modular design of heat exchanger allows the shape desirably customizing heat exchanger, the i.e. curvature of heat exchanger, thus make heat exchanger can be used as aircraft outer skin heat exchanger in the part of any expectation of aircraft outer skin, only use the different heat transfer module of limited amount simultaneously.Therefore, heat exchanger can be installed to be aircraft outer skin heat exchanger in any expectation part of aircraft outer skin.
The heat exchanger multilayer main body of heat exchanger can comprise at least one heat transfer module comprising the heat transfer module main body with rectangular cross section.In order to provide the curvature of expectation to the heat exchanger multilayer main body of heat exchanger, heat exchanger multilayer main body preferably comprises at least one heat transfer module comprising the heat transfer module main body with following shape of cross section further, and this shape of cross section narrows gradually towards the center of the osculating circle that the outside face by heat exchanger limits.The heat transfer module with following heat transfer module main body can be used in be had in the heat exchanger of convex curvature, the shape of cross section of this heat transfer module main body narrows gradually along the direction from the outside face of heat transfer module main body to inside face, and the heat transfer module comprising the heat transfer module main body with following conical butt cross-sectional plane can be used in the heat exchanger with recessed curvature, this conical butt cross-sectional plane narrows gradually along the direction from the inside face of heat transfer module main body to outside face.
The shape of cross section of the heat transfer module main body of the heat transfer module in heat exchanger multilayer main body can change along the direction of the curvature axis (curvature axis) being parallel to heat exchanger.But the change of shape of cross section should not cause heating agent edge to be provided in the obvious change of the flow velocity of the heat transfer medium channels in heat transfer module.The heat exchanger multilayer main body of heat exchanger can only be limited by the heat transfer module with following heat transfer module main body, the shape of cross section that the center that this heat transfer module main body has the osculating circle limited towards the outside face by heat exchanger narrows gradually, thus make heat exchanger have large curvature, namely flexing rate axis has little radius of curvature.By adopting the heat transfer module of the heat transfer module comprising the heat transfer module main body with rectangular cross section and the heat transfer module main body comprising the shape of cross section that the center with the osculating circle limited towards the outside face by the heat exchanger in heat transfer module main body narrows gradually, can obtain the heat exchanger with slight curvature, namely flexing rate axis has large radius of curvature.
In the heat transfer module of heat transfer module main body comprising the shape of cross section that the center with the osculating circle limited towards the outside face by heat exchanger narrows gradually, cone angle may correspond to central axis in heat transfer module relative to the inclination angle of the central axis of adjacent heat transfer module.As a result, the side of adjacent heat transfer module is oriented parallel to each other.The heat transfer module comprising the heat transfer module main body of the shape of cross section that the center with the osculating circle limited towards the outside face by heat exchanger with large cone angle narrows gradually can be used to manufacture the heat exchanger with deep camber, and namely flexing rate axis has little radius of curvature.In contrast, the heat transfer module comprising the heat transfer module main body of the shape of cross section that the center with the osculating circle limited towards the outside face by heat exchanger with little cone angle narrows gradually can be used to manufacture the heat exchanger with slight curvature, i.e. the large radius of curvature of flexing rate axis.
The direction that at least one heat transfer medium channels be provided in heat transfer module is designed to allow the curvature axis that heating agent edge is parallel to heat exchanger flows through at least one heat transfer medium channels.When heat exchanger to be installed in aircraft thus to form aircraft outer skin a part of, the ambient air that aircraft outer skin flows through is for discharging the heat from the heating agent flowing through the heat transfer medium channels be provided in heat transfer module.When heat exchanger is installed in aircraft, therefore heat transfer medium channels preferably along the direction of longitudinal axis being parallel to aircraft, and is parallel to the direction that ambient air flows in aircraft outer skin in aircraft flight runs and extends.Heat transfer medium can be supplied to heat transfer medium channels via supply manifold and discharge from heat transfer medium channels via discharge manifold.Can be unidirectional or two-way by the heating agent stream of heat transfer medium channels.If expected, heat exchanger can be designed to allow at least one 180 degree turns to by the heating agent stream of heat transfer medium channels, makes heating agent stream snake through heat exchanger multilayer main body.
If expected, the heat transfer module be used in heat exchanger also can comprise more than one heat transfer medium channels.These heat transfer medium channels can be disposed in over each other along the direction of the axis of heat transfer module, namely along being basically parallel to the side surface of heat transfer module main body of heat transfer module and the direction of the inside face and outside face that are basically perpendicular to heat transfer module main body is disposed in over each other, and the curvature Axis Extension of heat exchanger is parallel to.So the heat transfer medium channels adjacent with the outside face of the heat transfer module main body of heat transfer module is advantageously used for the heating agent guiding the heat sending the heat-producing device on aircraft with relative high cooling power demand, and the heat transfer medium channels adjacent with the inside face of the heat transfer module main body of heat transfer module is advantageously assigned to the heating agent of the heat sending the heat-producing device on aircraft with lower cooling power demand.
The heat transfer module main body of at least one heat transfer module can have inside face, and this inside face is suitable for a part for the inside face forming heat exchanger and has the curvature that adaptation heat exchanger is intended to the curvature of the inside face of the aircraft outer skin part formed.If aircraft outer skin part and therefore heat exchanger have convex curvature, then the inside face of heat transfer module main body preferably has small recessed curvature.If aircraft outer skin part and therefore heat exchanger have recessed curvature, then the inside face of heat transfer module main body preferably has small convex curvature.
Similarly, the heat transfer module main body of at least one heat transfer module can have outside face, and this outside face is suitable for a part for the outside face forming heat exchanger and has the curvature that adaptation heat exchanger is intended to the curvature of the outside face of the aircraft outer skin part formed.If aircraft outer skin part and therefore heat exchanger have convex curvature, then the outside face of heat transfer module main body preferably has small convex curvature.If aircraft outer skin part and therefore heat exchanger have recessed curvature, then the outside face of heat transfer module main body preferably has small recessed curvature.Preferably, the radius of curvature of the inside face of heat transfer module is less than the radius of curvature of the outside face of heat transfer module main body.
At least one heat transfer module can comprise rib, and this rib forms the outshot of the outside face of heat exchanger multilayer main body.Preferably, rib extends along the direction of the curvature axis being parallel to heat exchanger.When heat exchanger is installed in aircraft, rib is preferably along being parallel to the longitudinal axis of aircraft and therefore parallel with the direction that the flight runtime environment air at aircraft flows in aircraft outer skin direction extends.Rib strengthens the cooling performance of heat exchanger, and protect multilayer main body particularly its outside face not by external action.But when being installed in aircraft particularly in aircraft, rib increases the aerodynamic drag caused by heat exchanger.
Rib can be formed with the heat transfer module main body of heat transfer module integral.Further, the material that rib can be identical by the heat transfer module main body with heat transfer module is formed, but also can be made up of different materials.Such as, rib can be made up of metal or plastic material, is preferably made up of fiber reinforced plastic materials.Particularly preferably, rib is integrally formed with the heat transfer module main body of heat transfer module in extrusion process.Rib can have the cross-sectional plane be generally triangular.Further, rib can have circular distal.
Heat exchanger can comprise the heat transfer module arranged with being closely adjacent to each other.In another embodiment of heat exchanger, at least two in the multilayer main body of heat exchanger adjacent heat transfer modules are separated from one another by breakaway-element.Breakaway-element is preferably made up of the material with good transfer of heat characteristic.Alternately, breakaway-element can have insulating characteristics.Generally speaking, breakaway-element can be used as in the multilayer main body of heat exchanger between heat transfer module separator.As separator, breakaway-element can be designed and be arranged as in the space preventing ambient air from entering between adjacent heat transfer module.So heat exchanger has the function of surface exchanger, and only cause low aerodynamic loss when being used in aircraft particularly in aircraft.
Heat exchanger comprises breakaway-element, and this breakaway-element is U-shaped substantially, and has the substantially parallel leg of two of to extend between the side surface of the heat transfer module main body of adjacent heat transfer module.Further, breakaway-element can comprise the pipe link extended between leg along the direction of curvature axis being parallel to heat exchanger.Pipe link prevents ambient air from entering space between two adjacent heat transfer modules, and allows the smooth outer surface forming heat exchanger.The outside face of pipe link can be parallel to and be extended by the outside face of the heat transfer module main body of breakaway-element adjacent heat transfer module separated from one another, and can be smooth or bending as required.
Alternately or additionally, heat exchanger comprises breakaway-element, this breakaway-element is included in the air side fins extended between the side surface of the heat transfer module main body of adjacent heat transfer module.Air side fins can be serrated fin (offset fin) or louvered fin, and can design according to the thermal transmission requirement of heat exchanger.When heat exchanger be installed in aircraft particularly in aircraft time, such breakaway-element allows ambient air to enter space between two adjacent heat transfer modules, and because this enhancing the cooling power of heat exchanger.In order to make the extra aerodynamic drag that caused by the design of breakaway-element little as far as possible, breakaway-element can comprise the tiny groove of sharp-edged, when heat exchanger be installed in aircraft particularly in aircraft time, the tiny groove of sharp-edged is oriented the streamline being parallel to the ambient air flowed on the outside face of aircraft when aircraft moves.This surface texture brings so-called " sharkskin effect ", and namely it makes the friction drag caused by heat exchanger reduce.
Heat exchanger is particularly suitable for being used in aircraft.Therefore aircraft cooling system can comprise at least one heat exchanger as above, and this at least one heat exchanger can be integrated in aircraft outer skin, is preferably placed in the lower area of airframe, thus protection heat exchanger is from solar radiation.
A kind of for the manufacture of in the method for heat exchanger, multiple heat transfer module is arranged side by side to limit the multilayer main body of heat exchanger, wherein each heat transfer module is provided with at least one heat transfer medium channels, this at least one heat transfer medium channels is designed to allow heating agent and flows through, wherein heat exchanger multilayer main body be provided with curvature at least partially, this curvature is designed to allow the bending exterior skin part that heat exchanger is used as aircraft, and wherein the adjacent heat transfer module at least partially of multilayer main body is arranged to their central axis and has inclination angle each other, each heat transfer module is made to aim at the center of the local osculating circle limited by the outside face of heat exchanger.
Preferably, heat transfer module is arranged side by side in modeling, and when being disposed in modeling relative to being fixed to one another.
Biasing force can be applied to the heat transfer module be arranged side by side, until heat transfer module is relative to each other fixing along the direction that the side surface of the heat transfer module main body with heat transfer module is substantially vertical.
Accompanying drawing explanation
The preferred embodiments of the present invention are explained in more detail, in accompanying drawing referring now to accompanying schematic figure:
Figure 1A to Fig. 1 D illustrates the diagram of four of the heat transfer module being designed to the layer forming heat exchanger multilayer main body different embodiments,
Fig. 2 illustrates after the fabrication and the diagram with the heat exchanger of multilayer main body before being integrated into aircraft outer skin,
Fig. 3 illustrates the cutaway view of heat exchanger when being integrated in aircraft outer skin with multilayer main body,
Fig. 4 illustrates the cutaway view of alternative heat exchanger when being integrated in aircraft outer skin,
Fig. 5 illustrates the 3-D view of the alternative heat exchanger according to Fig. 4, and
Diagram when Fig. 6 illustrates that heat exchanger is accommodated in modeling during its manufacturing process.
Detailed description of the invention
Figure 1A to Fig. 1 D illustrates four of heat transfer module 10,20,30,40 different embodiments, and each heat transfer module all can form one deck of the multilayer main body 102,202,302 of the heat exchanger 100,200,300 such as shown in Fig. 2 to Fig. 5.Each heat exchanger multilayer main body 102,202,302 comprises the multiple heat transfer modules 10,20,30,40 as shown in Figure 1A to Fig. 1 D.If expected, the heat transfer module 10,20,30,40 of a type only can be adopted in heat exchanger multilayer main body 102,202,302.But, alternately, also can be susceptible to as heat exchanger multilayer main body 102,202,302 is equipped with the dissimilar heat transfer module 10,20,30,40 of as shown in Figure 1A, Figure 1B, Fig. 1 C or Fig. 1 D at least two kinds.
Heat transfer module 10 shown in Figure 1A comprises heat transfer module main body 10a and the rib that is integrally formed with heat transfer module main body 10a or fin 12.But rib or fin 12 and heat transfer module main body 10a also can be formed the parts be separated, these parts be separated are connected to each other thus form the heat transfer module 10 shown in Figure 1A.The heat transfer module main body 10a of heat transfer module 10 has the cross-sectional plane of general rectangular, and is provided with four heat transfer medium channels 14.Heat transfer medium channels 14 also has the cross-sectional plane of general rectangular, and is designed to allow heat transfer medium flows and passes through.Particularly, heat transfer medium channels 14 is designed to allow heat transfer medium flows through heat transfer module 10 heat transfer module main body 10a along the direction perpendicular to the axis A of heat transfer module 10.
The heat transfer module main body 10a of heat transfer module 10 comprises inside face 18 and two substantially parallel side surfaces 16 further.The inside face 18 of heat transfer module main body 10a is set to relative with rib or fin 12, and can be smooth as shown in Figure 1A, or can be provided with the curvature of expectation.When heat transfer module 10 is installed in heat exchanger multilayer main body 102,202,302, the inside face 18 of heat transfer module main body 10a forms a part for the inside face 104,204,304 of heat exchanger 100,200,300.In contrast, rib or fin 12 form the outshot of the outside face 106,206,306 of heat exchanger 100,200,300.As become obvious from Figure 1A, rib or fin 12 have the cross-sectional plane of fundamental triangle, are namely set to the base portion adjacent with the heat transfer module main body 10a cross-sectional plane being set to narrow gradually away from the end of heat transfer module main body 10 to rib or fin 12 along with the direction of the axis A parallel of heat transfer module 10 from rib or fin 12.The end of rib or fin 12 has round-shaped.
The heat transfer module 20 of Figure 1B is with the difference of the heat transfer module 10 shown in Figure 1A, and it does not have the rib or fin that are attached to heat transfer module main body 20a or be integrally formed with heat transfer module main body 20.And the heat transfer module main body 20a of heat transfer module 20 has the cross-sectional plane of general rectangular, and be provided with four heat transfer medium channels 24, these four heat transfer medium channels 24 also have the cross-sectional plane of general rectangular.The heat transfer module main body 20a of heat transfer module 20 comprises inside face 28 and two substantially parallel side surfaces 26, wherein when heat transfer module 20 is installed in heat exchanger multilayer main body 102,202,302, the inside face 28 of heat transfer module main body 20a is suitable for a part for the inside face 104,204,304 forming heat exchanger 100,200,300.Inside face 28 can be smooth as shown in fig. 1b, or can be provided with curvature.
The heat transfer module main body 20a of heat transfer module 20 comprises the outside face 22 being set to relative with inside face 28 further.When heat transfer module 20 is installed in heat exchanger 100,200,300, the outside face 22 of heat transfer module main body 20a forms a part for the outside face 106,206,306 of heat exchanger 100,200,300.Similar with inside face 28, outside face 22 as shown in fig. 1b for smooth and be arranged essentially parallel to inside face 28 and extend, or can be provided with curvature.
The heat transfer module 30 of Fig. 1 C corresponds to the heat transfer module 20 shown in Figure 1B substantially, but, the shape of cross section that the center that its heat transfer module main body 30a has the osculating circle limited towards the outside face 106,206,306 by the heat exchanger 100,200,300 comprising heat transfer module 30 narrows gradually.Correspondingly, the shape of cross section that the center that each heat transfer medium channels 34 also has the osculating circle limited towards the outside face 106,206,306 by the heat exchanger 100,200,300 comprising heat transfer module 30 narrows gradually.Two side surfaces 36 of heat transfer module main body 30a tilt, thus closer to each other from the direction of outside face 32 to the inside face 38 of heat transfer module main body 30a along the axis A parallel with heat transfer module 30.Side surface 36 can be inclination, thus the cone angle limiting the shape of cross section of heat transfer module main body 30a is about 1 to 2 °, 1.6 ° especially.
When heat transfer module 30 is installed in the heat exchanger multilayer main body 102,202,302 of heat exchanger 100,200,300, the inside face 38 of heat transfer module main body 30a is suitable for a part for the inside face 104,204,304 forming heat exchanger 100,200,300.Inside face 38 has concave shape.The outside face 32 of heat transfer module 30a is set to relative with inside face 38, and when heat transfer module 30 is installed in the heat exchanger multilayer main body 102,202,302 of heat exchanger 100,200,300, outside face 32 is suitable for a part for the outside face 106,206,306 forming heat exchanger 100,200,300.Outside face 32 has convex shape.But the heat transfer module main body 30a that also can be susceptible to as heat transfer module 30 provides smooth inside and outside surperficial 38,32, or provides convex inside face 38 and concave outer surface 32.
Heat transfer module 40 shown in Fig. 1 D corresponds to the heat transfer module 10 shown in Figure 1A substantially, but, the shape of cross section that the center that its heat transfer module main body 40a has the osculating circle limited towards the outside face 106,206,306 by the heat exchanger 100,200,300 comprising heat transfer module 40 narrows gradually.Correspondingly, the shape of cross section that the center that each heat transfer medium channels 44 also has the osculating circle limited towards the outside face 106,206,306 by the heat exchanger 100,200,300 comprising heat transfer module 40 narrows gradually.Two side surfaces 46 of heat transfer module main body 40a tilt, thus closer to each other from the direction of outside face 42 to the inside face 48 of heat transfer module main body 40a along the axis A parallel with heat transfer module 40.That side surface 46 can be inclination thus the cone angle limiting the shape of cross section of heat transfer module main body 40a is about 1 to 2 °, 1.6 ° especially.The inside face 48 of heat transfer module main body 40a has concave shape.But the heat transfer module main body 40a that also can be susceptible to as heat transfer module 40 provides smooth or the inside face of convex 38.
Heat exchanger 100 shown in Fig. 2 comprises the multilayer main body 102 formed by two kinds of dissimilar heat transfer modules 40,30, i.e. 11 heat transfer modules 40 as shown in Figure 1 D and ten heat transfer modules 30 as is shown in fig. 1 c.In the multilayer main body 102 of the heat exchanger 100 according to Fig. 2, different heat transfer modules 40,30 is arranged such that the side surface 36 of the side surface 46 of heat transfer module 40 in the face of two adjacent heat transfer modules 30, and vice versa.Therefore heat transfer module 40,30 limits the alternating layer of multilayer main body 102.Particularly, the central axis A that the adjacent heat transfer module 40,30 of multilayer main body 102 is arranged to them has inclination angle each other, makes each heat transfer module 30,40 all aim at the center of the local osculating circle limited by the outside face 106 of heat exchanger 100.Therefore, limit the multilayer main body 102 of heat exchanger 100, multilayer main body 102 flexing rate axis C bends.
The radius of curvature of multilayer main body 102 depends on the shape of heat transfer module main body 40a, 30a.Such as, by adopting the heat transfer module 40,30 with heat transfer module main body 40a, 30a in multilayer main body 102, the minimum profile curvature radius that can obtain multilayer main body 102 is 500mm, and the cone angle of the shape of cross section of side surface 46, the 36 restriction heat transfer module main body 40a of heat transfer module main body 40a, 30a is about 1.6 degree.The heat transfer medium channels 44,34 of heat transfer module 40,30 allows heat transfer medium edge and the direction of the curvature axis C parallel of heat exchanger 100 to flow through heat transfer module main body 10a, the 30a of heat transfer module 10,30.
Therefore by suitably adjusting the heat transfer module main body 40a of heat transfer module 40,30, the shape of cross section of 40a, the radius of curvature of customizable heat exchanger 100.But, also can be susceptible to by installing the radius of curvature that dissimilar heat transfer module customizes heat exchanger 100 in the multilayer main body 102 of heat exchanger 100, namely following heat transfer module: the heat transfer module main body of this heat transfer module has different shape of cross sections.Such as, in the heat exchanger 100 of Fig. 2, replace heat transfer module 40, heat transfer module 10 is used the radius of curvature increasing heat exchanger 100, and the heat transfer module main body of heat transfer module 10 has rectangular cross-sectional shape.Certainly, heat transfer module 40 that is all or that only select quantity can be replaced by heat transfer module 10.Similarly, heat exchanger 100 all or select the heat transfer module 30 of quantity can replace by heat transfer module 20 radius of curvature increasing heat exchanger 100.
In the embodiment of the heat exchanger 100 shown in Fig. 2, multilayer main body 102 comprises multiple breakaway-element 50 further.Breakaway-element 50 illustrates in the detailed view of Fig. 2 along the cutaway view in curvature axis C direction.Breakaway-element 50 is provided between heat transfer module 40,30 alternately, and is therefore used as adjacent heat transfer module 40,30 separator separated from one another.Each breakaway-element 50 is U-shaped substantially, and the leg 52 that two that extend between the side surface 46,36 being included in the heat transfer module main body 40a of adjacent heat transfer module 40,30,30a substantially parallel.Be similar to heat transfer module main body 40a, the 30a of heat transfer module 40,30, the shape of cross section that the center that the leg 52 of breakaway-element 50 can have the osculating circle limited towards the outside face 106 by heat exchanger 100 narrows gradually.Compared with the breakaway-element 50 comprising the leg 52 with rectangular cross section with employing, by adopting the breakaway-element 50 of the leg 52 comprising the shape of cross section that the center with the osculating circle limited towards the outside face 106 by heat exchanger 100 narrows gradually, the less radius of curvature of heat exchanger 100 can be obtained.But, also can be susceptible to as breakaway-element 50 that is all or selection quantity provides the leg 52 with rectangular cross section, thus desirably customize the radius of curvature of heat exchanger 100.
Pipe link 53 extends between the leg 52 of each breakaway-element 50 along the direction of the curvature axis C being parallel to heat exchanger 100, and has outside face, and this outside face is designed to the smooth of the outside face forming multilayer main body 102.Particularly, the outside face of multilayer main body 102 is formed by the periodic sequence of the outside face of the pipe link of breakaway-element 50, the rib of heat transfer module 40 or fin 12, the pipe link of another breakaway-element 50 and the outside face 32 of heat transfer module 30.In the space that the pipe link 53 of breakaway-element 50 prevents ambient air from entering between two adjacent heat transfer modules 30,40.Therefore, when be used in aircraft particularly in aircraft time, heat exchanger 100 has the function of surface exchanger and only causes low aerodynamic loss.
As mentioned above, the outside face 32 of heat transfer module 30 has convex shape, and this convex shape adapts to the desired curvature radius of the outside face 106 of the flexing rate axis C of heat exchanger 100.Similar with the outside face 32 of heat transfer module 30, the outside face of the pipe link 53 of breakaway-element 50 also can be provided with convex curvature, and this convex curvature adapts to the radius of curvature of the expectation of the outside face 106 of the flexing rate axis C of heat exchanger 100.Further, with the inside face 38 of heat transfer module 30,40,48 similar, the inside face of the leg 52 of breakaway-element 50 can be provided with recessed curvature, and this recessed curvature adapts to the radius of curvature of the expectation of the inside face 104 of the flexing rate axis C of heat exchanger 100.
As substituting the breakaway-element 50 shown in Fig. 2, the multilayer main body 102 of heat exchanger 100 also can be provided with breakaway-element 250 ', and it is used in the heat exchanger 300 of Fig. 4 and Fig. 5, and will more be described in detail below.
Heat exchanger 100 as shown in Figure 2 comprises two Connection Elements 60 further.Each Connection Element 60 has the cross-sectional plane of basic L shape and comprises the first leg 62 and the second leg 64.First leg 62 of each Connection Element 60 forms the outermost layer of multilayer main body 102.Second leg 64 substantially vertically extends from the first leg 62.Connection Element 60 is suitable for the exterior skin being connected to aircraft in mode favourable on aerodynamics, heat exchanger 100 is integrated in aircraft outer skin thus forms its part.
Fig. 3 illustrates another heat exchanger 200 with multilayer main body 202, and it forms its part when being integrated in aircraft outer skin 210.Connection Element 260 is provided, and it is for being integrated into heat exchanger 200 in aircraft outer skin 210 in mode favourable on aerodynamics.The multilayer main body 202 of heat exchanger 200 comprises six heat transfer modules as shown in Figure 1 D 40, heat transfer module 20, four as shown in Figure 1A heat transfer module 20 and three heat transfer modules 30 as is shown in fig. 1 c as shown in fig. 1b.In the sequence of layer of multilayer main body 202, heat transfer module 20 or 30 as shown in figure ib or figure 1 c and the heat transfer module 40 shown in Fig. 1 D alternately, and replace once with the heat transfer module 10 shown in Figure 1A.As discussed above, by suitably selecting type and the order of the heat transfer module in the multilayer main body 202 of heat exchanger 200, desirably can customize the curvature of heat exchanger 200, thus make its shape being adapted to the aircraft outer skin treating integrated heat exchanger 200 and particularly its curvature.Especially, the curvature of heat exchanger 200 and the Curvature Matching of aircraft outer skin, thus the aerodynamic loss produced due to heat exchanger is reduced as much as possible.
The heat exchanger 200 of Fig. 3 is also provided with the breakaway-element 50 between the heat transfer module 10,20,30,40 replaced and also between two outermost heat transfer modules 20,40 and Connection Element 260.Each smooth being all provided as the outside face being designed to formation multilayer main body 202 in the pipe link 53 of breakaway-element 50.
The alternative heat exchanger 300 forming Fig. 4 and Fig. 5 of a part for aircraft outer skin 310 is only with the difference of the heat exchanger 200 shown in Fig. 3, and it comprises the breakaway-element 250 ' with air side fins, instead of breakaway-element 50.Breakaway-element 250 ' allows cooling media, particularly ambient air enters in the space between adjacent heat transfer module 10,20,30,40, and therefore supports that heat transfer medium from flow through the heat transfer path 14,24,34,44 of heat transfer module 10,20,30,40 is to the heat transfer of cooling media.
Above-mentioned heat exchanger 100,200,300 is particularly suitable for being integrated in aircraft outer skin, and can be used in aircraft to the heat generating components supply cooling energy on aircraft.Heat exchanger 100,200,300 shown in Fig. 2 to Fig. 4 has convex curvature, and is therefore suitable for the part with convex curvature such as in the tail region of aircraft forming aircraft outer skin.But heat exchanger also can be provided with recessed curvature, thus be suitable for the part with recessed curvature forming aircraft outer skin.If expected, the heat transfer module main body of heat transfer module can have convex inside face and concave outer surface.Further, by suitably selecting the shape of heat transfer module main body and/or the order of heat transfer module of heat transfer module, the heat exchanger with change curvature can be obtained.Such as, the heat exchanger of the Part II comprising the Part I with convex curvature and there is recessed curvature can be obtained.
When heat exchanger 100,200,300 is installed in aircraft, flow through be provided in heat transfer module 10,20,30,40 heat transfer module main body 10a, heat transfer path 14,24,34,44 in 20a, 30a, 40a heat transfer medium be cooled by the heat transfer of ambient air flow through on the outside face of heat exchanger multilayer main body 102,202,302 to the flight run duration particularly at aircraft.Typically, heat exchanger 100,200,300 is installed to be and rib or fin 12 is extended along the direction parallel with the direction that the flight run duration ambient air at aircraft flows in aircraft outer skin in aircraft.Rib or fin 12 enhance the cooling performance of heat exchanger 100,200,300, but add the aerodynamic drag caused by heat exchanger 100,200,300.
By the cooling performance providing the heat exchanger 100,200,300 with following breakaway-element 250 ' that heat exchanger 100,200,300 can be strengthened further, breakaway-element 250 ' allows the ambient air flow through in aircraft outer skin at aircraft flight run duration to enter in the space between adjacent heat transfer module 10,20,30,40 be provided in heat exchanger multilayer main body 102,202,302, and therefore allows directly from flow through the heat transfer medium discharge heat of the heat transfer path 14,24,34,44 of heat transfer module 10,20,30,40.But the breakaway-element 250 ' allowing ambient air to enter the space between adjacent heat transfer module 10,20,30,40 be provided in heat exchanger multilayer main body 102,202,302 also increases the aerodynamic loss caused by heat exchanger 100,200,300.
Fig. 6 illustrates the modeling 400 for the manufacture of heat exchanger 100,200,300.The multiple layers comprising heat transfer module 10,20,30 and/or 40 and breakaway-element 50,250 and/or 250 ' are accommodated in modeling 400.The type of the heat transfer module 10,20,30,40 in modeling 400 and order are selected as making the Curvature Matching heat exchanger 100,200,300 of the heat exchanger 100,200 or 300 obtained be intended to the curvature of the part of the aircraft outer skin formed.When being received in modeling 400, multiple layer is relative to each other fixed.
As shown in Figure 6, modeling 400 is provided with the layer support portion 410 for supporting heat transfer module 10,20,30,40, and support portion 410 meets the curvature that heat exchanger 100,200 or 300 is intended to the part of the aircraft outer skin formed.Further, modeling 400 comprises displaceable element 420, displaceable element 420 passes through use two coil springs 430 by prestress, and for applying biasing force to heat transfer module 10,20,30,40, until heat transfer module 10,20,30,40 is relative to each other fixed along with the heat transfer module main body 10a of heat transfer module 10,20,30,40, direction that the side surface 16,26,36,46 of 20a, 30a, 40a is substantially vertical.
Claims (15)
1. a heat exchanger (100, 200, 300), multiple heat transfer module (10 is comprised, 20, 30, 40), the plurality of heat transfer module (10, 20, 30, 40) be arranged side by side to limit described heat exchanger (100, 200, 300) multilayer main body (102, 202, 302), wherein each heat transfer module (10, 20, 30, 40) at least one heat transfer medium channels (14 is provided with, 24, 34, 44), this at least one heat transfer medium channels (14, 24, 34, 44) be designed to allow heating agent to flow through, wherein said heat exchanger (100, 200, 300) multilayer main body (102, 202, 302) be provided with curvature at least partially, this curvature is designed to allow described heat exchanger (100, 200, 300) the bending exterior skin part of aircraft is used as, and wherein said multilayer main body (102, 202, 302) described adjacent heat transfer module (10 at least partially, 20, 30) this adjacent heat transfer module (10 is arranged to, 20, 30) central axis (A) has inclination angle each other, makes each heat transfer module (10, 20, 30, 40) aim at by described heat exchanger (100, 200, 300) outside face (106, 206, 306) center of the local osculating circle limited.
2. heat exchanger according to claim 1, the multilayer main body (102,202,302) of wherein said heat exchanger comprises at least one heat transfer module (10,20,30,40) with heat transfer module main body (10a, 20a, 30a, 40a), and described heat transfer module main body (10a, 20a, 30a, 40a) has the shape of cross section narrowed gradually towards the center of described osculating circle.
3. heat exchanger according to claim 2, wherein in the heat transfer module (30,40) comprising the heat transfer module main body (30a, 40a) with the shape of cross section narrowed gradually towards the center of described osculating circle, cone angle corresponds to the inclination angle of central axis (A) relative to the central axis (A) of adjacent heat transfer module (10,20,30,40) of described heat transfer module (30,40).
4. heat exchanger according to any one of claim 1 to 3, at least one heat transfer medium channels described (14,24,34,44) be wherein provided in described heat transfer module (10,20,30,40) is designed to allow heating agent and flows through along the direction parallel with the curvature axis (C) of described heat exchanger (100,200,300).
5. heat exchanger according to any one of claim 1 to 4, wherein the described heat transfer module main body (30a, 40a) of at least one heat transfer module (30,40) has inside face (38,48), this inside face (38,48) is suitable for a part for the inside face (104,204,304) forming described heat exchanger (100,200,300), and this inside face (38,48) has the curvature that the described heat exchanger of adaptation (100,200,300) is intended to the curvature of the inside face of the aircraft outer skin part formed.
6. heat exchanger according to any one of claim 1 to 5, wherein the described heat transfer module main body (30a) of at least one heat transfer module (30) has outside face (32), this outside face (32) is suitable for forming described heat exchanger (100, 200, 300) part for outside face, and this outside face (32) has the described heat exchanger (100 of adaptation, 200, 300) curvature of the curvature of the outside face of the aircraft outer skin part formed is intended to, wherein said heat transfer module main body (30a, inside face (38 40a), 48) radius of curvature is preferably less than the radius of curvature of the outside face (32) of described heat transfer module main body (30a).
7. heat exchanger according to any one of claim 1 to 6, wherein at least one heat transfer module (10,40) comprises rib (12), and this rib (12) forms the outshot of the outside face of the multilayer main body (102,202,302) of described heat exchanger.
8. heat exchanger according to claim 7, wherein said rib (12) is formed with the heat transfer module main body (10a, 40a) of described heat transfer module (10,40) integral, described rib (12) has substantially cylindrical-conical cross-sectional plane, and/or described rib (12) is provided with circular distal.
9. heat exchanger according to any one of claim 1 to 8, at least two wherein in the multilayer main body (102,202,302) of described heat exchanger (100,200,300) adjacent heat transfer modules (10,20,30,40) are separated from each other by breakaway-element (50,250,250 ').
10. heat exchanger according to claim 9, wherein said heat exchanger (100, 200, 300) breakaway-element (50 is comprised, 250), this breakaway-element (50, 250) be U-shaped substantially, and this breakaway-element (50, 250) have at adjacent heat transfer module (10, 20, 30, 40) described heat transfer module main body (10a, 20a, 30a, side surface (16 40a), 26, 36, 46) two the substantially parallel legs (52) extended between and along and described heat exchanger (100, 200, 300) pipe link (53) that the parallel direction of curvature axis (C) extends between described leg (52).
11. heat exchangers according to claim 9 or 10, wherein said heat exchanger (100,200,300) comprises breakaway-element (250 '), and this breakaway-element (250 ') is included in the air side fins extended between the side surface (16,26,36,46) of the described heat transfer module main body (10a, 20a, 30a, 40a) of adjacent heat transfer module (10,20,30,40), and (250 ' a).
The purposes of 12. 1 kinds of heat exchangers according to any one of claim 1 to 11 in aircraft.
13. 1 kinds of manufacture heat exchangers (100, 200, 300) method, wherein multiple heat transfer module (10, 20, 30, 40) be arranged side by side to limit described heat exchanger (100, 200, 300) multilayer main body (102, 202, 302), wherein each heat transfer module (10, 20, 30, 40) at least one heat transfer medium channels (14 is provided with, 24, 34, 44), this at least one heat transfer medium channels (14, 24, 34, 44) be designed to allow heating agent to flow through, wherein said heat exchanger (100, 200, 300) multilayer main body (102, 202, 302) be provided with curvature at least partially, this curvature is designed to allow described heat exchanger (100, 200, 300) the bending exterior skin part of aircraft is used as, and wherein said multilayer main body (102, 202, 302) described adjacent heat transfer module (10 at least partially, 20, 30) this adjacent heat transfer module (10 is arranged to, 20, 30) central axis (A) has inclination angle each other, makes each heat transfer module (10, 20, 30, 40) aim at by described heat exchanger (100, 200, 300) outside face (106, 206, 306) center of the local osculating circle limited.
14. methods according to claim 13, wherein said heat transfer module (10,20,30,40) is arranged side by side in modeling (400), and when being disposed in described modeling (400) relative to being fixed to one another.
15. methods according to claim 13 or 14, wherein apply biasing force along the direction substantially vertical with the side surface (16,26,36,46) of the heat transfer module main body (10a, 20a, 30a, 40a) of described heat transfer module (10,20,30,40) to the described heat transfer module be arranged side by side (10,20,30,40), until described heat transfer module (10,20,30,40) is relative to each other fixing.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201261620474P | 2012-04-05 | 2012-04-05 | |
| EP12002472.4 | 2012-04-05 | ||
| US61/620,474 | 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104245510A true CN104245510A (en) | 2014-12-24 |
| CN104245510B CN104245510B (en) | 2017-01-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380022262.1A Expired - Fee Related CN104245510B (en) | 2012-04-05 | 2013-03-28 | Craft outer skin heat exchanger and method for manufacturing craft outer skin heat exchanger |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20150027676A1 (en) |
| EP (1) | EP2834149A1 (en) |
| CN (1) | CN104245510B (en) |
| WO (1) | WO2013149936A1 (en) |
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| CN107966044A (en) * | 2017-11-17 | 2018-04-27 | 珠海格力电器股份有限公司 | Skin heat exchanger, vehicle air conditioning system and vehicle |
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| US10059435B2 (en) | 2014-12-04 | 2018-08-28 | Parker-Hannifin Corporation | Low drag skin heat exchanger |
| US10443436B2 (en) | 2016-07-01 | 2019-10-15 | General Electric Company | Modular annular heat exchanger |
| US10670346B2 (en) * | 2018-01-04 | 2020-06-02 | Hamilton Sundstrand Corporation | Curved heat exchanger |
| 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 |
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| Publication number | Publication date |
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| US20150027676A1 (en) | 2015-01-29 |
| EP2834149A1 (en) | 2015-02-11 |
| CN104245510B (en) | 2017-01-18 |
| WO2013149936A1 (en) | 2013-10-10 |
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