CN206187352U - Liquid cooling heat exchanger - Google Patents
Liquid cooling heat exchanger Download PDFInfo
- Publication number
- CN206187352U CN206187352U CN201620939025.2U CN201620939025U CN206187352U CN 206187352 U CN206187352 U CN 206187352U CN 201620939025 U CN201620939025 U CN 201620939025U CN 206187352 U CN206187352 U CN 206187352U
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- Prior art keywords
- heat exchanger
- core body
- aircraft
- heat
- cold
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- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The utility model discloses a liquid cooling heat exchanger, including heat exchanger shell, collector and heat exchanger core body, heat exchanger shell set up the outside at heat exchanger core body to cladding heat exchanger core body, the collector setting on heat exchanger core body, heat exchanger core body on be equipped with working medium import and working medium outlet, heat exchanger shell be aircraft skin, heat exchanger shell and the conformal setting of aircraft skin, the heat exchange surface of this heat exchanger is conformal with aircraft skin, has both satisfied the requirement of aircraft appearance, satisfies the requirement of heat exchanger efficiency and performance again.
Description
Technical field
The utility model is related to a kind of heat exchanger, more particularly to the liquid cold heat exchanger being just used on aircraft or unmanned plane.
Background technology
Liquid cold heat exchanger is hot side liquid, and cold side is a kind of heat exchanger of air.The liquid cold heat exchange conformal with aircraft skin
Device can be described as covering heat exchanger.Its conformal technology is to realize the key of covering heat exchanger.This project can be used in aircraft, gondola,
For cooling down from high power electronic component coolant.Aircraft makes covering approximate in high-altitude flight by high-altitude cold air
It is changed into constant temperature cold wall, covering heat exchanger outer surface uses as the covering of engine body exterior, is passed through inside covering heat exchanger and Gao Gong
Rate electronic component exchanged heat after hot working fluid, covering heat exchanger outside atmosphere as low-temperature receiver is entered using covering heat exchanger
Row heat exchange cools down the purpose of hot working fluid to reach.
In scounting aeroplane environmental control system process is developed, due to the low detectivity requirement of unmanned plane, if with tradition
Heat exchanger is as environmental control system core annex, it is necessary to open punching press porting in fuselage, this is that a comparing is tight to designer
High test.Because the country is there is presently no so special heat exchanger：It is low in high cruise ambient temperature using aircraft
Innate advantage, i.e., with covering as the cold side of heat exchanger heat exchanger.In this way, then fuselage need not open ram intake.
Another have the China Patent No. to be：201110113992.5, date of publication is 2011.12.28, discloses a kind of aircraft individual layer
Air-liquid skin heat exchange method, belongs to environment controlling technique field, is to reduce aircraft ram-air amount, improve empty solution-air
The new technology of body heat exchange efficiency, is the improvement to air-liquid heat exchange method.Fuselage outer surface install single-layer air-
Liquid covering heat exchanger, the air-liquid covering heat exchanger includes outer surface (1), and inner surface (2), inlet (3) goes out
Liquid mouthful (4), sealing termination (5), (6), and divide (8) with Fuselage connection, installed between outer surface (1) and inner surface (2)
Individual layer radiating fin (7).Compared with air-air covering heat exchanger, its coefficient of heat transfer is higher, and heat exchange amount is bigger for the method,
Refrigeration is more preferable；Compared with sky-liquid heat exchanger, air-liquid covering heat exchanger is utilized and combined together with aircraft skin
Boundary-layer heat dissipation technology, eliminate traditional ram air duct cooling air mode, substantially reduce combustion of the system to aircraft
Oily panelty, when improve Aircraft；Aircraft Stealth Fighter requirement can be met simultaneously.Above-mentioned patent does not increase without porting
Plus aircraft aerodynamic drag, fuel penalty be small, Stealth Fighter is good；Using the cold heat exchange of liquid, heat exchange efficiency is higher.But its heat exchanger
Profile is designed by aircraft configuration, and its machine-shaping is difficult；Liquid cold passage need to carry out gas-tight design, and heat exchanger is relatively difficult to ensure when being molded
Card.
Utility model content
In order to overcome the defect of above-mentioned prior art, the utility model provides a kind of liquid cold heat exchanger, the heat exchanger
Heat exchange surface is conformal with aircraft skin, has both met the requirement of aircraft configuration, and the requirement of heat exchanger efficiency and performance is met again.
In order to solve the above-mentioned technical problem, the technical solution adopted in the utility model is：
A kind of liquid cold heat exchanger, it is characterised in that：Including outer cover of heat exchanger, collector and heat exchanger core body, described changes
Hot device shell is arranged on the outside of heat exchanger core body, and coats heat exchanger core body, and described collector is arranged on heat exchanger core body
On, described heat exchanger core body is provided with working medium import and sender property outlet, and described outer cover of heat exchanger is aircraft skin, described
Outer cover of heat exchanger and the conformal setting of aircraft skin.
Described outer cover of heat exchanger include the heat exchanger being connected with each other it is cold while and during exchanger heat, the cold side of described heat exchanger
It is to be arranged on exchanger heat side with the conformal setting of aircraft skin, described collector, working medium import and sender property outlet.
Described heat exchanger core body carries out welded seal into heat exchanger with described aircraft skin, then will be welded by mould
Good heat exchanger is pressed into the shape conformal with aircraft outer surface.Described welding, compacting are known method.
The utility model has advantages below：
1st, the utility model includes outer cover of heat exchanger, collector and heat exchanger core body, and described outer cover of heat exchanger is arranged on
The outside of heat exchanger core body, and heat exchanger core body is coated, described collector is arranged on heat exchanger core body, described heat exchanger
Core body is provided with working medium import and sender property outlet, and described outer cover of heat exchanger is aircraft skin, described outer cover of heat exchanger with fly
The conformal setting of machine covering.Conformal technology can well realize fitting for heat exchanger core body and aircraft skin, both meet aircraft configuration
Requirement, the requirement of heat exchanger efficiency and performance is met again.
2nd, outer cover of heat exchanger of the present utility model include the heat exchanger being connected with each other it is cold while and during exchanger heat, described changes
The hot cold side of device is to be arranged on exchanger heat side with the conformal setting of aircraft skin, described collector, working medium import and sender property outlet
On.Described heat exchanger core body carries out welded seal into heat exchanger with described aircraft skin, then will be welded by mould
Heat exchanger is pressed into the shape conformal with aircraft outer surface.Simplify processing technology, it is to avoid be first molded and weld afterwards needs and carry out
The problem of cambered surface welding, and need using complex proprietary frock weld the problem of positioning.Avoid welding stress simultaneously
Influence to thin-walled heat exchanger profile.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is using the thin-walled liquid cold heat exchanger core body figure of single layer flow path；
Fig. 3 aircraft outer skins as liquid cold heat exchanger heat exchange shell figure；
Fig. 4 is that heat exchanger core body carries out welded seal figure with the covering of flat board；
Fig. 5 is that the heat exchanger that will be welded by mould is pressed into the shape graph conformal with aircraft outer surface；
Marked in figure：1st, outer cover of heat exchanger, 2, working medium import, 3, collector, 4, heat exchanger core body, 5, sender property outlet, 6,
Exchanger heat side, 7, the cold side of heat exchanger.
Specific embodiment
The utility model is described further below in conjunction with the accompanying drawings：
Embodiment 1
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4 and Fig. 5, a kind of liquid cold heat exchanger, including outer cover of heat exchanger 1, collector 3 and change
Hot device core body 4, described outer cover of heat exchanger 1 is arranged on the outside of heat exchanger core body 4, and coats heat exchanger core body 4, heat exchanger core
Working medium is formed in body 4（Or caloic）Passage, described collector 3 is arranged on heat exchanger core body 4, and collector 3 is located at that liquid is cold changes
On the both sides inwall of hot device, for the coolant of inlet ductwork to be evenly distributed in each bar passage of heat exchanger, and will flow through
The coolant of each bar passage is collected into and imports in outlet conduit together, and described heat exchanger core body 4 is provided with working medium import 2 and work
Matter outlet 5, described outer cover of heat exchanger 1 is aircraft skin, described outer cover of heat exchanger 1 and the conformal setting of aircraft skin, described
Conformal setting, i.e. outer cover of heat exchanger 1 is made basically identical with the shape of aircraft skin.
Further, described outer cover of heat exchanger 1 includes that the heat exchanger being connected with each other is cold at 7 and exchanger heat 6, described
The cold side 7 of heat exchanger be aircraft outer layer, the one side with air contact, its to one side be exchanger heat side 6, described heat exchange
The cold side 7 of device be with the conformal setting of aircraft skin, will the cold side 7 of heat exchanger be made of aircraft skin, and with aircraft on the outside of covering
Shape is consistent, and described collector 3, working medium import 2 are arranged on exchanger heat side 6 with sender property outlet 5.
Further, preparation method of the present utility model：Heat exchanger core body is the thin-walled liquid cold heat exchanger core of single layer flow path
Body（As shown in Figure 2）, aircraft outer skin as liquid cold heat exchanger heat exchange shell（As shown in Figure 3）, described heat exchanger core body
Welded seal into heat exchanger is carried out with described aircraft skin（As shown in Figure 4）, then the heat exchanger pressure that will be welded by mould
It is made the shape conformal with aircraft outer surface（As shown in Figure 5）.Welding described in the utility model, compacting are known method.
Claims (3)
1. a kind of liquid cold heat exchanger, it is characterised in that：Including outer cover of heat exchanger (1), collector (3) and heat exchanger core body (4), institute
The outer cover of heat exchanger (1) stated is arranged on the outside of heat exchanger core body (4), and coats heat exchanger core body (4), described collector
(3) it is arranged on heat exchanger core body (4), described heat exchanger core body (4) is provided with working medium import (2) and sender property outlet (5), institute
The outer cover of heat exchanger (1) stated is aircraft skin.
2. a kind of liquid cold heat exchanger according to claim 1, it is characterised in that：Described outer cover of heat exchanger (1) is including phase
The heat exchanger for connecting is cold at (7) and exchanger heat (6), the cold side of described heat exchanger (7) be with the conformal setting of aircraft skin,
Described collector (3), working medium import (2) and sender property outlet (5) are arranged on exchanger heat side (6).
3. a kind of liquid cold heat exchanger according to claim 2, it is characterised in that：Described heat exchanger core body (4) with it is described
Aircraft skin carry out welded seal into heat exchanger, then be pressed into by the heat exchanger that mould will be welded and be total to aircraft outer surface
The shape of shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620939025.2U CN206187352U (en) | 2016-08-25 | 2016-08-25 | Liquid cooling heat exchanger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620939025.2U CN206187352U (en) | 2016-08-25 | 2016-08-25 | Liquid cooling heat exchanger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206187352U true CN206187352U (en) | 2017-05-24 |
Family
ID=58728554
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620939025.2U Active CN206187352U (en) | 2016-08-25 | 2016-08-25 | Liquid cooling heat exchanger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206187352U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100273A (en) * | 2017-11-29 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft fuel oil cooling system |
| CN111564687A (en) * | 2020-03-30 | 2020-08-21 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Curved surface conformal antenna liquid cooling plate structure for 3D printing |
| CN112177778A (en) * | 2020-08-28 | 2021-01-05 | 成都飞机工业（集团）有限责任公司 | Temperature and pressure regulating method for bleed air of engine |
-
2016
- 2016-08-25 CN CN201620939025.2U patent/CN206187352U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100273A (en) * | 2017-11-29 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft fuel oil cooling system |
| CN108100273B (en) * | 2017-11-29 | 2021-08-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel cooling system |
| CN111564687A (en) * | 2020-03-30 | 2020-08-21 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Curved surface conformal antenna liquid cooling plate structure for 3D printing |
| CN112177778A (en) * | 2020-08-28 | 2021-01-05 | 成都飞机工业（集团）有限责任公司 | Temperature and pressure regulating method for bleed air of engine |
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