CN221036946U - Multi-channel integrated aviation tube type heat exchanger - Google Patents
Multi-channel integrated aviation tube type heat exchanger Download PDFInfo
- Publication number
- CN221036946U CN221036946U CN202322591534.3U CN202322591534U CN221036946U CN 221036946 U CN221036946 U CN 221036946U CN 202322591534 U CN202322591534 U CN 202322591534U CN 221036946 U CN221036946 U CN 221036946U
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- Prior art keywords
- tube
- heat dissipation
- heat exchanger
- shell
- heat
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- 230000017525 heat dissipation Effects 0.000 claims abstract description 45
- 238000001816 cooling Methods 0.000 claims description 16
- 238000007789 sealing Methods 0.000 claims description 5
- 238000005192 partition Methods 0.000 claims description 4
- 238000005219 brazing Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 2
- 230000010354 integration Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The utility model belongs to the technical field of aviation heat exchangers, and particularly discloses a multichannel integrated aviation tube type heat exchanger. The heat dissipation core body (100) comprises a series connection type heat dissipation core body, and the heat dissipation core body can simultaneously realize heat exchange of multiple paths of media, realize integrated design of the aviation heat exchanger, optimize space arrangement of aircraft accessories, simplify system pipelines and installation, reduce weight of an aircraft system, improve reliability of the aircraft system and meet development requirements of future aviation heat exchangers.
Description
Technical Field
The utility model belongs to the technical field of aviation heat exchangers, and particularly discloses a multichannel integrated aviation tube type heat exchanger.
Background
The traditional shell and tube heat exchanger adopts the structure of two medium channels to exchange heat, and the function is single, leads to aircraft heat exchanger annex quantity to be many, and the fault rate also can correspondingly increase, influences the flight reliability of complete machine, has also increased aircraft annex space arrangement's complexity simultaneously, and heat exchanger volume and weight are big, the pipeline is complicated, the interface is many, the reliability reduces. With the improvement of the new generation of airplane functional performance and the more complex of the airplane self system, the functions needing to be born by accessories are more and more increased, in recent years, in order to optimize the space arrangement of the airplane accessories, simplify the system pipelines, reduce the weight of the airplane, improve the reliability of the airplane, the requirements on the integration level of the system are higher and higher, and on the premise of completing the established functions, the fewer the number of the accessories, the higher the integration level is, so that the weight reduction and the reliability improvement of the airplane are more beneficial. The heat exchanger plays an increasingly important role as a main device for radiating heat of onboard devices of various systems, and the integration of functions and structures is a necessary requirement for future development of aviation heat exchangers.
Disclosure of utility model
The purpose of the utility model is that: the multi-channel integrated aviation tube type heat exchanger can simultaneously realize heat exchange of multiple media, realize integrated design of the aviation heat exchanger, optimize space arrangement of aircraft accessories, simplify system pipelines and installation, reduce weight of an aircraft system, improve reliability of the aircraft system and meet development requirements of future aviation heat exchangers.
The technical scheme of the utility model is as follows: the multi-channel integrated aviation tube type heat exchanger comprises a serial heat dissipation core body 100, a shell 14, a first sealing head 1 and a second sealing head 13; the serial heat dissipation core 100 comprises a plurality of groups of tube type heat dissipation core units 5 which are sequentially connected in series, wherein the tube type heat dissipation core units 5 in each group are communicated with each other; the series heat dissipation core 100 is disposed in the casing 14 with two open ends, the ends of each group of tubular heat dissipation core units 5 are respectively connected with the inner surface of the casing 14 in a sealing manner, a plurality of segments of mutually isolated tubular cooling cavities are formed in the casing 14, and each segment of tubular cooling cavity is provided with an inlet and an outlet for cooling working medium between the tubular cooling cavities; the first seal head 1 and the second seal head 13 are respectively sealed at two ends of the shell 14, the first seal head 1 is provided with an in-column cooling working medium inlet, and the second seal head 13 is provided with an in-column cooling working medium outlet.
In one possible embodiment, the shell and tube heat dissipation core unit 5 comprises an end plate 10, a heat dissipation shell and tube 11 and a partition plate 12; the end plates 10 penetrate through the end parts of the heat dissipation tubes 11 and are sleeved and fixed at the two ends of the heat dissipation tubes 11, and the partition plates 12 are sleeved and fixed on the heat dissipation tubes 11 in a staggered manner at intervals in a segmented mode so as to form a flow channel from a cooling working medium inlet between the tubes to a cooling working medium outlet between the tubes.
In one possible embodiment, a plurality of groups of tube-type heat dissipation core units 5 connected in series in turn are butted against each other and welded.
In one possible embodiment, the heat dissipation tube array 11 of the heat dissipation core unit 5 and the end plate 10 are connected by expansion interference fit or brazing.
In one possible embodiment, the number of the tube array heat dissipation core units 5 is 2.
In one possible embodiment, the number of baffles 12 is 3.
The utility model has the technical effects that: the heat exchanger plays an increasingly important role as a main device for radiating heat of onboard devices of various systems, and the integration of functions and structures is a necessary requirement for future development of aviation heat exchangers. The multi-channel integrated aviation tube type heat exchanger provided by the utility model can realize simultaneous heat exchange of multiple media, so that the product structure is simplified, the welding lines are fewer, the weight is lighter, and the reliability is obviously improved, thereby solving the problem of heat exchanger integrated design, and having wide application direction and good application prospect.
Drawings
Fig. 1 is a schematic structural view of a preferred embodiment of the present utility model.
The heat dissipation device comprises a seal head 1, a medium c inlet 2, a medium a outlet 3, a medium a inlet 4, a heat dissipation core a5, a heat dissipation core b6, a medium b outlet 7, a medium b inlet 8 and a medium c outlet 9.
Fig. 2 is a schematic structural view of a tubular heat dissipation core unit 5 according to a preferred embodiment of the present utility model.
Wherein, end plate 10, heat dissipation tubulation 11, baffle 12.
Detailed Description
The utility model is further illustrated by the following examples in conjunction with the accompanying drawings:
As shown in fig. 1, a multi-channel integrated aviation shell and tube heat exchanger comprises a sealing head 1, a medium c inlet 2, a medium a outlet 3, a medium a inlet 4, a heat dissipation core a5, a heat dissipation core b6, a medium b outlet 7, a medium b inlet 8 and a medium c outlet 9, wherein the heat dissipation core a5 and the heat dissipation core b6 comprise an end plate 10, a heat dissipation shell and tube 11 and a partition plate 12; the heat dissipation core a5 and the heat dissipation core b6 are connected by the end plate 10.
Medium c enters the heat dissipation core a5 from the medium c inlet 2 and flows in the pipe; medium a enters the heat dissipation core a5 from the medium a inlet 4 and flows out from the medium a outlet 3 to flow between the pipes, and heat exchange between the medium a and the medium c is realized in the medium flowing process.
Medium c flows out from the heat dissipation core a6 into the heat dissipation core b6 to flow in the pipe, and flows out from the medium c outlet 9, medium b enters the heat dissipation core b6 from the medium b inlet 8 and flows out from the medium b outlet 7 to flow between the pipes, and heat exchange between the medium b and the medium c is realized in the medium flowing process.
Claims (6)
1. The multi-channel integrated aviation tube type heat exchanger is characterized by comprising a serial heat dissipation core body (100), a shell (14), a first end enclosure (1) and a second end enclosure (13); the series heat dissipation core (100) comprises a plurality of groups of tubular heat dissipation core units (5) which are sequentially connected in series, and the tubular heat dissipation core units (5) of each group are communicated with each other; the series-connected heat dissipation core body (100) is arranged in the shell (14) with openings at two ends, the end parts of each group of tube-array heat dissipation core body units (5) are respectively connected with the inner surface of the shell (14) in a sealing way, a plurality of sections of tube-array cooling cavities which are isolated from each other are formed in the shell (14), and each section of tube-array cooling cavity is provided with a cooling working medium inlet and a cooling working medium outlet between tubes; the first end enclosure (1) and the second end enclosure (13) are respectively sealed at two ends of the shell (14), the first end enclosure (1) is provided with a related cooling working medium inlet, and the second end enclosure (13) is provided with a cooling working medium outlet in a tube array.
2. A multichannel integrated aviation shell-and-tube heat exchanger according to claim 1, characterized in that the shell-and-tube heat-dissipating core unit (5) comprises end plates (10), heat-dissipating shell-and-tube (11), baffles (12); the end plates (10) penetrate through the end parts of the heat dissipation tubes (11) and are sleeved and fixed at the two ends of the heat dissipation tubes (11), and the partition plates (12) are alternately sleeved and fixed on the heat dissipation tubes (11) at intervals in a staggered manner to form a flow channel from an inter-tube cooling working medium inlet to an inter-tube cooling working medium outlet.
3. A multichannel integrated aviation tube heat exchanger according to claim 1, characterized in that groups of tube heat dissipation core units (5) connected in series in turn are butted against each other and welded.
4. A multichannel integrated air tube heat exchanger according to claim 2, characterized in that the heat radiating tubes (11) of the heat radiating core unit (5) and the end plates (10) are connected by expansion interference fit or brazing.
5. A multichannel integrated air tube heat exchanger according to claim 1, characterized in that the number of tube array heat sink core units (5) is 2.
6. A multichannel integrated air tube heat exchanger according to claim 2, wherein the number of baffles (12) is 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322591534.3U CN221036946U (en) | 2023-09-22 | 2023-09-22 | Multi-channel integrated aviation tube type heat exchanger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322591534.3U CN221036946U (en) | 2023-09-22 | 2023-09-22 | Multi-channel integrated aviation tube type heat exchanger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221036946U true CN221036946U (en) | 2024-05-28 |
Family
ID=91171043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322591534.3U Active CN221036946U (en) | 2023-09-22 | 2023-09-22 | Multi-channel integrated aviation tube type heat exchanger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221036946U (en) |
-
2023
- 2023-09-22 CN CN202322591534.3U patent/CN221036946U/en active Active
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