CN105509514A - Fin tube type gas-liquid heat exchanger - Google Patents
Fin tube type gas-liquid heat exchanger Download PDFInfo
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- CN105509514A CN105509514A CN201510912587.8A CN201510912587A CN105509514A CN 105509514 A CN105509514 A CN 105509514A CN 201510912587 A CN201510912587 A CN 201510912587A CN 105509514 A CN105509514 A CN 105509514A
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- heat exchanger
- shell
- liquid
- heat exchange
- interlayer
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D7/00—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
- F28D7/16—Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being arranged in parallel spaced relation
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention discloses a fin tube type gas-liquid heat exchanger. The fin tube type gas-liquid heat exchanger is a cuboid of which the cross section is a rectangle, and comprises a plurality of heat exchange units, high-temperature gas inlets, liquid outlets, liquid inlets and high-temperature gas outlets, wherein through holes are formed in the bottom surfaces of the heat exchange units; a shell is arranged on the side surfaces; four sequentially adjacent shell interlayers are arranged in the shell; a first shell interlayer is communicated with a second shell interlayer and a third shell interlayer; a fourth shell interlayer is communicated with the second shell interlayer and the third shell interlayer; and inclined baffle plates are arranged in the second shell interlayer and the third shell interlayer. According to the heat exchanger provided by the invention, the high-temperature gas is cooled after the heat of the high-temperature gas is released through liquid flowing from the shell pass to the tube pass, and at the same time, the high-temperature gas is cooled by liquid (such as kerosene) of the shell interlayers, so that the heat exchange efficiency of the heat exchanger is improved; the liquid of the shell interlayers cools the wall surface of the heat exchanger shell, the heat exchange area is enlarged, and the heat exchange efficiency is improved, so that the heat exchanger material is protected from being damaged due to overheating; and the heat exchanger is compact in structure, simple in manufacturing, and easy to achieve.
Description
Technical field
The present invention relates to heat convection technical field, be specifically related to a kind of fin-tube type gas liquid exchanger.
Background technology
The science of hypersonic technology, advance and multifunctionality make it all serve key effect in a lot of technical field, especially at high-tech aerospace field.The flight Mach number that can reach along with aircraft constantly promotes, and the Aerodynamic Heating that aircraft surface is subject to high velocity air is more and more stronger, causes temperature constantly to raise.If temperature exceedes the working limit temperature of component materials, not only can shorten working life, even there will be material and burnt, the danger of normal vehicle operation cannot be ensured.
For the particularity of its thermal protection condition of scramjet engine and operating thermal environment, propose multiple thermal protection method at present, wherein mainly contained:
(1) gaseous film control
Gaseous film control refer to hot near wall along its tangential direction or be used for along certain angle to high temperature air jet cool air-flow, under the acting in conjunction of pressure and frictional force, the cold airflow injected can be attached to the relatively low cooling air film of hot near wall formation temperature, wall and high-temperature gas are kept apart, thus avoid high-temperature gas and wall direct contact heat transfer, simultaneously, some high-temperature gases or thermal-flame can be taken away the radiations heat energy that hot wall face is caused, thus good thermal protection effect be played to wall.
(2) radiation cooling
Radiation cooling is the refractory metal wall using individual layer, as the outside wall surface of its thrust chamber, by carrying out heat-radiation heat-dissipating to its surrounding volume, reaches the requirement cooled.
(3) ablation cooling
Ablation cooling refers to and is attached to coating material on wall at high temperature because fusing, evaporation and chemical reaction are to absorb heat, this will make the cooling blast that neighbouring generation one deck temperature in hot wall face is lower, by to boundary layer temperature by reduction, thus reach the effect of cooling.
(4) Sweat coolling
The cooling of sweating formula refers to that cooling agent flows through the many small hole flowing in combustion chamber that wall is opened, and high-temperature gas and wall is kept apart, thus reaches cooling effect.
(5) active cooling is regenerated
Regeneration active cooling is the one of the convection current type of cooling, is when the engine operates, uses propellant as cooling agent, injects cooling duct, cool Inner Wall of Combustion Chamber, after temperature raises, then enters combustion chambers burn acting.The heat that cooling agent is absorbed by thrust chamber inwall has got back to again combustion chamber, achieves the regeneration of energy, is therefore called re-generatively cooled.
To regeneration active cooling be incorporated in the middle of the cooling system of supersonic aircraft air intake duct front end use, just need to design a kind of heat exchange efficiency high, take up room little cooler, this is not only faced with the difficult problem pursued and increase heat exchange area as far as possible in limited less space, improve heat exchange efficiency, also will under supersonic state of flight, the very high operating temperature that heat exchanger materials itself is born, needs design heat exchanger wall cooling scheme.
Summary of the invention
For realize heat exchanger wall participate in cooling, the invention provides a kind of fin-tube type gas liquid exchanger, this heat exchanger can improve under high hot-fluid, high reynolds number, heat exchange efficiency.
For achieving the above object, a kind of fin-tube type gas liquid exchanger provided by the invention, comprises some heat exchange units and high-temperature fuel gas import, liquid fuel outlet, liquid fuel inlet, high-temperature fuel gas outlet.The bottom surface of described heat exchange unit arranges through hole, and side arranges housing; In housing, crustless sandwich is set, interlayer is divided into first, second, third and fourth four crustless sandwiches, and four crustless sandwiches are adjacent successively, and first and second, three crustless sandwiches communicate, 4th and second and third crustless sandwich also communicate, second and the 3rd arranges slanting baffle in crustless sandwich.Arrange plain fin in described through hole, plain fin is parallel with through-bore axis or acutangulate or become obtuse angle; Described heat exchange unit also arranges heat exchanger tube, and described heat exchanger tube is through plain fin, and the opening of heat exchanger tube is positioned at crustless sandwich.
Use baffle plate to separate between described first crustless sandwich of adjacent heat exchange unit, between described 4th crustless sandwich, also use baffle plate to separate.
Described high-temperature gas import and high-temperature gas outlet are the through hole of first and last heat exchange unit, and described liquid outlet and liquid-inlet are separately positioned on first with on the housing of last heat exchange unit.
Fin-tube type gas liquid exchanger of the present invention, high-temperature gas--combustion gas by means of only in liquid (as the kerosene) release heat of shell fluid flow to tube side flow, is not cooled, and is also cooled by the liquid of crustless sandwich (as kerosene) simultaneously.The liquid of crustless sandwich, as kerosene cooling heat exchanger shell wall side simultaneously, adds heat exchange area, improves heat exchange efficiency, thus protection heat exchanger materials is unlikely damages with because of overheated.This heat exchanger structure is compact, manufactures simple, is easy to realize.
Accompanying drawing explanation
Fig. 1 is heat exchanger contour structures schematic diagram of the present invention;
Fig. 2 is heat exchange unit structural representation of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention will be further described.Should be clear, the specific embodiments of the invention described in accompanying drawing are only and use of the present invention are described, it is not strictly drawn in actual size and ratio.Therefore, the accompanying drawing in the application should not be construed as any limitation of the invention.Following used " first ", " second ", " front " and " afterwards ", " side ", " above " and " below " etc. just protect the structure of instrument for convenience of description, and not order of representation or relative position relation, does not cause restriction to protection domain.
Heat exchanger of the present invention, makes the heat of the high-temperature fuel gas after fuel combustion be taken away by low temp fuel (as kerosene etc.) by heat convection principle, thus reaches the object of cooling down high-temperature combustion gas and heat exchanger materials.Heat exchanger can adopt the shape that cuboid or cylinder or other are suitable, and the present embodiment illustrates the structure of heat exchanger with cuboid.
As shown in Fig. 1 to 2, the cuboid of fin-tube type gas liquid exchanger of the present invention to be cross section be rectangle, comprises some heat exchange units and liquid outlet 1, high-temperature gas import 2, liquid-inlet 3, high-temperature gas outlet 4.The bottom surface of described heat exchange unit arranges through hole, and side arranges housing; Arrange crustless sandwich 8 in housing, interlayer is divided into four, upper and lower, left and right crustless sandwich 81,82,83,84, and four crustless sandwiches are adjacent successively, and upper shell interlayer and left and right crustless sandwich all communicate, and lower house interlayer and left and right crustless sandwich also all communicate.First, second slanting baffle 71,72 is set in left and right crustless sandwich.Between the upper shell interlayer of adjacent heat exchange unit, use the 3rd, fourth gear plate 73,74 separate, and also use baffle plate to separate between lower house interlayer.Arrange plain fin 6 in through hole, plain fin 6 is parallel with through-bore axis or acutangulate or become obtuse angle; Heat exchange unit also arranges heat exchanger tube 5, and heat exchanger tube 5 is through plain fin, and the opening of heat exchanger tube 5 is positioned at crustless sandwich.High-temperature fuel gas import 2 and high-temperature fuel gas outlet 4 are the through hole of first and last heat exchange unit, and liquid outlet 1 and liquid-inlet 3 are separately positioned on first with on the housing of last heat exchange unit.
High-temperature fuel gas after burning enters in fin-tube type gas liquid exchanger of the present invention through high-temperature fuel gas import 2, fuels such as coal oil enters in heat exchanger through liquid-inlet 3, high/low temperature fluid is after heat exchanger carries out exchange heat, high-temperature fuel gas after temperature reduces flows out through high-temperature fuel gas outlet 4, liquid such as kerosene after temperature raises flows out from liquid outlet 1, enter combustion chambers burn again, realize re-generatively cooled.
Heat exchanger heat exchange unit crustless sandwich operation principle is as follows: each heat exchange unit has four, upper and lower, left and right crustless sandwich respectively.Upper and lower shell interlayer body all arranges baffle plate, to block and being communicated with of adjacent heat exchange unit.But upper interlayer communicates with left and right interlayer, lower interlayer also communicates with left and right interlayer, as shown in Figure 2 (in Fig. 2, thick arrow represents), in the interlayer of the heat exchange unit left and right sides, arranges slanting baffle respectively, goes up interlayer like this and lower interlayer cannot communicate.Fuels such as coal oil flows into from the lower interlayer of heat exchange unit, heat exchanger tube is entered under the driving of pressure, with heat exchanger shell pass combustion gas heat-shift, then interlayer on housing is entered, be divided into two strands afterwards, flow to two crustless sandwiches in left and right respectively, under the stop of adjacent two heat exchange unit slanting baffles, flow into the lower house interlayer of next heat exchange unit along heat exchanger side wall surface.This completes the work of fuel in a heat exchange unit.Can find out, by the flowing of design fuel at crustless sandwich, four walls of heat exchanger all receive the cooling of kerosene.In each heat exchange unit, fuel all repeats above flow circuit at crustless sandwich, so just achieves the object cooled by heat exchanger shell interlayer.
With application example, the application of heat exchanger of the present invention in all kinds of Aero-Space engine is described below:
Application example 1
In rocket chamber, fuel gas temperature is up to 3000 ~ 4700K, normally a few MPa of gaseous-pressure (tens atmospheric pressure), and high reaches 20 MPas (about 200 atmospheric pressure).Whole thrust chamber inwall is subject to heat intensive, and the most serious position is near nozzle throat, and heat flow density can up to 104 ~ 105 kilowatts/meter.The fin-tube type gas liquid exchanger of band housing cooling of the present invention is applied to this engine, high-temperature fuel gas after burning enters in fin-tube type gas liquid exchanger of the present invention through fuel gas inlet 1, liquid fuel enters in heat exchanger through fuel inlet 4, after high/low temperature fluid carries out exchange heat in heat exchanger, high-temperature fuel gas after temperature reduces flows out through gas outlet 3, and the liquid fuel after temperature raises flows out through fuel outlet 2.With the combustion gas of liquid fuel cooling down high-temperature, be heated zero to protect, assembly, improve their performance.Fin-tube type gas liquid exchanger crustless sandwich cooling system works simultaneously, and reason is overheated not impaired for protection heat exchanger.
Application example 2
Turbojet combustion chamber flame temperature can reach 2300K, and Turbine Inlet Gas Temperature reaches 1600K.Ensure that Heating Components normally works or the performance that improves them all depends on cooling technology.Spiral baffle heat exchanger of the present invention can be adopted, by the combustion gas of liquid fuel cooling down high-temperature.The fin-tube type gas liquid exchanger of band housing cooling of the present invention is applied to this engine, high-temperature fuel gas after burning enters in heat exchanger through fuel gas inlet 1, liquid fuel enters in heat exchanger through fuel inlet 3, after high/low temperature fluid carries out exchange heat in heat exchanger, high-temperature fuel gas after temperature reduces flows out through gas outlet 4, and the liquid fuel after temperature raises flows out through fuel outlet 2.With the combustion gas of liquid fuel cooling down high-temperature, be heated zero to protect, assembly, improve their performance.Fin-tube type gas liquid exchanger crustless sandwich cooling system works simultaneously, and reason is overheated not impaired for protection heat exchanger.
Application example 3
The aloof punching engine of hypersonic aircraft, when the engine operates, adopt fin-tube type gas liquid exchanger of the present invention, use propellant as cooling agent, inject cooling duct, high-temperature fuel gas in combustion chamber is cooled, after propellant temperature raises, enter combustion chambers burn acting again, realize re-generatively cooled.
Based on description of the preferred embodiment of the present invention, should be clear, the present invention limited by appending claims is not limited only to the specific detail set forth in description above, and what do not depart from present inventive concept or scope may reach object of the present invention equally to many apparent changes of the present invention.
Claims (3)
1. a fin-tube type gas liquid exchanger, is characterized in that: the cuboid of to be cross section be rectangle, comprises some heat exchange units and high-temperature fuel gas import, liquid outlet, liquid inlet, high-temperature fuel gas outlet; The bottom surface of described heat exchange unit arranges through hole, and side arranges housing; In housing, crustless sandwich is set, interlayer is divided into first, second, third and fourth four crustless sandwiches, and four crustless sandwiches are adjacent successively, and first and second, three crustless sandwiches communicate, 4th and second and third crustless sandwich also communicate, second and the 3rd arranges slanting baffle in crustless sandwich; Arrange plain fin in described through hole, plain fin is parallel with through-bore axis or acutangulate or become obtuse angle; Described heat exchange unit also arranges heat exchanger tube, and described heat exchanger tube is through plain fin, and the opening of heat exchanger tube is positioned at crustless sandwich.
2. fin-tube type gas liquid exchanger according to claim 1, is characterized in that: use baffle plate to separate between described first crustless sandwich of adjacent heat exchange unit, also uses baffle plate to separate between described 4th crustless sandwich.
3. fin-tube type gas liquid exchanger according to claim 1, it is characterized in that: described high-temperature fuel gas import and high-temperature fuel gas outlet are the through hole of first and last heat exchange unit, and described liquid outlet and liquid inlet are separately positioned on first with on the housing of last heat exchange unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510912587.8A CN105509514A (en) | 2015-12-11 | 2015-12-11 | Fin tube type gas-liquid heat exchanger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510912587.8A CN105509514A (en) | 2015-12-11 | 2015-12-11 | Fin tube type gas-liquid heat exchanger |
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| Publication Number | Publication Date |
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| CN105509514A true CN105509514A (en) | 2016-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510912587.8A Pending CN105509514A (en) | 2015-12-11 | 2015-12-11 | Fin tube type gas-liquid heat exchanger |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307151A (en) * | 2018-11-12 | 2019-02-05 | 中国人民解放军海军工程大学 | A kind of high pressure gas cylinder fills gas cooling device |
| CN114060850A (en) * | 2021-10-18 | 2022-02-18 | 北京航空航天大学 | Ultra-high temperature air fuel heat exchanger with independent cooling interlayer |
Citations (6)
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| CN101896787A (en) * | 2007-12-12 | 2010-11-24 | Gea机械冷却技术有限公司 | Exhaust gas recirculation cooling element for an internal combustion engine |
| CN201935600U (en) * | 2010-12-13 | 2011-08-17 | 苏州工业园区久禾工业炉有限公司 | Heat exchanger and heat treatment heating system |
| CN103307910A (en) * | 2013-06-24 | 2013-09-18 | 华北电力大学 | Anti-corrosion and dirt-resistant efficient flue gas waste heat recovery device |
| CN203464803U (en) * | 2013-06-24 | 2014-03-05 | 华北电力大学 | Anti-corrosion anti-scale high-efficiency flue gas waste heat recovery device |
| JP2014202379A (en) * | 2013-04-01 | 2014-10-27 | トヨタ自動車株式会社 | Heat exchanger |
| CN205279810U (en) * | 2015-12-11 | 2016-06-01 | 江苏海事职业技术学院 | Pipe wing formula solution -air heat exchanger |
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2015
- 2015-12-11 CN CN201510912587.8A patent/CN105509514A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101896787A (en) * | 2007-12-12 | 2010-11-24 | Gea机械冷却技术有限公司 | Exhaust gas recirculation cooling element for an internal combustion engine |
| CN201935600U (en) * | 2010-12-13 | 2011-08-17 | 苏州工业园区久禾工业炉有限公司 | Heat exchanger and heat treatment heating system |
| JP2014202379A (en) * | 2013-04-01 | 2014-10-27 | トヨタ自動車株式会社 | Heat exchanger |
| CN103307910A (en) * | 2013-06-24 | 2013-09-18 | 华北电力大学 | Anti-corrosion and dirt-resistant efficient flue gas waste heat recovery device |
| CN203464803U (en) * | 2013-06-24 | 2014-03-05 | 华北电力大学 | Anti-corrosion anti-scale high-efficiency flue gas waste heat recovery device |
| CN205279810U (en) * | 2015-12-11 | 2016-06-01 | 江苏海事职业技术学院 | Pipe wing formula solution -air heat exchanger |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307151A (en) * | 2018-11-12 | 2019-02-05 | 中国人民解放军海军工程大学 | A kind of high pressure gas cylinder fills gas cooling device |
| CN109307151B (en) * | 2018-11-12 | 2023-11-07 | 中国人民解放军海军工程大学 | High-pressure gas cylinder filling gas cooling device |
| CN114060850A (en) * | 2021-10-18 | 2022-02-18 | 北京航空航天大学 | Ultra-high temperature air fuel heat exchanger with independent cooling interlayer |
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Application publication date: 20160420 |
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