CN102295070A - Double-layer air-liquid aircraft skin heat exchange method - Google Patents
Double-layer air-liquid aircraft skin heat exchange method Download PDFInfo
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- CN102295070A CN102295070A CN2011101139944A CN201110113994A CN102295070A CN 102295070 A CN102295070 A CN 102295070A CN 2011101139944 A CN2011101139944 A CN 2011101139944A CN 201110113994 A CN201110113994 A CN 201110113994A CN 102295070 A CN102295070 A CN 102295070A
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Abstract
一种飞机双层空气-液体蒙皮热交换方法，属于环境控制技术领域，是减少飞机冲压空气量、提高空气-液体热交换效率的新技术，是对单层空气-液体蒙皮热交换方式的改进。在机身蒙皮外表面安装双层空气-液体蒙皮热交换器，该空气-液体蒙皮热交换器包括外表面(1)，内表面(2)，进液导管(3)，出液导管(4)，密封端头(5)、(6)，机身连接部分(10)，在内表面(2)与蒙皮外表面之间留有间隙(11)，外表面(1)与内表面(2)之间安装双层散热翅片，该双层散热翅片包括内层散热翅片(7)、外层散热翅片(8)和内外层散热翅片的隔板(9)。该方法与空气-空气蒙皮热交换器相比，其换热系数更高，换热量更大，制冷效果更好；与空-液热交换器相比，空气-液体蒙皮热交换器利用与飞机蒙皮融为一体的附面层散热技术，取消了传统的冲压进气道空气冷却方式，大大减小了系统对飞机的燃油代偿损失，提高了飞机航时；同时可满足飞机隐身性能要求。
The invention relates to an aircraft double-layer air-liquid skin heat exchange method, which belongs to the field of environmental control technology, and is a new technology for reducing the amount of aircraft ram air and improving the air-liquid heat exchange efficiency. improvement of. A double-layer air-liquid skin heat exchanger is installed on the outer surface of the fuselage skin, and the air-liquid skin heat exchanger includes an outer surface (1), an inner surface (2), a liquid inlet conduit (3), and a liquid outlet Conduit (4), sealing end (5), (6), fuselage connecting part (10), leave gap (11) between inner surface (2) and skin outer surface, outer surface (1) and Double-layer heat dissipation fins are installed between the inner surfaces (2), and the double-layer heat dissipation fins include inner heat dissipation fins (7), outer heat dissipation fins (8) and partitions (9) for inner and outer heat dissipation fins . Compared with the air-air skin heat exchanger, this method has higher heat transfer coefficient, larger heat transfer, and better cooling effect; compared with the air-liquid heat exchanger, the air-liquid skin heat exchanger Utilizing the boundary layer heat dissipation technology integrated with the aircraft skin, the traditional ram intake air cooling method is cancelled, which greatly reduces the system’s fuel compensation loss to the aircraft and improves the flight time of the aircraft; at the same time, it can meet the requirements of the aircraft. Stealth performance requirements.
Description
Technical field
The invention belongs to the environment controlling technique field, particularly to the improvement of aircraft air-liquid heat-exchange mode.
Background technology
At present there are following two kinds with the approaching technology of this patent in state, the internal and external environment control system:
1) (abbreviation: sky-liquid heat exchanger)---adopt ram air duct, utilize ram air that the hot fluid from electronic machine is cooled, state, inside and outside most aircrafts adopt this form to air-liquid heat exchanger at present.
Advantage: sky-liquid heat exchanger and ram air duct simplicity of design are easy to coordinate to install aboard.
Shortcoming: sky-liquid heat exchanger volume more greatly, highly higher (usually greater than 100mm), ram air duct and ram air produce bigger aerodynamic drag to aircraft, the air in the ram air duct has the compensatory loss of bigger fuel oil to aircraft.
2) air-air covering H Exch (be called for short: air covering H Exch)---when flowing in the interlayer of hot air between aircraft exterior skin and airframe structure, utilize the relative velocity of aircraft and ambient air that hot air is cooled, at present existing aircraft adopts this mode, as A320, B767, C-17; And the approaching patent of this invention has: Airbus SAS 200780009653.4 " eduction gear, aircraft and the method that is used to make the fluid between the interior lining panel of the exterior skin that is present in aircraft to flow out ".
Advantage: air covering H Exch is positioned at the aircraft skin inside face, and is little to the aerodynamic drag of aircraft, the compensatory loss of fuel oil is less relatively; In addition, because air covering H Exch is installed on interior of aircraft, what flow in the H Exch is air, and therefore, air covering H Exch is less demanding to the air-tightness of self.
Shortcoming: exchange capability of heat, the refrigeration of air-air covering H Exch can not show a candle to air-liquid covering H Exch, and (be called for short: liquid covering H Exch), what flow in the liquid covering H Exch is liquid, as No. 65 refrigerant fluids etc.
Summary of the invention
The objective of the invention is: by technical solution of the present invention, reduce aircraft aerodynamic drag and the compensatory loss of fuel oil, prolong aircraft cruise duration, can satisfy the stealthy performance requriements of aircraft simultaneously.
Technical scheme of the present invention is:
A kind of aircraft double-deck air-liquid covering heat change method, it is characterized in that, at the fuselage skin outside face double-deck air-liquid covering H Exch is installed, this air-liquid covering H Exch comprises outside face, inside face, inlet, liquid outlet, the sealing termination, the fuselage connecting bridge, leave the gap between inside face and covering outside face, double-deck radiating fin is installed between outside face and the inside face, this bilayer radiating fin comprises the dividing plate of internal layer radiating fin, outer radiating fin and ectonexine radiating fin.
Described air-liquid covering H Exch is attached at the fuselage skin outside face, and employing is spirally connected or the airtight mode of being spirally connected connects.
The height in described gap is 5-10mm.
Described air-liquid covering H Exch material therefor is an aluminum alloy.
The invention has the beneficial effects as follows: this method is compared with air-air covering H Exch, and its coefficient of heat transfer is higher, and the heat exchange amount is bigger, and refrigeration is better; Air-liquid covering H Exch is compared with sky-liquid heat exchanger, the boundary-layer heat dissipation technology that air-liquid covering H Exch utilization and aircraft skin combine together, cancelled traditional ram air duct cooling air mode, reduced system greatly to the compensatory loss of the fuel oil of aircraft, when having improved the aircraft boat; Simultaneously can satisfy the stealthy performance requriements of aircraft.
With certain type machine is example, the electronic machine thermal load is 13kW, flight time is 4h, aircraft flies in cruising altitude, if with sky-liquid heat exchanger that air-replacement of liquid covering H Exch has ram air duct, when the ram air amount is 2160kg/h, can reduce the compensatory loss of aircraft fuel oil 307kg, prolong 10min (comprising that cancellation ram air duct drum makes the flight time that the aircraft aerodynamic drag reduces to be increased the cruise duration of prolongation) cruise duration.Above-mentioned sky-liquid heat exchanger oad is: totally 21 layers of length=170mm * 550mm * 120mm, fin, and wherein hot boundary layer number is 10 layers, cold boundary layer number is 11 layers.
Description of drawings
Fig. 1: double-deck air-liquid covering H Exch scheme of installation
Fig. 2: double-deck air-liquid covering heat converter structure scheme drawing
The 1-outside face
The 2-inside face
3-feed liquor conduit
4-goes out fluid catheter
5-radial seal termination
6-side seal termination
7-internal layer radiating fin
The outer radiating fin of 8-
The inside and outside layer of 9-heat-exchanger fin dividing plate
10-fuselage butt flange
The narrow passage of 11-between H Exch inside face and covering outside face
12-aircraft exterior skin
The distribution header of 13-feed liquor
14-feed liquor dispensing branch
15-fluid arm
16-fluid collecting tube
17-double-deck air-liquid covering H Exch
The specific embodiment
Below by the specific embodiment the present invention is described in further detail.
The boundary-layer heat dissipation technology that employing of the present invention and aircraft skin combine together, design a kind of double-deck air-liquid covering H Exch that is installed on the aircraft skin outside face, covering H Exch inside is hot fluid (No. 65 refrigerant fluids), and the H Exch outside face utilizes the relative velocity of aircraft and ambient air that outer hot fluid is cooled; In addition, H Exch inside face and aircraft skin outside face form the gap of 5～10mm, utilize the relative velocity of aircraft and ambient air that the internal layer hot fluid is cooled once more.
Workflow: the hot fluid (No. 65 refrigerant fluids) that comes out from electronic machine enters " feed liquor distribution header [13] " through " inlet [3] ", enter separate " double-deck air-liquid covering H Exch [17] " by " feed liquor dispensing branch [14] " again, hot fluid in the outer fin of air-liquid covering H Exch carries out interchange of heat with the extraneous ambient air that flows and cools, the ambient air that flows in hot fluid in air-liquid covering H Exch internal layer fin and the narrow passage carries out interchange of heat and cools, then, fluid in the skin converges again, and warp " fluid arm [15] " enters " fluid collecting tube [16] ", after " liquid outlet [4] " flow out into electronic machine, electronic machine is cooled off once more, to guarantee that electronic device works is in suitable range of temperatures.
With certain type machine is example, the electronic machine thermal load is 13kW, flight time is 4h, aircraft flies in cruising altitude, if with sky-liquid heat exchanger that air-replacement of liquid covering H Exch has ram air duct, when the ram air amount is 2160kg/h, can reduce the compensatory loss of aircraft fuel oil 307kg, prolong 10min (comprising that cancellation ram air duct drum makes the flight time that the aircraft aerodynamic drag reduces to be increased the cruise duration of prolongation) cruise duration.Above-mentioned sky-liquid heat exchanger oad is: length=170mm * 550mm * 120mm, and wherein hot boundary layer number is 10 layers, cold boundary layer number is 11 layers.
If adopt this programme technological invention " double-deck air-liquid covering H Exch ", under identical initial conditions, the required covering heat interchanging area of system is about 2m
2, suppose that the aircraft diameter is 2m, this moment, required covering area was equivalent to the ring of 1 318mm.
Claims (5)
1. aircraft double-deck air-liquid covering heat change method, it is characterized in that, at the fuselage skin outside face double-deck air-liquid covering H Exch is installed, this air-liquid covering H Exch comprises outside face (1), inside face (2), feed liquor conduit (3), go out fluid catheter (4), sealing termination (5), (6), fuselage connecting bridge (10), leave gap (11) between inside face (2) and covering outside face, double-deck radiating fin is installed between outside face (1) and the inside face (2), this bilayer radiating fin comprises internal layer radiating fin (7), the dividing plate (9) of outer radiating fin (8) and ectonexine radiating fin.
2. aircraft double-deck air according to claim 1-liquid covering heat change method is characterized in that, described air-liquid covering H Exch is attached at the fuselage skin outside face, and employing is spirally connected or the airtight mode of being spirally connected connects.
3. aircraft double-deck air according to claim 1-liquid covering heat change method is characterized in that the height of described gap (11) is 5-10mm.
4. aircraft double-deck air according to claim 1-liquid covering heat change method is characterized in that, described air-liquid covering H Exch material therefor is an aluminum alloy.
5. aircraft double-deck air according to claim 1-liquid covering heat change method is characterized in that, described inside face (1) and outside face (2) are processed to form shallow table rib line by special process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2011101139944A CN102295070A (en) | 2011-05-04 | 2011-05-04 | Double-layer air-liquid aircraft skin heat exchange method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011101139944A CN102295070A (en) | 2011-05-04 | 2011-05-04 | Double-layer air-liquid aircraft skin heat exchange method |
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| CN102295070A true CN102295070A (en) | 2011-12-28 |
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| CN2011101139944A Pending CN102295070A (en) | 2011-05-04 | 2011-05-04 | Double-layer air-liquid aircraft skin heat exchange method |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102548364A (en) * | 2012-01-09 | 2012-07-04 | 南京航空航天大学 | Dual-heat-sink device for cooling electronic equipment |
| CN105366028A (en) * | 2015-12-11 | 2016-03-02 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft skin heat exchanger |
| CN105416591A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安飞机设计研究所 | Double-layer airplane skin heat exchanger |
| CN105416563A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安飞机设计研究所 | Embedded skin heat exchanger for airplane |
| 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 |
| CN111878238A (en) * | 2020-07-23 | 2020-11-03 | 西北工业大学 | A double-layer cooling channel for reducing the temperature of aircraft components |
| CN113147808A (en) * | 2020-01-07 | 2021-07-23 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Double-deck withstand voltage vacuum pipeline train body structure in main cabin |
| CN113147809A (en) * | 2020-01-07 | 2021-07-23 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Vacuum pipeline train body structure with double-layer pressure-resistant passenger cabin |
| CN114435582A (en) * | 2022-01-10 | 2022-05-06 | 南京理工大学 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
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| CN101405181A (en) * | 2006-03-21 | 2009-04-08 | 空中客车德国有限公司 | Drainage device, aircraft, and method for letting out a fluid that is present between the exterior skin and the interior lining of an aircraft |
| CA2726558A1 (en) * | 2008-06-03 | 2009-12-10 | Airbus Operations Gmbh | System and method for cooling a device subjected to heat in a vehicle, particularly an aircraft |
| CN201407249Y (en) * | 2009-06-04 | 2010-02-17 | 中国航空工业集团公司西安飞机设计研究所 | A compensator for a fully enclosed liquid circulation system |
| DE102009013159A1 (en) * | 2009-03-16 | 2010-09-23 | Airbus Operations Gmbh | Radiator for aircraft cooling system, has matrix body including coolant channels extending from surface of matrix body to another surface of matrix body so that coolant flows through matrix body |
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2011
- 2011-05-04 CN CN2011101139944A patent/CN102295070A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101405181A (en) * | 2006-03-21 | 2009-04-08 | 空中客车德国有限公司 | Drainage device, aircraft, and method for letting out a fluid that is present between the exterior skin and the interior lining of an aircraft |
| CA2726558A1 (en) * | 2008-06-03 | 2009-12-10 | Airbus Operations Gmbh | System and method for cooling a device subjected to heat in a vehicle, particularly an aircraft |
| DE102009013159A1 (en) * | 2009-03-16 | 2010-09-23 | Airbus Operations Gmbh | Radiator for aircraft cooling system, has matrix body including coolant channels extending from surface of matrix body to another surface of matrix body so that coolant flows through matrix body |
| CN201407249Y (en) * | 2009-06-04 | 2010-02-17 | 中国航空工业集团公司西安飞机设计研究所 | A compensator for a fully enclosed liquid circulation system |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102548364A (en) * | 2012-01-09 | 2012-07-04 | 南京航空航天大学 | Dual-heat-sink device for cooling electronic equipment |
| CN102548364B (en) * | 2012-01-09 | 2014-08-13 | 南京航空航天大学 | Dual-heat-sink device for cooling electronic equipment |
| CN105366028A (en) * | 2015-12-11 | 2016-03-02 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft skin heat exchanger |
| CN105416591A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安飞机设计研究所 | Double-layer airplane skin heat exchanger |
| CN105416563A (en) * | 2015-12-11 | 2016-03-23 | 中国航空工业集团公司西安飞机设计研究所 | Embedded skin heat exchanger for airplane |
| 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 |
| CN113147808A (en) * | 2020-01-07 | 2021-07-23 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Double-deck withstand voltage vacuum pipeline train body structure in main cabin |
| CN113147809A (en) * | 2020-01-07 | 2021-07-23 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Vacuum pipeline train body structure with double-layer pressure-resistant passenger cabin |
| CN111878238A (en) * | 2020-07-23 | 2020-11-03 | 西北工业大学 | A double-layer cooling channel for reducing the temperature of aircraft components |
| CN114435582A (en) * | 2022-01-10 | 2022-05-06 | 南京理工大学 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
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Application publication date: 20111228 |