CN102295072A - Single-layer air-liquid aircraft skin heat exchange method - Google Patents
Single-layer air-liquid aircraft skin heat exchange method Download PDFInfo
- Publication number
- CN102295072A CN102295072A CN2011101139925A CN201110113992A CN102295072A CN 102295072 A CN102295072 A CN 102295072A CN 2011101139925 A CN2011101139925 A CN 2011101139925A CN 201110113992 A CN201110113992 A CN 201110113992A CN 102295072 A CN102295072 A CN 102295072A
- Authority
- CN
- China
- Prior art keywords
- air
- liquid
- aircraft
- exch
- liquid covering
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention provides a single-layer air-liquid aircraft skin heat exchange method, belonging to the technical field of environmental control. The method is a new technology beneficial to reduction of the ram air amount of the aircraft and improvement of the air-liquid heat exchange efficiency and is used for improving the air-liquid heat exchange methods. The method is characterized in that a single-layer air-liquid skin heat exchanger is installed on the outer surface of the fuselage skin and comprises an outer surface (1), an inner surface (2), a liquid inlet (3), a liquid outlet (4), seal ends (5), (6) and fuselage connecting portions (8); and single-layer radiating fins (7) are installed between the outer surface (1) and the inner surface (2). The method has the following beneficial effects: compared with the air-air skin heat exchangers, the single-layer air-liquid skin heat exchanger has the advantages of higher heat exchange coefficient, higher heat exchange amount and better refrigeration effect; compared with the air-liquid heat exchangers, the air-liquid skin heat exchanger utilizes the boundary layer radiating technology fused with the aircraft skin into one, thus omitting the traditional inlet ram air cooling method, greatly reducing the aircraft fuel penalties caused by the system and improving the aircraft endurance; and meanwhile, the aircraft stealth performance requirement can be met.
Description
Technical field
The invention belongs to the environment controlling technique field, is the improvement to 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 individual layer air-liquid covering heat change method, it is characterized in that, at the fuselage outside face individual layer air-liquid covering H Exch is installed, this air-liquid covering H Exch comprises outside face, inside face, inlet, liquid outlet, the sealing termination, and with the fuselage connecting bridge, the individual layer radiating fin is installed between outside face and inside face.
Described air-liquid covering H Exch is attached at the fuselage skin outside face, and the fuselage skin outside face is with air-employing of liquid covering H Exch is spirally connected or the airtight mode of being spirally connected is connected.
Described fuselage outside face is removed local covering, embeds air-liquid covering H Exch, and the fuselage outside face is with air-employing of liquid covering H Exch is spirally connected or the airtight mode of being spirally connected is connected.
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: individual layer air-liquid covering H Exch scheme of installation
Fig. 2: individual layer 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-individual layer radiating fin
8-fuselage butt flange
9-aircraft exterior skin
The distribution header of 10-feed liquor
11-feed liquor dispensing branch
12-fluid arm
13-fluid collecting tube
14-individual layer 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 individual layer air-liquid covering H Exch that is attached at the aircraft skin outside face, covering H Exch inside is hot fluid (No. 65 refrigerant fluids), the outside utilizes the relative velocity of aircraft and ambient air that hot fluid is cooled, cancel traditional ram air duct cooling air mode, (internal flow be hot liquid) has higher exchange capability of heat and refrigeration than air-air covering H Exch (internal flow be hot air) because air-liquid covering H Exch, so this invention can make the compensatory loss of fuel oil of aircraft reduce to minimum.
Workflow: the hot fluid (No. 65 refrigerant fluids) that comes out from electronic machine enters " feed liquor distribution header 10 " through " feed liquor conduit 3 ", enter separate " single layer of liquid covering H Exch 14 " by " feed liquor dispensing branch 11 " again, the ram air in the hot fluid in the liquid covering H Exch and the external world carries out interchange of heat and cools, enter " fluid collecting tube 13 " through " fluid arm 12 " then,, " going out fluid catheter 4 " enter electronic machine after flowing out, and electronic machine 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 " individual layer air-liquid covering H Exch ", under identical initial conditions, the required covering heat interchanging area of system is 2.72m2, supposes that the aircraft diameter is 2m, and this moment, required covering area was equivalent to the ring of 1 433mm.
Claims (5)
1. aircraft individual layer air-liquid covering heat change method, it is characterized in that, at the fuselage outside face individual layer 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), and with fuselage connecting bridge (8), installation individual layer radiating fin (7) between outside face (1) and inside face (2).
2. aircraft individual layer air according to claim 1-liquid covering heat change method, it is characterized in that, described air-liquid covering H Exch is attached at the fuselage skin outside face, and the fuselage skin outside face is with air-employing of liquid covering H Exch is spirally connected or the airtight mode of being spirally connected is connected.
3. aircraft individual layer air according to claim 1-liquid covering heat change method, it is characterized in that, described fuselage outside face is removed local covering, embeds air-liquid covering H Exch, and the fuselage outside face is with air-employing of liquid covering H Exch is spirally connected or the airtight mode of being spirally connected is connected.
4. aircraft individual layer 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 individual layer air according to claim 1-liquid covering heat change method is characterized in that, described outside face (2) is processed to form shallow table rib line by special process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101139925A CN102295072A (en) | 2011-05-04 | 2011-05-04 | Single-layer air-liquid aircraft skin heat exchange method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101139925A CN102295072A (en) | 2011-05-04 | 2011-05-04 | Single-layer air-liquid aircraft skin heat exchange method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102295072A true CN102295072A (en) | 2011-12-28 |
Family
ID=45355807
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011101139925A Pending CN102295072A (en) | 2011-05-04 | 2011-05-04 | Single-layer air-liquid aircraft skin heat exchange method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102295072A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102914111A (en) * | 2012-10-24 | 2013-02-06 | 中国航空工业集团公司北京航空材料研究院 | Aircraft surface skin cooling device |
| 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 |
| CN112158326A (en) * | 2020-09-11 | 2021-01-01 | 中国航空工业集团公司成都飞机设计研究所 | Ventral fin type radiator suitable for aircraft |
| CN113955123A (en) * | 2021-12-09 | 2022-01-21 | 中国商用飞机有限责任公司 | Aircraft dehumidification system |
| CN114828570A (en) * | 2022-04-22 | 2022-07-29 | 中国电子科技集团公司第二十九研究所 | Small-size covering heat exchanger and heat exchange system |
Citations (5)
| 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 |
| 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 | Compensator of fully-closed 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 |
| CN102143887A (en) * | 2008-07-31 | 2011-08-03 | 空中客车营运有限公司 | Heat exchanger for the outer skin of an aircraft |
-
2011
- 2011-05-04 CN CN2011101139925A patent/CN102295072A/en active Pending
Patent Citations (5)
| 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 |
| CN102143887A (en) * | 2008-07-31 | 2011-08-03 | 空中客车营运有限公司 | Heat exchanger for the outer skin of 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 | Compensator of fully-closed liquid circulation system |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102914111A (en) * | 2012-10-24 | 2013-02-06 | 中国航空工业集团公司北京航空材料研究院 | Aircraft surface skin cooling device |
| CN102914111B (en) * | 2012-10-24 | 2014-11-26 | 中国航空工业集团公司北京航空材料研究院 | Aircraft surface skin cooling device |
| 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 |
| CN112158326A (en) * | 2020-09-11 | 2021-01-01 | 中国航空工业集团公司成都飞机设计研究所 | Ventral fin type radiator suitable for aircraft |
| CN112158326B (en) * | 2020-09-11 | 2023-03-14 | 中国航空工业集团公司成都飞机设计研究所 | Ventral fin type radiator suitable for aircraft |
| CN113955123A (en) * | 2021-12-09 | 2022-01-21 | 中国商用飞机有限责任公司 | Aircraft dehumidification system |
| CN114828570A (en) * | 2022-04-22 | 2022-07-29 | 中国电子科技集团公司第二十九研究所 | Small-size covering heat exchanger and heat exchange system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102295070A (en) | Double-layer air-liquid aircraft skin heat exchange method | |
| CN102295072A (en) | Single-layer air-liquid aircraft skin heat exchange method | |
| US8857767B2 (en) | De-icing system for an aircraft | |
| CN103362650B (en) | The cooling system of aeroengine and method thereof | |
| CN102381479B (en) | Comprehensive environmental control/liquid cold and heat energy management system for non-stamping air inlet duct | |
| US20160161189A1 (en) | Plate-fin tubular hybrid heat exchanger design for an air and fuel cooled air cooler | |
| CN110925096A (en) | Engine lubricating oil cooling system | |
| CN101590913A (en) | Adopt the anti-icing and deicing method for civil aircraft of loop circuit heat pipe | |
| WO2010136710A3 (en) | Fluid-cooling device for a turbine engine propulsive unit | |
| WO2023092962A1 (en) | Aircraft cockpit heating system | |
| CN103334820B (en) | Thermal control system and method of automobile engine | |
| CN102390538A (en) | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet | |
| CN103786886A (en) | Ice preventing and removing system for aircraft wing | |
| CN106882390A (en) | Airplane air entraining precooling heat regenerative system | |
| CN102390537A (en) | Comprehensive heat energy management system for environmental control system and liquid cooling system | |
| CN206122541U (en) | Oven | |
| CN205190000U (en) | Crankcase ventilation system | |
| CN105416591A (en) | Double-layer airplane skin heat exchanger | |
| CN105083569B (en) | Enhanced heat exchange device for aircraft fuel and enhanced heat exchange method thereof | |
| CN204923304U (en) | Cabin air cooling apparatus of chemical tanker | |
| CN202630748U (en) | Fuel oil-air radiator of airborne environment control system | |
| US20200317358A1 (en) | Aircraft nacelle comprising at least one heat exchanger | |
| CN203687470U (en) | Backheating condenser | |
| CN107956569A (en) | Engine cooling management system | |
| CN205808158U (en) | A kind of airborne refrigeration system heat exchanger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20111228 |