CN106184742A - A kind of supersonic vehicle air intake duct microchannel cooling system - Google Patents
A kind of supersonic vehicle air intake duct microchannel cooling system Download PDFInfo
- Publication number
- CN106184742A CN106184742A CN201610827620.1A CN201610827620A CN106184742A CN 106184742 A CN106184742 A CN 106184742A CN 201610827620 A CN201610827620 A CN 201610827620A CN 106184742 A CN106184742 A CN 106184742A
- Authority
- CN
- China
- Prior art keywords
- sprue
- import
- wall
- microchannel
- intake duct
- 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
- 238000001816 cooling Methods 0.000 title claims abstract description 28
- 230000008676 import Effects 0.000 claims abstract description 40
- 239000002826 coolant Substances 0.000 claims abstract description 24
- 238000002485 combustion reaction Methods 0.000 claims abstract description 9
- 239000003350 kerosene Substances 0.000 claims description 16
- 239000007788 liquid Substances 0.000 claims description 5
- 208000015943 Coeliac disease Diseases 0.000 description 42
- 239000000463 material Substances 0.000 description 8
- 238000000889 atomisation Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 239000002828 fuel tank Substances 0.000 description 4
- 238000004806 packaging method and process Methods 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000002679 ablation Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000010742 number 1 fuel oil Substances 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
Abstract
A kind of supersonic vehicle air intake duct microchannel cooling system.If main flow import, annular entrance sprue, import sprue, microchannel, outlet sprue, ring exit sprue and main flow outlet；Main flow import is positioned at above electromotor distance piece, coolant enters annular entrance sprue from main flow import, annular entrance sprue is positioned at outside electromotor distance piece, coolant is divided into three strands at annular entrance sprue, respectively enter and be under air intake duct, left, import sprue above right wall, coolant enters the microchannel respective wall from the import sprue being in above different wall, microchannel is in air intake duct wall, wall and air are cooled down, enter back into combustor, coolant absorbs heat in microchannel, each enter the outlet sprue above different wall, import and be in the ring exit sprue above distance piece, flow out from main flow outlet again, coolant exits into combustor and air mixed combustion from main flow outlet, eject from jet pipe.
Description
Technical field
The present invention relates to supersonic vehicle, especially relate to be suitable for High Mach number and a kind of Supersonic of long-time navigation
Speed aircraft air intake duct microchannel cooling system.
Background technology
Hypersonic aircraft technology is the new commanding elevation of 21 century aeronautical and space technology, and being that in aviation history, secondary is bright flies
3rd epoch-making milestone after machine, breakthrough baffle flight, but there is also many technical barriers at present.When aircraft with
When High Mach number and aloft flying for long time, in air intake duct, gas speed of incoming flow is up to more than 5 Mach, the stagnation now flowed
Temperature is up to more than 1500K, and due to the viscous effect of gas, at air intake duct wall, flow velocity is zero, i.e. now close to entering
The temperature of air flue wall air-flow can reach stagnation temperature.For flight during long boat, now air intake duct wall thermic load will be very big,
The most even can burn air intake duct wall, the most too high engine temperature can reduce the reliability of each parts,
Thus cause the performance of electromotor drastically to deteriorate.Therefore it is required that air intake duct is had a kind of compact structure, the thermal protection system that performance is good
System, is effectively reduced the temperature of engine inlets and improves each component working condition, it is ensured that the workability of engine stabilizer
Can, thus flight when realizing the High Mach number of aero-engine and long boat.
The hypersonic aircraft thermal protection that tradition often uses is passive heat guard system, mainly by self structure material
The thermal capacitance of material absorbs heat, and then dispersion heat；Or be the painting using and covering high radiant rate on exotic material surface
Layer, distributes substantial amounts of heat energy to surrounding in the form of radiation.But High Mach number, for a long time flight are persistently produced
Heat, the simple thermal capacitance by self structure material absorbs, and electromotor entirety can be made to be brought rapidly up, and reduces the reliable of parts
Property, even cause air intake duct wall ablation.And for the type of cooling of coating, there are one and can bear total heat quantitative limitation
Value, be air intake duct cannot be carried out high efficiency, long cooling protection (Shi Liping, He Xiaodong. reusable launch vehicle
Thermal protection system general introduction [J]. aero-manufacturing technology, 2004 (07): 80-82.).
Summary of the invention
It is an object of the invention to provide and can reduce air intake duct wall surface temperature, when reducing High Mach number, long boat, condition issues
A kind of supersonic vehicle air intake duct microchannel cooling system of the thermic load of motivation material.
The present invention is provided with main flow import, annular entrance sprue, import sprue, microchannel, outlet sprue, annular go out
Mouth sprue and main flow outlet；
Main flow import is positioned at above electromotor distance piece, and the aerial kerosene of cold conditions enters ring as coolant from main flow import
Shape import sprue, annular entrance sprue is positioned at outside electromotor distance piece, and coolant is divided at annular entrance sprue
Three strands, respectively enteing the import sprue being in above air intake duct lower wall surface, left wall face, right wall, coolant is from being in difference
Import sprue above wall enters the microchannel on respective wall, and microchannel is in air intake duct wall, to wall and sky
Gas quickly cools down, and the air after cooling enters back into combustor, and coolant absorbs heat in microchannel, each enters different wall
Outlet sprue above face, imports and is in the ring exit sprue above distance piece, and then flows out from main flow outlet, preheating
After coolant flow out from main flow outlet, enter combustor, and air mixed combustion, then spouting from jet pipe.
Described annular entrance sprue and ring exit sprue use has identical profile with distance piece cross section, makes whole
The cooling system volume more compact of individual microchannel.
Described import sprue and outlet sprue, near wall, reduce the spatial volume of whole cooling system.
The circular pipe of described wall microchannel cross section, simple in construction, it is easy to processing, there is higher heat convection effect
Rate.
When aircraft is with High Mach number flight, ultrasonic compressed air enters electromotor, at air intake duct near wall
Air-flow has the highest stagnation temperature；High-speed air rubs consumingly with air intake duct wall simultaneously, produces substantial amounts of heat, make into
Air flue wall and compressed air steep temperature rise.Too high temperature can reduce the reliability of each parts of electromotor, make electromotor without
Method has normal working performance.Now in microchannel cooling system the microchannel on air intake duct wall due to fluid boundary layer thickness
Little, conduction of heat and diffusion mass transfer resistance are little, and the most a large amount of microchannels are integrated on wall, thus have efficient heat and mass effect
Rate.Wall and the compressed air of high temperature will quickly be cooled down by the microchannel being thus in air intake duct wall, reduce wall
Stagnation temperature, under the conditions of minimizing High Mach number, the thermic load of material, makes wall be in suitable operating temperature.Cold in microchannel
But liquid uses from the cold conditions aerial kerosene in fuel tank, utilizes cold conditions kerosene that air intake duct wall is carried out heat convection, coal
Oil injects combustor through ejector filler after being heated.Kerosene after preheating can improve atomization, promotes burning, and in this process
In, make the heat spread out of by wall be returned to combustor, improve the thermal efficiency of cycle of entirety.
The present invention can reduce the temperature of air intake duct wall, when reducing High Mach number, long boat under the conditions of the heat of engine material
Load；Coolant in microchannel uses the cold conditions aerial kerosene from fuel tank, after microchannel preheats, enters burning
Room, promotes fuel oil initial temperature, improves atomization, increases aero-engine thrust-weight ratio；The most integrated microchannel has
The feature that heat convection ability is strong, can significantly improve heat and mass efficiency；In shape, MCA is simple, and volume is little
Ingeniously, with air intake duct wall integrative packaging, make air intake duct overall structure the compactest；This is that one can be long-time, and high efficiency is followed
The air intake duct thermal protection system that ring utilizes.
The present invention, compared with traditional thermal protection system, has the advantage that
(1) microchannel cooling system be a kind of can heat convection, the thermal protection system that recycles for a long time, it is adaptable to high
Mach number, flight during long boat.In microchannel, fluid boundary layer thickness is little, and diffusional resistance is little, the most integrated microchannel tool
There is high efficiency heat convection ability, the temperature of air intake duct wall can be reduced quickly and efficiently.
(2) micro-channel inner-cooling but liquid selects the aerial kerosene of cold conditions, and this mode can take away air intake duct wall and compression
The heat of air, makes engine stabilizer normally work, and can preheat aerial kerosene again, improves atomization, promotes burning, reduces
Fuel oil consumes, and makes the heat of air intake duct return to combustor again simultaneously, and improve electromotor follows the bad thermal efficiency.
(3) microchannel and wall integrative packaging, use circular channel cross section, simple in construction, it is easy to processing；Annular enters,
Outlet sprue uses the profile similar with distance piece, and import and export sprue, near wall, reduces the space body of micro channel systems
Long-pending, allow whole cooling system be combined with air intake duct the compactest small and exquisite.
Accompanying drawing explanation
Fig. 1 is the aircraft inlet location schematic diagram of the present invention.
Fig. 2 is the structure composition schematic diagram of the embodiment of the present invention.
Fig. 3 is the structure composition upward view of the embodiment of the present invention.
Fig. 4 is the horizontal cross of the embodiment of the present invention.
Fig. 5 is the vertical sectional view of the embodiment of the present invention.
Detailed description of the invention
As shown in Fig. 1～5, the embodiment of the present invention is provided with main flow import 101, annular entrance sprue 102, import sprue
103, microchannel 104, outlet sprue 105, ring exit sprue 106 and main flow outlet 107；
Main flow import 101 is positioned at above electromotor distance piece, the aerial kerosene of cold conditions as coolant from main flow import 101
Entering annular entrance sprue 102, annular entrance sprue 102 is positioned at outside electromotor distance piece, and coolant is in annular entrance
Sprue is divided into three strands, respectively enters the import sprue 103 being in above air intake duct lower wall surface, left wall face, right wall, cold
But the microchannel 104 that liquid enters respective wall from the import sprue 103 being in above different wall, microchannel 104 is in
In air intake duct wall, quickly cooling down wall and air, the air after cooling enters back into combustor, and coolant is in microchannel
104 absorb heat, each enter the outlet sprue 105 above different wall, import and be in the ring exit above distance piece
Sprue 106, and then flow out from main flow outlet 107, the coolant after preheating flows out from main flow outlet 107, enters combustor, with
Air mixed combustion, then spouting from jet pipe.
Described annular entrance sprue and ring exit sprue use has identical profile with distance piece cross section, makes whole
The cooling system volume more compact of individual microchannel.
Described import sprue and outlet sprue, near wall, reduce the spatial volume of whole cooling system.
The circular pipe of described wall microchannel cross section, simple in construction, it is easy to processing, there is higher heat convection effect
Rate.
Hypersonic aircraft electromotor is mainly made up of air intake duct 1, distance piece 2, combustor 3 and jet pipe 4.The present invention
It it is the microchannel cooling system about hypersonic aircraft engine inlets 1.
Microchannel 104 in the right wall of described air intake duct 110, and it is in wall upper inlet sprue 103 and outlet
Sprue 105, near wall, reduces the volumetric spaces of microchannel cooling system.
Described microchannel 104 uses circular cross-section passage, embeds wall, with wall integrative packaging, makes overall structure more
For compact.
In Fig. 1～4, arrow represents to come flow path direction.
The combination that the present invention cools down based on air intake duct wall and microchannel, both can be embodied as boat when High Mach number, long boat
Empty engine inlets carry out for a long time, cool down expeditiously, overcome the engine inlets cannot be long-time, high efficiency
Thermal protection problem, can preheat the aerial kerosene of cold conditions again, promotes burning, reduces oil consumption, improves the thermal efficiency.
The present invention by tradition hypersonic aircraft air intake duct is transformed, the most integrated microchannel, and enter
Air flue wall integrative packaging, compact structure is compact, and heat convection ability is strong, air intake duct when can reduce rapidly High Mach number flight
Temperature, aircraft air intake duct wall is carried out cooling protection.The cold conditions aerial kerosene conduct stored in using aircraft fuel tank
Coolant in microchannel, the method can not only be taken away the heat of air intake duct, can preheat for aerial kerosene again, can actively improve coal
Oil atomization in combustor and efficiency of combustion.The present invention can realize the aero-engine of flight when High Mach number, long boat
Air intake duct cools down for a long time, reduces the thermic load of material, overcomes the wall ablation etc. that air intake duct stagnation temperature height causes
Shortcoming；Use cold conditions aerial kerosene as coolant, reinject combustor, promote fuel oil initial temperature, promote atomization, improve combustion
Burn efficiency and engine thrust-weight ratio.
The present invention is designed with three import sprues and three outlet sprues press close to wall, by substantial amounts of inlet microchannel
It is connected to three import sprues, and microchannel outlet is connected to three outlet sprues；It is designed with annular import and export main flow
Road, its pipeline is similar with distance piece profile, presses close to wall, reduces volumetric spaces, three import sprues is connected to annular and enters
Mouthful sprue and three outlet sprues are connected to ring exit sprue, so annular import and export respectively set a main flow enter,
Outlet.Thus substantial amounts of wall microchannel is assembled an import, the cooling system of an outlet.The coolant used is cold
The aerial kerosene of state, coolant flows through wall microchannel, rear flowing in combustion chamber, carries out mixed combustion with air.Use this cold
But liquid can take away the amount of heat of air intake duct wall and air, reduces wall stagnation temperature, can carry out pre-to aerial kerosene again
Heat, improves fuel atomization and efficiency of combustion.Coolant owing to using is the aerial kerosene from fuel tank, the most this cooling system
Air intake duct can be cooled down by system for a long time, is particularly suitable for aircraft when High Mach number, long boat.
Claims (3)
1. a supersonic vehicle air intake duct microchannel cooling system, it is characterised in that be provided with main flow import, annular entrance master
Runner, import sprue, microchannel, outlet sprue, ring exit sprue and main flow outlet；
Main flow import is positioned at above electromotor distance piece, and the aerial kerosene of cold conditions enters annular as coolant from main flow import and enters
Mouth sprue, annular entrance sprue is positioned at outside electromotor distance piece, and coolant is divided into three strands at annular entrance sprue,
Respectively enteing the import sprue being in above air intake duct lower wall surface, left wall face, right wall, coolant is from being in different wall
The import sprue of side enters the microchannel on respective wall, and microchannel is in air intake duct wall, carries out wall and air
Quickly cooling, the air after cooling enters back into combustor, and coolant absorbs heat in microchannel, each enters above different wall
Outlet sprue, import and be in the ring exit sprue above distance piece, and then flow out from main flow outlet, cold after preheating
But liquid flows out from main flow outlet, enters combustor, and air mixed combustion is then spouting from jet pipe.
2. a kind of supersonic vehicle air intake duct microchannel cooling system, it is characterised in that described annular
Import sprue and ring exit sprue use has identical profile with distance piece cross section.
3. a kind of supersonic vehicle air intake duct microchannel cooling system, it is characterised in that described import
Sprue and outlet sprue are near wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610827620.1A CN106184742A (en) | 2016-09-18 | 2016-09-18 | A kind of supersonic vehicle air intake duct microchannel cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610827620.1A CN106184742A (en) | 2016-09-18 | 2016-09-18 | A kind of supersonic vehicle air intake duct microchannel cooling system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106184742A true CN106184742A (en) | 2016-12-07 |
Family
ID=58067817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610827620.1A Pending CN106184742A (en) | 2016-09-18 | 2016-09-18 | A kind of supersonic vehicle air intake duct microchannel cooling system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106184742A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112984556A (en) * | 2021-03-02 | 2021-06-18 | 北京航空航天大学 | Liquid oxygen gas fuel gas generator |
| CN114750965A (en) * | 2022-06-15 | 2022-07-15 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Cooling device based on bionic veins |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030182928A1 (en) * | 2002-03-28 | 2003-10-02 | Sillence Mark A. | Scram jet engine design |
| US20040134195A1 (en) * | 2002-03-04 | 2004-07-15 | Marc Bouchez | Ramjet engine combustion chamber and ramjet engine equipped with same |
| US20070018038A1 (en) * | 2005-07-19 | 2007-01-25 | United Technologies Corporation | Engine heat exchanger with thermoelectric generation |
| US20100242486A1 (en) * | 2009-03-25 | 2010-09-30 | United Technologies Corporation | Fuel-cooled heat exchanger with thermoelectric device compression |
| US20120168121A1 (en) * | 2007-10-25 | 2012-07-05 | Jarmon David C | Internal pocket fastener system for ceramic matrix composite heat exchanger |
| US20150315971A1 (en) * | 2013-10-21 | 2015-11-05 | Government Of The United States As Represented By The Secretary Of The Air Force | High-speed vehicle power and thermal management system and methods of use therefor |
-
2016
- 2016-09-18 CN CN201610827620.1A patent/CN106184742A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040134195A1 (en) * | 2002-03-04 | 2004-07-15 | Marc Bouchez | Ramjet engine combustion chamber and ramjet engine equipped with same |
| US20030182928A1 (en) * | 2002-03-28 | 2003-10-02 | Sillence Mark A. | Scram jet engine design |
| US20070018038A1 (en) * | 2005-07-19 | 2007-01-25 | United Technologies Corporation | Engine heat exchanger with thermoelectric generation |
| US20120168121A1 (en) * | 2007-10-25 | 2012-07-05 | Jarmon David C | Internal pocket fastener system for ceramic matrix composite heat exchanger |
| US20100242486A1 (en) * | 2009-03-25 | 2010-09-30 | United Technologies Corporation | Fuel-cooled heat exchanger with thermoelectric device compression |
| US20150315971A1 (en) * | 2013-10-21 | 2015-11-05 | Government Of The United States As Represented By The Secretary Of The Air Force | High-speed vehicle power and thermal management system and methods of use therefor |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112984556A (en) * | 2021-03-02 | 2021-06-18 | 北京航空航天大学 | Liquid oxygen gas fuel gas generator |
| CN114750965A (en) * | 2022-06-15 | 2022-07-15 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Cooling device based on bionic veins |
| CN114750965B (en) * | 2022-06-15 | 2022-09-13 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Cooling device based on bionic veins |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106959034B (en) | Heat exchanger for embedded engine applications | |
| CN106958485B (en) | Heat exchanger for embedded engine applications: curve plate | |
| CN105156227B (en) | Pre-cooling air-breathing type variable cycle engine | |
| US9494050B2 (en) | Concentric nozzles for enhanced mixing of fluids | |
| CN103192978B (en) | Laminate type sweating and reverse-jetting combined cooling nose cone | |
| CN105973052A (en) | Tube in cross-flow conduit heat exchanger | |
| CN103672966B (en) | Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling | |
| CN103615741B (en) | Heat protection method for injection support plate of scramjet engine by utilizing sweat and impingement cooling | |
| CN206398760U (en) | A kind of microchannel cooling device for rotating detonation engine | |
| US9623723B2 (en) | System for heating the cabin of an aircraft provided with an annular heat exchanger around the exhaust nozzle | |
| CN106247407A (en) | A kind of fuel support plate ejector filler | |
| CN109812352A (en) | Rocket ejector and its thermal protection structure and thermal protection method | |
| CN106184742A (en) | A kind of supersonic vehicle air intake duct microchannel cooling system | |
| CN109944645A (en) | A kind of flow-disturbing rod structure for turbo blade enhanced heat exchange | |
| CN107891970A (en) | The active thermal protection system of hypersonic aircraft gaseous film control | |
| CN114776470A (en) | Corrugated turbulent flow plane cooling device and application | |
| CN108100273B (en) | Aircraft fuel cooling system | |
| Lee | Mixing augmentation with cooled pylon injection in a scramjet combustor | |
| CN113217949A (en) | Combustion chamber diverging and cooling structure and ramjet combustion chamber | |
| CN209990561U (en) | Thermal protection structure of TRRE ejection rocket and ejection rocket thereof | |
| CN108488833A (en) | A kind of fuel support plate ejector filler of novel improved | |
| CN113123899B (en) | Central injection rocket, RBCC engine and fuel injection method thereof | |
| CN106768794B (en) | A kind of long-time high-temperature tunnel experimental cabin | |
| CN205279810U (en) | Pipe wing formula solution -air heat exchanger | |
| CN220701338U (en) | Thermal protection component |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161207 |