CN107091486B - A kind of after-burner annular flame barrel structure with cyclone - Google Patents
A kind of after-burner annular flame barrel structure with cyclone Download PDFInfo
- Publication number
- CN107091486B CN107091486B CN201710227204.2A CN201710227204A CN107091486B CN 107091486 B CN107091486 B CN 107091486B CN 201710227204 A CN201710227204 A CN 201710227204A CN 107091486 B CN107091486 B CN 107091486B
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- China
- Prior art keywords
- cyclone
- burner
- air inlet
- afterbunring
- tail bone
- 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.)
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- 210000000988 bone and bone Anatomy 0.000 claims abstract description 12
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 11
- 238000009792 diffusion process Methods 0.000 claims description 4
- 239000000295 fuel oil Substances 0.000 abstract description 11
- 230000003134 recirculating effect Effects 0.000 abstract description 4
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 13
- 239000007789 gas Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000010992 reflux Methods 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cyclones (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The present invention provides a kind of after-burner annular flame barrel structure with cyclone, the structure installs 6 cyclones additional in the middle part of after-burner, large-scale recirculating zone can be generated in after-burner, so as to reduce air velocity to the greatest extent, guarantee after-burner stablizes burning.Meanwhile it being provided with expansion air inlet section in reinforcing tail bone tail portion, and expansion air inlet is set at cyclone center, afterbunring After-market internal gas flow flowing velocity can be greatly reduced through a variety of ways, provide space to stablize burning.Air-flow can generate shear action to fuel oil after passing through cyclone, keep fuel-oil atmozation more thorough, so as to keep burning more abundant.After air-flow is by expansion air inlet section, fraction can be effectively reduced after-burner wall temperature by after-burner inside and outside wall intermediate channel, improve aircraft infrared stealth performance.
Description
Technical field
The invention belongs to after-burner fields, and in particular to one kind can effectively adjust air flow state, substantially mention
The after-burner annular flame barrel structure with cyclone of high combustion stability and efficiency of combustion.
Background technique
After-burner is the important component of modern Aviation gas turbine, is mainly pushed away on military aircraft for greater engine
Power enhances air maneuver and uses in short-term.Using after-burner, can be avoided makes because using the engine compared with high thrust
The front face area and quality of aircraft increase.
After-burner using the remaining oxygen in combustion gas spray into again fuel oil progress burning, by improve temperature and
Air-flow velocity improves motor power.Opening after-burner can make the maximum thrust of aircraft improve 50% or so, still, pole
High oil consumption rate makes after-burner can only the of short duration use in taking off, climbing or fighting.It is severe in after-burner
Burning situation also carry out very big difficulty to combustion zone.Wherein most important reason is that air velocity is excessive in after-burner, phase
Than the inlet air flow speed of main chamber, the intake velocity of after-burner can reach main chamber 2~3 times (350m/s~
450m/s).And how to light a fire in the air-flow of high speed, and stablize burning, it will determine the performance of an after-burner, into
And influence the performance of whole engine.
In main chamber, most combustion chamber reduces air velocity using cyclone, and the working principle of cyclone is: in gas
After stream passes through cyclone, flow rotation forward travel, and expand outward, outside air velocity increases, and has volume to central gas stream
Suction effect, so as to cause central pressure reduction；As air-flow moves backward, speed is gradually decreased, and central pressure gradually rises, from
And adverse pressure gradient, backflow are generated at burner inner liner center.Due to the generation of reflux, low speed is produced in a combustion chamber
Area, to provide condition for flame stabilization burning.
Cyclone is added in this programme in after-burner, effectively improves flame stabilization burning so as to generate recirculating zone
Region, meanwhile, cyclone can make fuel-oil atmozation more thorough, to guarantee the efficiency of combustion of after-burner.
Summary of the invention
The technical problem to be solved by the present invention is to one kind in after-burner can effectively adjust air flow state, substantially
Improve the annular flame barrel structure with cyclone of combustion stability and efficiency of combustion.Compared with prior art, the program exists
It installs 6 cyclones in the middle part of after-burner additional, large-scale recirculating zone can be generated, in after-burner so as to maximum
The reduction air velocity of degree, guarantee after-burner stablizes burning.Meanwhile cyclone structure is with respect to the bluff bodies flame such as v-shaped slot
Rock-steady structure can be effectively reduced the pressure loss.Vortex gas-flow can generate shear action to fuel oil, keep fuel-oil atmozation more thorough
Bottom, so as to keep burning more abundant.
Technical solution
The purpose of the present invention is to provide one kind can effectively adjust air flow state, greatly improve combustion stability with
The after-burner annular flame barrel structure with cyclone of efficiency of combustion.
The object of the present invention is achieved like this:
After-burner annular flame barrel structure uses one layer of rectification supporting plate in after-burner entry position, and supporting plate is high
Degree is the 1/3~1/2 of after-burner entrance height, and length is 35~40mm, with a thickness of 5~8mm, rectifies supporting plate blade profile head
Use radius for 1~3mm circular arc, blade uses radius for the circular arc of 1600~2000mm, and entire blade profile is using streamlined.Adding
The diffuser entrance of flaring is used in the middle part of power tail bone, expansion angle is 10 °~20 °, and drift angle should be less than the corresponding reinforcing in the position
The wall angle of tail bone.Reinforce tail bone tail portion be arranged ring baffle, ring baffle inner ring with reinforcing tail bone wall surface be connected, outer ring and
Afterbunring chamber interior walls are connected.
One layer of single-stage cyclone of setting on ring baffle, totally 6.Its distribution form is uniform in a ring around the baffle center of circle
Distribution.Swirler blades drift angle is 15 °~30 °, and flaring round entrance is arranged in cyclone center, and flaring angle is 5 °~10 °.Rotation
Flow 1/5~1/4 that device centre-height is after-burner channel height, the settable slightly above cyclone center of level-one blade height
Highly, cyclone total length is 20mm~50mm, can carry out appropriate adjustment according to after-burner size.Swirler blades blade profile
Using airflow design, wherein leaf head uses diameter for the circular arc of 1~1.5mm, blade use radius for 500~
The circular arc of 1000mm guarantees the airflow design of swirl vane.
Two layers of air inlet around center of circle arrangement is arranged in cyclone ring baffle, and hole is alternate with cyclone to be arranged, first layer
Air inlet is located at 4/5 radius of ring baffle, opening diameter be 15mm~20mm, totally 6.Second layer air inlet is located at annular gear
At 1/3 radius of plate, opening diameter be 20~25mm, totally 6.
Using the present invention it is desirable it is following the utility model has the advantages that
1. the present invention adds cyclone Combination Design to carry out flow slowing down using rectification supporting plate, large-scale reflux can be generated
Area, to guarantee that stablizing for after-burner internal flame is burnt.
2. using hydrocyclone structure, it can effectively change air flow state in after-burner, and can be effectively right
Fuel oil carries out shearing atomization, improves the fineness of fuel oil, so as to guarantee that fuel oil more fully burns.
3. inner wall is arranged in after-burner, effectively cooling, reduction after-burner can be carried out to after-burner wall surface
Infra-red radiation, so as to improve aircraft Stealth Fighter.
Detailed description of the invention
Fig. 1: after-burner cross-sectional view；
Fig. 2: cyclone layout viewing；
Fig. 3: cyclone schematic diagram；
Fig. 4: after-burner perspective view；
In figure: 1- afterbunring chamber inlet rectification supporting plate, 2- reinforcing tail bone, 3- cyclone, 4- center annular baffle, 5- add
Power outer wall of combustion chamber, 6- afterbunring chamber interior walls, 7- diffuser, 8- first layer air inlet, 9- cyclone center flaring air inlet,
10- second layer air inlet
Specific embodiment
Now in conjunction with attached drawing, the invention will be further described:
In conjunction with Fig. 1, Fig. 2, Fig. 3 and Fig. 4, the present invention provides a kind of changeable after-burner internal gas flows to flow shape
State increases after-burner recirculating zone size, improves fuel-oil atmozation fineness, improves the reinforcing combustion with cyclone of flame holding
Burn cell structure.Fig. 1 is after-burner overall diagram, and Fig. 2 is cyclone layout viewing, and Fig. 3 is cyclone schematic diagram, and Fig. 4 is reinforcing
Combustion chamber perspective view.
After air-flow enters after-burner, supporting plate 1 is rectified by entrance, air-flow is tentatively slowed down, and diffusion is then passed through
Section 7, air-flow further slows down, and later by cyclone 3, air-flow generates local eddy flow, generates reflux at after-burner rear portion
Area, while fuel oil is more uniform by the effect blending of eddy flow, so as to provide condition for the good burning of after-burner.
Meanwhile air-flow can enter after-burner by the first layer air inlet 8 and second layer air inlet 10 of center annular baffle 4, be
Burning provides sufficient air.Air-flow is divided into two strands, wherein most air-flow is passed through by central passage when by diffuser
Slow down and participate in burning, another fraction air-flow by the channel between after-burner inside and outside wall, can effective cooling wall, drop
Low after-burner infra-red radiation, so as to improve the Stealth Fighter of aircraft.
Claims (4)
1. a kind of afterbunring cell structure with cyclone, it is characterised in that: afterbunring chamber inlet is using one layer of rectification branch
Diffusion air inlet section is arranged in plate in the middle part of reinforcing tail bone, and ring baffle is arranged in reinforcing tail bone tail portion, and one layer of single-stage of setting is revolved on baffle
Device is flowed, totally 6, distribution form is to be uniformly distributed in a ring around the baffle center of circle, and cyclone centre-height is logical for after-burner
The 1/5~1/4 of road height, level-one blade height it is settable slightly above cyclone centre-height, cyclone total length be 20mm~
50mm, wherein swirler blades drift angle be 15 °~30 °, cyclone center be arranged flaring round entrance, flaring angle be 5 °~
10°。
2. a kind of afterbunring cell structure with cyclone according to claim 1, it is characterised in that: entry position is whole
Stream supporting plate length is 35~40mm, with a thickness of 5~8mm, rectifies supporting plate blade profile head and uses radius for 1~3mm circular arc, blade is adopted
The circular arc for being 1600~2000mm with radius, entire blade profile is using streamlined.
3. a kind of afterbunring cell structure with cyclone according to claim 1, it is characterised in that: in reinforcing tail bone
The diffusion air inlet section of portion's setting, wherein diffuser expansion angle is 10 °~20 °, and expansion angle should be less than corresponding to the position
The wall angle of tail bone is reinforced, to guarantee diffusion air inlet section for expansion entrance.
4. a kind of afterbunring cell structure with cyclone according to claim 1, it is characterised in that: after-burner
The ring baffle for reinforcing tail bone position is connected with afterbunring chamber interior walls and reinforcing tail bone wall surface, is arranged two layers in ring baffle
The air inlet arranged around the center of circle, every layer each 6, wherein first layer air inlet is located at 4/5 radius of ring baffle, and aperture is straight
Diameter is 15mm~20mm, and second layer air inlet is located at 1/3 radius of ring baffle, and opening diameter is 20~25mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710227204.2A CN107091486B (en) | 2017-04-10 | 2017-04-10 | A kind of after-burner annular flame barrel structure with cyclone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710227204.2A CN107091486B (en) | 2017-04-10 | 2017-04-10 | A kind of after-burner annular flame barrel structure with cyclone |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107091486A CN107091486A (en) | 2017-08-25 |
| CN107091486B true CN107091486B (en) | 2019-08-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710227204.2A Expired - Fee Related CN107091486B (en) | 2017-04-10 | 2017-04-10 | A kind of after-burner annular flame barrel structure with cyclone |
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| CN (1) | CN107091486B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10941939B2 (en) * | 2017-09-25 | 2021-03-09 | General Electric Company | Gas turbine assemblies and methods |
| CN108332233B (en) * | 2018-01-08 | 2020-04-21 | 南京航空航天大学 | Combustion chamber for adjusting combustion area based on inlet rotational flow rectification support plate and special support plate thereof |
| CN111780160B (en) * | 2020-08-21 | 2022-03-08 | 中国科学院工程热物理研究所 | Blunt body flame stabilizer with whirl stationary vortex structure |
| CN114719293B (en) * | 2022-03-24 | 2023-05-26 | 西北工业大学 | Annular cavity afterburner structure |
| CN115143489B (en) * | 2022-06-15 | 2023-08-11 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale rotational flow air intake |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN204438191U (en) * | 2014-12-19 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use |
| CN205065799U (en) * | 2015-08-03 | 2016-03-02 | 华中科技大学 | A flame holder for combustion chamber and combustion chamber thereof |
| CN105674332A (en) * | 2016-01-19 | 2016-06-15 | 西北工业大学 | Pre-evaporation type integrated afterburner |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9879862B2 (en) * | 2013-03-08 | 2018-01-30 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine afterburner |
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2017
- 2017-04-10 CN CN201710227204.2A patent/CN107091486B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN204438191U (en) * | 2014-12-19 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use |
| CN205065799U (en) * | 2015-08-03 | 2016-03-02 | 华中科技大学 | A flame holder for combustion chamber and combustion chamber thereof |
| CN105674332A (en) * | 2016-01-19 | 2016-06-15 | 西北工业大学 | Pre-evaporation type integrated afterburner |
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| Publication number | Publication date |
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| CN107091486A (en) | 2017-08-25 |
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| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhang Qun Inventor after: Li Chaochao Inventor after: Zhang Peng Inventor after: Wang Xin Inventor after: Hai Han Inventor after: Li Yifei Inventor after: Shen Shuai Inventor after: Song Yaheng Inventor after: Kou Rui Inventor after: Li Chengyu Inventor before: Zhang Qun Inventor before: Li Yifei Inventor before: Shen Shuai Inventor before: Song Yaheng Inventor before: Kou Rui Inventor before: Li Chengyu Inventor before: Li Chaochao |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190813 |
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| CF01 | Termination of patent right due to non-payment of annual fee |