CN107091486A - 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
- CN107091486A CN107091486A CN201710227204.2A CN201710227204A CN107091486A CN 107091486 A CN107091486 A CN 107091486A CN 201710227204 A CN201710227204 A CN 201710227204A CN 107091486 A CN107091486 A CN 107091486A
- Authority
- CN
- China
- Prior art keywords
- cyclone
- burner
- afterbunring
- air
- 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.)
- Granted
Links
- 210000000988 bone and bone Anatomy 0.000 claims abstract description 11
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 10
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims abstract description 4
- 238000002485 combustion reaction Methods 0.000 claims description 14
- 238000009792 diffusion process Methods 0.000 claims 3
- 239000000295 fuel oil Substances 0.000 abstract description 11
- 230000003134 recirculating effect Effects 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 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
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002708 enhancing effect Effects 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)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Cyclones (AREA)
Abstract
The 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 produced in after-burner, so as to farthest reduction air velocity, it is ensured that the stable burning of after-burner.Meanwhile, expansion air inlet section is provided with reinforcing tail bone afterbody, and in the centrally disposed expansion air admission hole of cyclone, afterbunring After-market internal gas flow flowing velocity can be greatly reduced by number of ways, provide space for stable burning.Air-flow makes fuel-oil atmozation more thorough, so as to make burning more abundant by that can produce shear action to fuel oil after cyclone.Air-flow is by expanding after air inlet section, and fraction can effectively reduce after-burner wall temperature by after-burner inside and outside wall center-aisle, improve aircraft infrared stealth performance.
Description
Technical field
The invention belongs to after-burner field, and in particular to one kind can effectively adjust air flow state, significantly carry
The after-burner annular flame barrel structure with cyclone of high combustion stability and efficiency of combustion.
Background technology
After-burner is the important component of modern Aviation gas turbine, is mainly pushed away on military aircraft for greater engine
Power, enhancing air maneuver and use in short-term.Using after-burner, it can avoid compared with the engine of high thrust making because using
Front face area and the quality increase of aircraft.
After-burner using the remaining oxygen in combustion gas spray into again fuel oil carry out 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 causes after-burner of short duration in taking off, climbing or fighting can only use.It is severe in after-burner
Burning situation also carry out very big difficulty to combustion zone.Wherein topmost 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 be lighted a fire in the air-flow of high speed, and stable burning, the performance of an after-burner will be determined, is entered
And influence the performance of whole engine.
In main chamber, most combustion chamber reduces air velocity using cyclone, and the operation principle of cyclone is：In gas
Stream passes through after cyclone, flow rotation forward travel, and expands laterally, the increase of outside air velocity, has volume to central gas stream
Suction is acted on, so as to cause central pressure to reduce；As air-flow is moved backward, speed is gradually reduced, and central pressure gradually rises, from
And adverse pressure gradient is produced at burner inner liner center, backflow.Due to the generation of backflow, low speed is generated in a combustion chamber
Area, so as to provide condition for flame stabilization burning.
This programme adds cyclone in after-burner, and flame stabilization burning is effectively improved so as to produce recirculating zone
Region, meanwhile, cyclone can make fuel-oil atmozation more thorough, so as to ensure the efficiency of combustion of after-burner.
The content of the invention
The technical problem to be solved in the present invention is that one kind can effectively adjust air flow state in after-burner, significantly
Improve the annular flame barrel structure with cyclone of combustion stability and efficiency of combustion.Compared with prior art, the program exists
6 cyclones are installed additional in the middle part of after-burner, large-scale recirculating zone can be produced in after-burner, so as to maximum
The reduction air velocity of degree, it is ensured that the stable burning of after-burner.Meanwhile, cyclone structure is with respect to the bluff body flame such as v-shaped groove
Rock-steady structure, can effectively reduce the pressure loss.Vortex gas-flow can produce shear action to fuel oil, make fuel-oil atmozation more thorough
Bottom, so as to make burning more abundant.
Technical scheme
Can effectively adjust air flow state it is an object of the invention to provide one kind, 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, in after-burner entry position using one layer of rectification support plate, support plate is high
Spend for the 1/3~1/2 of after-burner entrance height.The diffuser entrance of flaring, expansion angle are used in the middle part of reinforcing tail bone
For 10 °~20 °, drift angle should be less than the wall angle of the corresponding reinforcing tail bone in the position.Reinforce tail bone afterbody and cyclone is set,
6 single-stage cyclones are set on ring baffle.Wherein swirler blades drift angle is 15 °~30 °, the centrally disposed flaring circle of cyclone
Shape entrance, flaring angle is 5 °~10 °.Cyclone centre-height is the 1/5~1/4 of after-burner channel height, one-level leaf
Slightly above cyclone centre-height highly can be set in piece, and cyclone total length is 20mm~50mm, can be big according to after-burner
It is small suitably to be adjusted.Cyclone ring baffle sets two to discharge into stomata, and first row air admission hole is located at ring baffle top 1/5
Place, hole is alternate with cyclone to be arranged, and opening diameter is 15mm~20mm, totally 6 holes.Second row air admission hole is located at ring baffle
The position of bottom 1/3, opening diameter is 20~25mm, totally 6 holes.
Swirler blades blade profile uses airflow design, wherein, leaf head uses a diameter of 1~1.5mm circular arc, leaf
Body uses radius for 500~1000mm circular arc, it is ensured that the airflow design of swirl vane.
Following beneficial effect can use to obtain using the present invention：
1. the present invention adds cyclone Combination Design to carry out flow slowing down using rectification support plate, large-scale backflow can be produced
Area, so as to ensure the stable burning of after-burner internal flame.
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, the fineness of fuel oil is improved, so as to ensure that fuel oil more fully burns.
3. after-burner sets inwall, after-burner wall can effectively be cooled down, reduce after-burner
Infra-red radiation, so as to improve aircraft Stealth Fighter.
Brief description of the drawings
Fig. 1：After-burner sectional view；
Fig. 2：Cyclone layout viewing；
Fig. 3：Cyclone schematic diagram；
Fig. 4：After-burner stereogram；
In Fig. 1：1- afterbunring chamber inlet rectification support plates, 2- reinforcing tail bones, 3- cyclones, 4- center annular baffle plates, plus
Power burning outer wall, 6- afterbunring chamber interior walls
In Fig. 2：1- afterbunring chamber outer walls, 2- afterbunring chamber interior walls, 3- cyclones, 4- first row air admission holes, 5- rotations
Liu Qi centers flaring air admission hole, 6- second row air admission holes
Embodiment
In conjunction with accompanying drawing, the invention will be further described：
With reference to Fig. 1, Fig. 2 and Fig. 3, after-burner internal gas flow flow regime can be changed the invention provides one kind, is increased
Big after-burner recirculating zone size, improves fuel-oil atmozation fineness, improves the after-burner with cyclone of flame holding
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 cyclone leaf
Piece sectional view.
Air-flow is by entering after after-burner, and by entrance rectification support plate (1 in Fig. 1), air-flow is tentatively slowed down, afterwards
By diffuser (7 in Fig. 1), air-flow further slows down, and air-flow is by cyclone (3 in Fig. 1) afterwards, and air-flow produces local rotation
Stream, recirculating zone is produced at after-burner rear portion, at the same fuel oil blended by the effect of eddy flow it is more uniform, so as to add
The burning of power combustion chamber well provides condition.Meanwhile, air-flow can discharge into stomata by the two of center annular baffle plate (4 in Fig. 1)
(6) enter air-flow in Fig. 2 in 4, Fig. 2, the air of abundance is provided for burning.Air-flow is divided into two strands when by diffuser, wherein
Most of air-flow participates in burning by central passage by slowing down, and another fraction air-flow passes through between after-burner inside and outside wall
Passage, can effective cooling wall, after-burner infra-red radiation is reduced, so as to improve the Stealth Fighter of aircraft.
Claims (5)
1. a kind of afterbunring cell structure with cyclone, it is characterised in that：Afterbunring chamber inlet is using one layer of rectification branch
Plate, sets diffusion air inlet section in the middle part of reinforcing tail bone, and reinforcing tail bone afterbody sets and sets cyclone on ring baffle, baffle plate.
2. a kind of afterbunring cell structure with cyclone according to claim 1, it is characterised in that：Entry position is whole
It is 35~40mm to flow support plate length, and thickness is 5~8mm, and rectification support plate blade profile head uses radius for 1~3mm circular arcs, and blade is adopted
With the circular arc that radius is 1600~2000mm, whole blade profile is using streamlined.
3. a kind of afterbunring cell structure with cyclone according to claim 1, it is characterised in that：Reinforce in tail bone
The diffusion air inlet section that portion is set, wherein diffuser expansion angle are 10 °~20 °, and expansion angle should be less than corresponding to the position
The wall angle of tail bone is reinforced, to ensure diffusion air inlet section as expansion entrance.Diffuser is connected with afterbunring chamber interior walls, plus
Distance is 2~6mm between the inside and outside wall of power combustion chamber.
4. a kind of afterbunring cell structure with cyclone according to claim 1, it is characterised in that：After-burner
The ring baffle at reinforcing tail bone position is set to totally enclosed, is connected with afterbunring chamber interior walls and reinforcing tail bone wall, its
In open two in ring baffle and discharge into stomata, often arrange 6, wherein, first row air admission hole is located at ring baffle top 1/5, perforate
A diameter of 15mm~20mm；Second row air admission hole is located at the position of ring baffle bottom 1/3, and opening diameter is 20~25mm.
5. a kind of afterbunring cell structure with cyclone according to claim 1 or 4, it is characterised in that：Reinforcing combustion
Burn room and 6 single-stage cyclones are set on ring baffle.Cyclone centre-height is the 1/5~1/ of after-burner channel height
4, the settable slightly above cyclone centre-height of one-level blade height, cyclone total length is 20mm~50mm, can be according to reinforcing
Combustion chamber size is suitably adjusted.Wherein swirler blades drift angle is 15 °~30 °, and the centrally disposed flaring circle of cyclone enters
Mouthful, flaring angle is 5 °~10 °.
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 true CN107091486A (en) | 2017-08-25 |
| CN107091486B CN107091486B (en) | 2019-08-13 |
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Family Applications (1)
| 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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| Country | Link |
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| CN (1) | CN107091486B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108332233A (en) * | 2018-01-08 | 2018-07-27 | 南京航空航天大学 | The combustion chamber of combustion zone and its special support plate are adjusted based on import eddy flow rectification support plate |
| CN109556136A (en) * | 2017-09-25 | 2019-04-02 | 通用电气公司 | Gas turbine assemblies and method for inhibiting its pressure fluctuation |
| CN111780160A (en) * | 2020-08-21 | 2020-10-16 | 中国科学院工程热物理研究所 | Blunt body flame stabilizer with whirl stationary vortex structure |
| CN114719293A (en) * | 2022-03-24 | 2022-07-08 | 西北工业大学 | Ring cavity afterburner structure |
| CN115143489A (en) * | 2022-06-15 | 2022-10-04 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale cyclone air intake |
Citations (5)
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|---|---|---|---|---|
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| US20150121886A1 (en) * | 2013-03-08 | 2015-05-07 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine afterburner |
| 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 |
-
2017
- 2017-04-10 CN CN201710227204.2A patent/CN107091486B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150121886A1 (en) * | 2013-03-08 | 2015-05-07 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine afterburner |
| 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 |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109556136A (en) * | 2017-09-25 | 2019-04-02 | 通用电气公司 | Gas turbine assemblies and method for inhibiting its pressure fluctuation |
| CN108332233A (en) * | 2018-01-08 | 2018-07-27 | 南京航空航天大学 | The combustion chamber of combustion zone and its special support plate are adjusted based on import eddy flow rectification support plate |
| CN111780160A (en) * | 2020-08-21 | 2020-10-16 | 中国科学院工程热物理研究所 | Blunt body flame stabilizer with whirl stationary vortex structure |
| CN114719293A (en) * | 2022-03-24 | 2022-07-08 | 西北工业大学 | Ring cavity afterburner structure |
| CN115143489A (en) * | 2022-06-15 | 2022-10-04 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale cyclone air intake |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN107091486B (en) | 2019-08-13 |
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| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| 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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| CB03 | Change of inventor or designer information | ||
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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 |