CN108151069A - A kind of primary zone Radial Flow combustion chamber and oil gas mixing method - Google Patents
A kind of primary zone Radial Flow combustion chamber and oil gas mixing method Download PDFInfo
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- CN108151069A CN108151069A CN201711232682.9A CN201711232682A CN108151069A CN 108151069 A CN108151069 A CN 108151069A CN 201711232682 A CN201711232682 A CN 201711232682A CN 108151069 A CN108151069 A CN 108151069A
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- inner liner
- burner inner
- combustion chamber
- flame cylinder
- flame
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Classifications
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- 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
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
Abstract
The present invention relates to a kind of primary zone Radial Flow combustion chamber and oil gas mixing methods, are related to engine chamber technical field.A kind of primary zone Radial Flow supersonic combustor organizational technology proposed by the present invention, increase inclined hole jet stream on the basis of flame tube head is with macropore jet stream, coordinated by inside and outside burner inner liner jet stream and disc+swirl atomizer fueller, enhance fuel oil to blend with air, gas mixture recirculating zone supply into primary zone is burnt after blending, residence time of the fuel oil inside burner inner liner is improved, strengthens oil gas blending, efficiency of combustion is improved and widens combustion chamber operational range.
Description
Technical field
The present invention relates to engine chamber technical fields, and in particular to a kind of primary zone Radial Flow combustion chamber and oil gas
Mixing method.
Background technology
Small-sized fanjet is one of key technology of high and medium high-speed unmanned aerial vehicle.Combustion chamber is small-sized fanjet
One of core component, since small-sized fanjet is mostly using the centrifugal compressor of big front face area or oblique flow dynamic pressure mechanism of qi as pressure
The afterbody of compression system so to make full use of the radial space after compressor, is arranged in pairs or groups therewith using Radial Flow combustion chamber
It is one of best selection.Small-sized fanjet application background direction is wide spatial domain and long endurance, must to meet the demand
It must be specifically designed for the job stability of wide spatial domain working environment and the cruise of long endurance, the wide spatial domain working range of research,
High combustion stability and simple in structure, compact head of combustion chamber organizational technology, it is steady to improve small-sized fanjet work
It is qualitative, ensure unmanned captain's endurance working condition.
Fanjet combustion chamber flow field organizational technology is that combustion chamber meets the basis that engine requires it comprehensively
And key, good, the ginsengs such as efficiency of combustion, discharge, Exit temperature distribution, starting and igniting of combustion chamber flame drum head burning tissues
Number, which can be only achieved, requires index.Flame tube head vortex structure is a kind of common fluidal texture, head in Combustion chamber design at present
The quality of vortex structure has vital effect to the blending of combustion chamber oil gas and flame holding, is the core of Combustion chamber design
Intracardiac appearance.For small-sized fanjet, mainly existed by cyclone or burner inner liner fluidic vectoring thrust head vortex structure, cyclone
The device of the widely used formation vortex structure in conventional scale combustion chamber, but for small-sized fanjet combustion chamber, due to
Its scale is small, and radial space is big, is added significantly to the axial distance and complexity of combustion chamber.Inner and outer ring jet stream is in burner inner liner
Inside formed vortex structure come carry out oil gas blending and stablize flame, advantage be it is simple in structure, but inner and outer ring jet stream generate whirlpool
Structure dimension and intensity are all little, to stablizing flame and strengthening oil gas mixing effect unobvious.
Invention content
(1) technical problems to be solved
The technical problem to be solved by the present invention is to：Residence time of the fuel oil inside burner inner liner how is improved, strengthens oil gas
Blending improves efficiency of combustion and widens combustion chamber operational range.
(2) technical solution
In order to solve the above technical problem, the present invention provides a kind of primary zone Radial Flow combustion chamber, the combustion chambers
For full-annular type combustion chamber, including casing 9 and flame cylinder 11 in outer burner inner liner 1, outer combustion case 3, disc 5, combustion chamber；
Casing 9, outer burner inner liner 1 and flame cylinder 11 are fixed on engine interior, engine in the outer combustion case 3, combustion chamber
It is static during work；The disc 5 is fixed on engine high pressure axis, between outer burner inner liner 1 and flame cylinder 11；Hair
When motivation works, disc 5 is rotated with high-pressure shaft；6 cyclones are evenly arranged on disc 5, cyclone is by spin chamber 6 and combustion
Oil jet 7 forms, wherein, fuel jet 7 is the outlet of spin chamber 6, and outer burner inner liner 1, flame cylinder 11 are by there is certain curvature
Type face composition, be provided on outer 1 wall surface of burner inner liner outer burner inner liner primary holes 2, outer burner inner liner premix hole 4, in interior burner inner liner 11
Flame cylinder primary holes 10 and flame cylinder premix hole 8 are provided on wall surface, when engine works, air-flow is by the two main combustions
Hole and two premix hole fluidic vectoring thrust flame tube head combustion organizational structures, the trepanning principle of outer burner inner liner primary holes 2 are and water
The angle of plane is 45 °；The trepanning principle in outer burner inner liner premix hole 4 is 45 ° for the angle with horizontal plane；Flame cylinder primary holes
10 trepanning principle is 60 ° for the angle with horizontal plane；The trepanning principle in flame cylinder premix hole 8 is to be with the angle of horizontal plane
60°；When the engine operates, air-flow compression after enter formed between outer burner inner liner 1 and outer combustion case 3 outer ring channel,
The inner ring channel formed between casing 9 in flame cylinder 11 and combustion chamber is divided into two strands, when in terms of inner ring channel to outer ring channel,
Disc 5 is rotates clockwise, outer burner inner liner primary holes 2, outer burner inner liner premix hole 4, flame cylinder primary holes 10 and flame
Cylinder premix hole 8 tilts down trepanning.
Preferably, a diameter of 0.4mm~1mm of the fuel jet 7.
Preferably, the cyclone being made of the spin chamber 6 and fuel jet 7 is fixed on by helicitic texture gets rid of oil
On disk 5.
Preferably, the flame tube head axial length L is not more than 80mm, and flame tube head height is not more than 100mm.
Preferably, on 1 wall surface of outer burner inner liner cloth setting in the exclusive burner inner liner primary holes 2 in same level,
Totally 36, each bore dia is 8mm.
Preferably, cloth premixes hole 4 setting in the exclusive burner inner liner in same level on 1 wall surface of outer burner inner liner,
Totally 72, outer burner inner liner premixes 4 a diameter of 3mm of hole.
Preferably, on 11 wall surface of flame cylinder cloth setting in row's flame cylinder primary holes in same level
10, totally 36, each bore dia is 8mm.
Preferably, cloth premixes hole 8 setting in row's flame cylinder in same level on 11 wall surface of flame cylinder,
Totally 72, flame cylinder premix 8 a diameter of 3mm of hole.
The present invention also provides a kind of oil gas mixing methods realized using the combustion chamber, include the following steps：When
When engine works, enter the outer ring channel formed between outer burner inner liner 1 and outer combustion case 3, flame after air-flow compression
The inner ring channel formed between casing 9 in cylinder 11 and combustion chamber is divided into two strands, one is by outer burner inner liner primary holes 2 and outer burner inner liner
It premixes hole 4 and enters flame tube head, another stock premixes hole 8 by flame cylinder primary holes 10 and flame cylinder and enters burner inner liner head
Portion, the oil gas that this two strands of air-flows enter burner inner liner with disc 5 have cooperatively formed air flow swirl, and fuel oil is in disc 5
Wall jet, the fuel oil of injection to form one layer of adherent oil film by being rotated jointly with disc 5, under the influence of centrifugal force, should
Oil film enters spin chamber 6, and 6 internal fuel of spin chamber is rotated along 6 internal face of spin chamber, in centrifugal force and the common work of coriolis force
It is sprayed with lower by fuel jet 7, burns after oil gas blending, form burning tissues.
(3) advantageous effect
A kind of primary zone Radial Flow supersonic combustor organizational technology proposed by the present invention, is penetrated in flame tube head with macropore
Increase inclined hole jet stream on the basis of stream, coordinated by inside and outside burner inner liner jet stream and disc+swirl atomizer fueller, enhancing
Fuel oil is blended with air, and gas mixture recirculating zone into primary zone, which supplies, after blending burns, and improves fuel oil in burner inner liner
Internal residence time strengthens oil gas blending, improves efficiency of combustion and widens combustion chamber operational range.
Description of the drawings
Fig. 1 is the structure diagram of the present invention；
Fig. 2 is fueller structure diagram in Fig. 1.
Specific embodiment
To make the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to the present invention's
Specific embodiment is described in further detail.
As shown in fig. 1, primary zone Radial Flow combustion chamber of the invention be full-annular type combustion chamber, outer combustion case 3,
Casing 9, outer burner inner liner 1, flame cylinder 11 are fixed on engine interior in combustion chamber, and above-mentioned component is static when engine works；
Disc 5 is fixed in engine high pressure axis (not shown), between outer burner inner liner 1 and flame cylinder 11；Engine works
When, disc 5 is with high-pressure shaft high speed rotation；As shown in Fig. 2, being evenly arranged 6 cyclones on disc 5, cyclone is by eddy flow
Room 6 and fuel jet 7 form, wherein, outlet of the fuel jet 7 for spin chamber 6, a diameter of 0.4mm~1mm of fuel jet 7,
The cyclone being made of spin chamber 6 and fuel jet 7 is fixed on by helicitic texture on disc 5.Disc 5 revolves at a high speed
The oil gas generated after turning is mixed with the air that flame cylinder premix hole 8 and outer burner inner liner premix 4 jet stream of hole go out (see arrow in Fig. 1
It is shown), mixed oil gas enters flame tube head and forms stable burning tissues.Outer burner inner liner 1, flame cylinder 11 are by having
The type face composition of certain curvature is provided with outer burner inner liner primary holes 2, outer burner inner liner premix hole 4, inside on outer 1 wall surface of burner inner liner
Be provided on 11 wall surface of burner inner liner flame cylinder primary holes 10 and flame cylinder premix hole 8, engine work when, air-flow by this
Two primary holes and two premix hole fluidic vectoring thrust flame tube head combustion organizational structures, are shown in rotation arrows part in Fig. 1.Flame
Cylinder head axial length L ≯ 80mm, flame tube head height ≯ 100mm.Cloth is setting in same level on outer 1 wall surface of burner inner liner
On an exclusive burner inner liner primary holes 2, totally 36, each bore dia is 8mm, and the trepanning principle of outer burner inner liner primary holes 2 is essentially
Angle with wall surface plane where circumferential is 45 °.Cloth premixes hole 4 setting in 1 exclusive burner inner liner in same level, and totally 72
A, outer burner inner liner premixes 4 a diameter of 3mm of hole, and the trepanning principle in outer burner inner liner premix hole 4 is essentially and the circumferential place plane of wall surface
Angle be 45 °.Cloth is setting in row's flame cylinder primary holes 10 in same level on 11 wall surface of flame cylinder, and totally 36
A, each bore dia is 8mm, and it with the angle of wall surface plane where circumferential is 60 ° that the trepanning principle of flame cylinder primary holes 10, which is,.Cloth
Hole 8 is premixed setting in 1 row's flame cylinder in same level, totally 72, flame cylinder premixes 8 a diameter of 3mm of hole, flame
It is 60 ° that the trepanning principle in cylinder premix hole 8, which is essentially with the angle of wall surface plane where circumferential,.When the engine operates, air-flow pressure
Enter the outer ring channel formed between outer burner inner liner 1 and outer combustion case 3, flame cylinder 11 and casing 9 in combustion chamber after contracting
Between the inner ring channel that is formed be divided into two strands, when in terms of inner ring channel to outer ring channel, disc 5 is rotates clockwise, outer fire
Flame cylinder primary holes 2, outer burner inner liner premix hole 4, flame cylinder primary holes 10 and flame cylinder premix hole 8 tilt down trepanning.
The oil gas mixing method realized using the combustion chamber is included the following steps：When the engine operates, after air-flow compression
In into the outer ring channel, flame cylinder 11 and combustion chamber formed between outer burner inner liner 1 and outer combustion case 3 between casing 9
The inner ring channel of formation is divided into two strands, one enters flame tube head by outer burner inner liner primary holes 2 and outer burner inner liner premix hole 4,
Another stock premixes hole 8 by flame cylinder primary holes 10 and flame cylinder and enters flame tube head, this two strands of air-flows and disc 5
Oil gas into burner inner liner has cooperatively formed air flow swirl, and fuel oil is sprayed toward 5 internal face of disc, and the fuel oil of injection passes through
It rotates jointly to form one layer of adherent oil film with disc 5, under the influence of centrifugal force, which enters spin chamber 6, spin chamber 6
Internal fuel is rotated along 6 internal face of spin chamber, is sprayed under the collective effect of centrifugal force and coriolis force by fuel jet 7.
It burns after oil gas blending, forms stable burning tissues.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvement and deformation can also be made, these are improved and deformation
Also it should be regarded as protection scope of the present invention.
Claims (9)
1. a kind of primary zone Radial Flow combustion chamber, which is characterized in that the combustion chamber is full-annular type combustion chamber, including outer flame
Cylinder (1), outer combustion case (3), disc (5), casing (9) and flame cylinder (11) in combustion chamber；The burning outdoor unit
Casing (9), outer burner inner liner (1) and flame cylinder (11) are fixed on engine interior in casket (3), combustion chamber, when engine works
It is static；The disc (5) is fixed on engine high pressure axis, between outer burner inner liner (1) and flame cylinder (11)；Hair
When motivation works, disc (5) is rotated with high-pressure shaft；6 cyclones are evenly arranged on disc (5), cyclone is by spin chamber
(6) it is formed with fuel jet (7), wherein, outlet of the fuel jet (7) for spin chamber (6), outer burner inner liner (1), flame cylinder
(11) it is formed by by the type face of certain curvature, outer burner inner liner primary holes (2), outer flame is provided on outer burner inner liner (1) wall surface
Cylinder premix hole (4) is provided with flame cylinder primary holes (10) and flame cylinder premix hole (8), hair on interior burner inner liner (11) wall surface
Motivation work when, air-flow by the two primary holes and two premix hole fluidic vectoring thrust flame tube head combustion organizational structures,
The trepanning principle of outer burner inner liner primary holes (2) is 45 ° for the angle with horizontal plane；The trepanning principle of outer burner inner liner premix hole (4)
It it is 45 ° for the angle with horizontal plane；The trepanning principle of flame cylinder primary holes (10) is 60 ° for the angle with horizontal plane；Endogenous fire
The trepanning principle of flame cylinder premix hole (8) is 60 ° for the angle with horizontal plane；When the engine operates, enter after air-flow compression outer
The outer ring channel that is formed between burner inner liner (1) and outer combustion case (3), flame cylinder (11) and casing (9) in combustion chamber it
Between the inner ring channel that is formed be divided into two strands, when in terms of inner ring channel to outer ring channel, disc (5) is rotates clockwise, outer fire
Flame cylinder primary holes (2), outer burner inner liner premix hole (4), flame cylinder primary holes (10) and flame cylinder premix hole (8) dip down
Oblique trepanning.
2. combustion chamber as described in claim 1, which is characterized in that a diameter of 0.4mm~1mm of the fuel jet (7).
3. combustion chamber as described in claim 1, which is characterized in that the rotation being made of the spin chamber (6) and fuel jet (7)
Stream device is fixed on by helicitic texture on disc (5).
4. combustion chamber as described in claim 1, which is characterized in that the flame tube head axial length L is not more than 80mm, fire
Flame cylinder height of head is not more than 100mm.
5. combustion chamber as described in claim 1, which is characterized in that cloth is setting in same water on outer burner inner liner (1) wall surface
An exclusive burner inner liner primary holes (2) in plane, totally 36, each bore dia is 8mm.
6. combustion chamber as described in claim 1, which is characterized in that cloth is setting in same level on outer 1 wall surface of burner inner liner
Exclusive burner inner liner premix hole (4) on face, totally 72, outer burner inner liner premixes hole (4) a diameter of 3mm.
7. combustion chamber as described in claim 1, which is characterized in that cloth is setting in same water on flame cylinder (11) wall surface
Row's flame cylinder primary holes (10) in plane, totally 36, each bore dia is 8mm.
8. the combustion chamber as described in any one of claim 1 to 7, which is characterized in that cloth on flame cylinder (11) wall surface
Hole (8) are premixed setting in row's flame cylinder in same level, totally 72, flame cylinder premix hole (8) a diameter of 3mm.
9. a kind of oil gas mixing method that combustion chamber using described in any one of claim 1 to 8 is realized, including following step
Suddenly：When the engine operates, enter the outer shroud formed between outer burner inner liner (1) and outer combustion case (3) after air-flow compression to lead to
The inner ring channel formed between casing (9) in road, flame cylinder (11) and combustion chamber is divided into two strands, one is by the main combustion of outer burner inner liner
Into flame tube head, another stock passes through flame cylinder primary holes (10) and flame cylinder for hole (2) and outer burner inner liner premix hole (4)
Hole (8) are premixed into flame tube head, the oil gas of this two strands of air-flows and disc (5) into burner inner liner has cooperatively formed gas
Whirlpool is flowed, fuel oil is sprayed toward disc (5) internal face, and the fuel oil of injection to form one layer of patch by being rotated jointly with disc (5)
Wall oil film, under the influence of centrifugal force, the oil film enter spin chamber (6), and spin chamber's (6) internal fuel is along in spin chamber (6)
Wall surface rotates, and is sprayed under the collective effect of centrifugal force and coriolis force by fuel jet (7), burns after oil gas blending,
Form burning tissues.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201711232682.9A CN108151069B (en) | 2017-11-30 | 2017-11-30 | Main combustion zone radial flow combustion chamber and oil-gas mixing method |
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| CN201711232682.9A CN108151069B (en) | 2017-11-30 | 2017-11-30 | Main combustion zone radial flow combustion chamber and oil-gas mixing method |
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| CN108151069A true CN108151069A (en) | 2018-06-12 |
| CN108151069B CN108151069B (en) | 2020-03-31 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110513721A (en) * | 2019-09-19 | 2019-11-29 | 广东省航空航天装备技术研究所 | Bluff body structure surely fires combustion chamber |
| CN111473363A (en) * | 2020-06-02 | 2020-07-31 | 中国科学院工程热物理研究所 | Radially-partitioned oil thrower |
| CN112392602A (en) * | 2020-11-16 | 2021-02-23 | 四川航天中天动力装备有限责任公司 | Oil thrower disc of turbine engine |
| CN114278438A (en) * | 2021-12-03 | 2022-04-05 | 南京航空航天大学 | Intelligent combustion adjusting system for flow distribution of outlet of gas compressor and working method of intelligent combustion adjusting system |
| CN115143491A (en) * | 2022-06-06 | 2022-10-04 | 中科航星科技有限公司 | Be suitable for disc combustion chamber inner ring flame tube cooling module |
| CN115978582A (en) * | 2023-01-29 | 2023-04-18 | 中国航发沈阳发动机研究所 | Flame tube with wall surface jet nozzle |
| CN116045309A (en) * | 2023-01-29 | 2023-05-02 | 中国航发沈阳发动机研究所 | Radial swirl mixing reinforced flame tube |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110513721A (en) * | 2019-09-19 | 2019-11-29 | 广东省航空航天装备技术研究所 | Bluff body structure surely fires combustion chamber |
| CN111473363A (en) * | 2020-06-02 | 2020-07-31 | 中国科学院工程热物理研究所 | Radially-partitioned oil thrower |
| CN112392602A (en) * | 2020-11-16 | 2021-02-23 | 四川航天中天动力装备有限责任公司 | Oil thrower disc of turbine engine |
| CN114278438A (en) * | 2021-12-03 | 2022-04-05 | 南京航空航天大学 | Intelligent combustion adjusting system for flow distribution of outlet of gas compressor and working method of intelligent combustion adjusting system |
| CN115143491A (en) * | 2022-06-06 | 2022-10-04 | 中科航星科技有限公司 | Be suitable for disc combustion chamber inner ring flame tube cooling module |
| CN115143491B (en) * | 2022-06-06 | 2024-04-12 | 中科航星科技股份有限公司 | Be suitable for oil slinger combustor inner ring flame tube cooling module |
| CN115978582A (en) * | 2023-01-29 | 2023-04-18 | 中国航发沈阳发动机研究所 | Flame tube with wall surface jet nozzle |
| CN116045309A (en) * | 2023-01-29 | 2023-05-02 | 中国航发沈阳发动机研究所 | Radial swirl mixing reinforced flame tube |
| CN116045309B (en) * | 2023-01-29 | 2024-09-27 | 中国航发沈阳发动机研究所 | Radial swirl mixing reinforced flame tube |
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