CN103807878A - Combustion chamber fuel jetting and mixing device and combustion chamber with same - Google Patents
Combustion chamber fuel jetting and mixing device and combustion chamber with same Download PDFInfo
- Publication number
- CN103807878A CN103807878A CN201210452038.3A CN201210452038A CN103807878A CN 103807878 A CN103807878 A CN 103807878A CN 201210452038 A CN201210452038 A CN 201210452038A CN 103807878 A CN103807878 A CN 103807878A
- Authority
- CN
- China
- Prior art keywords
- cyclone
- main combustion
- stage
- combustion stage
- combustion
- 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
Images
Abstract
The invention provides a combustion chamber fuel jetting and mixing device. The device comprises a pre-combustion stage, an intermediate stage and a main combustion stage, wherein the pre-combustion stage comprises a central conical body, a first-stage cyclone, a pre-film spray nozzle and a second-stage cyclone; the intermediate stage comprises an intermediate fuel supplying passage, a lining, an intermediate-stage cyclone and a sleeve, and fuel is supplied to a space, between the sleeve and the lining, at the downstream of the intermediate-stage cyclone; the main combustion stage comprises a main fuel supplying passage, a main-combustion-stage internal wall, a main-combustion-stage cyclone and a main-combustion-stage external wall, and the fuel is supplied to a space, between the main-combustion-stage internal wall and the main-combustion-stage external wall, at the downstream of the main-combustion-stage cyclone; the tail end of the main-combustion-stage internal wall and the tail end of the sleeve are connected, a hollow cavity is formed between the sleeve and the main-combustion-stage internal wall, cooling holes are formed in the tail end of the main-combustion-stage internal wall, and upstream air enters the hollow cavity and penetrates through the cooling holes so as to impact the tail end of the sleeve and cool the tail end of the main-combustion-stage internal wall and the tail end of the sleeve. The invention further provides a combustion chamber comprising the device.
Description
Technical field
The invention belongs to energy and power engineering burner field, particularly a kind of combustion chamber fuel oil injection of aero-engine and mixing arrangement and comprise the combustion chamber of this device.
Background technology
Along with atmospheric environment problem worldwide receives increasing concern, require also increasingly strict for aero-engine pollutant emission.The Aeroengine Products market demand of future generation shows, the discharge capacity of nitrogen oxide (NOx) also will reduce by 50% left and right than existing International Civil Aviation Organization (ICAO) required standard, and simultaneously other emissions are such as carbon monoxide (CO) and unburned carbon hydrogen (UHC) all will be lower than ICAO specified standards.
Research shows, the indoor fuel gas temperature of control combustion is the key of controlling NOx disposal of pollutants, and one of Major Technology of control combustion district temperature is exactly to adopt poor oil firing's pattern.But under the duty such as ground idle speed, starting ignition, need again combustion zone to adopt the fuel-air matching mode that approaches fuel-rich combustion, to guarantee combustibility, reduce CO and UHC discharge under small-power state simultaneously.In order to solve the contradiction of CO, UHC discharge under the discharge of NOx under high-power state and small-power state, can adopt the form of fractional combustion, under assurance engine different capacity, combustion chamber regional area burns with best fuel-air match pattern.
The grading combustion technology application of having succeeded on aeroengine combustor buring chamber, more work is being done by GE company aspect the low emission combustor of this type, design the fuel injection equipment (FIE) that can realize poor oil firing for the application of engine engineering, such as: the dicyclo cavity combustion chamber grading combustion technology that some engine adopts; The center grading combustion technology that some engine adopts, this technology adopts three grades of fuel feeding, Pyatyi cyclone.
Because compact conformation, subregion poor oil firing are controlled the advantages such as NOx effect is better, adopting center grading combustion technology has been the trend of low emission combustor development.But existing grading combustion technology, not can solve the contradiction of the classification status point NOx discharge that faces in grading combustion technology and CO, UHC discharge performance, and the cyclone adopting is too much, causes structure comparatively complicated.
Summary of the invention
Therefore, provide a kind of simple and compact for structure, can effectively reduce the discharge capacity of key pollutants NOx, to spray with mixing arrangement will be favourable for the combustion chamber fuel oil that can reduce again the discharge capacity of CO, UHC under low operating mode.
According to a first aspect of the invention, provide a kind of combustion chamber fuel oil to spray and mixing arrangement, described device comprises pre-combustion grade, around the intergrade of described pre-combustion grade with around the main combustion stage of described intergrade, wherein:
Described pre-combustion grade comprises conical inner body, around the one-level cyclone of described conical inner body, around the pre-membrane type nozzle of described one-level cyclone and around the second cyclone of described pre-membrane type nozzle;
Fuel feeding path in the middle of described intergrade comprises, lining, around the intergrade cyclone of described lining and around the sleeve of described intergrade cyclone, described in the middle of fuel feeding path supply fuel to the space of described intergrade cyclone downstream between described sleeve and described lining;
Described main combustion stage comprises main fuel feeding path, main combustion stage inwall, around the main combustion stage cyclone of described main combustion stage inwall and around the main combustion stage outer wall of described main combustion stage cyclone, described main fuel feeding path supplies fuel to the space of described main combustion stage cyclone downstream between described main combustion stage inwall and main combustion stage outer wall; And
The end of described main combustion stage inwall is connected with the end of described sleeve and forms a cavity between described sleeve and described main combustion stage inwall, the end of described main combustion stage inwall is provided with at least one Cooling Holes, upstream air enters described cavity and impacts the end of described sleeve, the end of cooling described main combustion stage inwall and the end of described sleeve thus through described Cooling Holes.
Aspect this, there is following beneficial effect of the present invention:
1. simple and compact for structure: to adopt level Four cyclone and three grades of independent oil supplies, radially arrange from center pre-combustion grade, intergrade, main combustion stage structure, the eddy flow that makes full use of cyclones generations at different levels reaches the object of three bursts of fuel injected of atomization, optimized fuel-air matching, the effect of the control key pollutants NOx of subregion poor oil firing is better.
2. pre-combustion grade oil circuit is selected pre-membrane type nozzle, can improve nozzle anti-carbon deposition performance, and obtains higher low-load performance, reduces CO, UHC discharge capacity.
3. carry out the group section between cooling main combustion stage and intergrade by upstream air, thereby can effectively extend the service life of apparatus of the present invention.
Preferably, described main fuel feeding path and/or middle fuel feeding path are provided with nozzle.
Further preferably, described nozzle adopts pressure atomization structure or pneumatic nebulization structure.
Again further preferably, described nozzle comprises at least one spray site or adopts domain liquid film to spray.Main combustion stage and intergrade adopt respectively direct-injection type multi-point fuel injection or domain liquid film injection design, and fuel oil sprays in the swirling eddy of cyclone generation, and atomizing effect is good.
Preferably, described pre-combustion grade, described intergrade and described main combustion stage inwall form an entirety by welding, and coordinate with described main combustion stage cyclone axial float.This assembly entirety vertically centerline direction moves and carries out dismounting, thereby the oil circuit of three grades of fuel feeding all can, with nozzle body in the lump dismounting, can effectively check oil circuit working condition.
Further preferably, described main combustion stage inwall has installs the radially expansion wall arranging with guiding slope wall with described guiding slope wall next-door neighbour, and the described wall that radially expands coordinates with the fixed wall axial float of described main combustion stage cyclone.The arranging of guiding slope wall facilitates assembly entirety along the center line importing that slides axially.
According to a second aspect of the invention, provide a kind of combustion chamber, comprise that aforesaid combustion chamber fuel oil sprays and mixing arrangement.This combustion chamber has all beneficial effects of device according to a first aspect of the invention.
By reference to described embodiment below, these and other aspects of the present invention will clearly be set forth.
Accompanying drawing explanation
Structure of the present invention and mode of operation and further object and advantage will be better understood by the description below in conjunction with accompanying drawing, and wherein, identical reference marker identifies identical element:
Fig. 1 shows the cutaway view with the preferred embodiment of mixing arrangement according to the injection of combustion chamber of the present invention fuel oil;
Fig. 2 shows combustion chamber fuel oil in Fig. 1 and sprays and the assembling schematic diagram of mixing arrangement.
Description of reference numerals
1 first mating surface 2 second mating surfaces
3 main combustion stage cyclone 4 fixed walls
5 radially expand the wall 51 slope wall that leads
6 main fuel feeding path 7 nozzles
10 nozzle 11 sleeves
12 pre-membrane type nozzle 121 gaps
13 conical inner body 14 one-level cyclones
The pre-liquid film spout of 15 second cyclone 16
17 lining 18 main combustion stage outer walls
19 main combustion stage inwall 20 Cooling Holes
21 end 22 main combustion stage passages
The specific embodiment
Some terms of paper the art, wherein:
Cyclone: the device that makes γ-ray emission rotating jet;
Fractional combustion: a kind of combustion strategies, be divided into axially staged burning and radial grading burning, refer to fuel oil, the mixed combustion of air subregion, burn in zones of different;
Nozzle: the device of fuel oil injection and atomization;
Fuel-oil atmozation: utilize nozzle liquid fuel to be become to oil droplet group's process;
Shown in Fig. 1 and Fig. 2, spray with mixing arrangement and adopt the fuel oil injection, the air-fuel mixture system that are formed by fuel nozzle system and cyclone according to combustion chamber of the present invention fuel oil, and be provided with 3 grades of independent partitions fuel feeding according to arranging of center classification.Whole device is connected with group section and the splash pan of combustion chamber flame drum head end wall with the second mating surface 2 by the first mating surface 1 is installed.
Fig. 1 shows the cutaway view of whole device along central axis.Combustion chamber fuel oil sprays with mixing arrangement and comprises pre-combustion grade, intergrade and main combustion stage, and intergrade is around pre-combustion grade, and main combustion stage is around intergrade.
In the present embodiment, pre-combustion grade adopts pre-membrane type nozzle 12, comprises conical inner body 13, around the one-level cyclone 14 of conical inner body 13, around the pre-membrane type nozzle 12 of one-level cyclone 14 and around the second cyclone 15 of pre-membrane type nozzle 12.Wherein, fuel oil enters long and narrow gap 1 21 from pre-membrane type nozzle 12, then form liquid film from pre-liquid film spout 16 ejections, oil film both sides are respectively the vortex gas-flows that first order cyclone 14 and second level cyclone 15 form, thereby oil film atomization under the shear action of vortex gas-flow, and spray into combustion chamber.
Main combustion stage comprises main fuel feeding path 6, main combustion stage inwall 19, around the main combustion stage cyclone 3 of main combustion stage inwall 19 and around the main combustion stage outer wall 18 of main combustion stage cyclone 3, main fuel feeding path 6 supplies fuel to the space of main combustion stage cyclone 3 downstreams between main combustion stage inwall 19 and main combustion stage outer wall 18.Wherein, peripheral main combustion stage passage 22 is made up of main combustion stage outer wall 18 and main combustion stage inwall 19, channel entrance is settled main combustion stage cyclone 3, fuel oil sprays the multi-point injection simple nozzle 7 that adopts circumferential Central Symmetry to arrange, the fuel oil spraying into goes out atomization under the swirling eddy effect of interruption-forming and sprays into combustion chamber at cyclone 3.Main fuel feeding path 6 is connected with fuel system.
The end of main combustion stage inwall 19 is connected with the end 21 of sleeve 11, and between sleeve 11 and main combustion stage inwall 19, form a cavity, the end of main combustion stage inwall 19 is provided with at least one Cooling Holes 20, upstream air enters this cavity and carrys out the end 21 of impingement sleeve 11 through Cooling Holes 20, the end 21 of the end of cooling main combustion stage inwall 19 and sleeve 11 thus, i.e. group section between cooling main combustion stage and intergrade.
In some embodiments, nozzle 7 or 10 can adopt pressure atomization structure or pneumatic nebulization structure, and comprises at least one spray site or adopt domain liquid film to spray.
As shown in Figure 2, in the present embodiment, the cyclones at different levels of the pre-combustion grade of fuel injection equipment (FIE), intergrade, main combustion stage are connected group section with assembly, are designed to an entirety that adopts welding procedure.Thereby this assembly entirety can move and carry out dismounting along centerline direction, thereby coordinate and can realize overall rapid-assembling/disassembling with main combustion stage cyclone 3 axial floats, assemblage gap mating surface is radially expanding between wall 5 and the fixed wall 4 of outermost main combustion stage cyclone 3.In figure dashed region be can dismounting assembly entirety, when assembling by the installation that radially expands wall 5 with guiding slope wall 51 along the center line importing that slides axially from left to right, this cooperation can realize Fast Installation and the dismounting between assembly entirety and main combustion stage cyclone 3.Wherein, in Fig. 2, the direction of arrow is installation direction, and disassembly direction is contrary with installation direction.
The present invention is according to the demand of engine different capacity, center radial direction pre-combustion grade, intergrade, the main combustion stage totally 3 grades of independent partitions fuel feeding of having arranged.Between 3 grades of fuel feeding, interact less, avoid near the classification status point of combustion chamber producing the local air-fuel mixture district that is unfavorable for burning, can in compared with wide operating range, well solve the contradiction of the classification status point NOx discharge that faces in grading combustion technology and CO, UHC discharge performance.
The specific embodiment described in the present invention is only better case study on implementation of the present invention, is not used for limiting practical range of the present invention.Be that all equivalences of doing according to the content of the present patent application the scope of the claims change and modify, all belong to protection scope of the present invention.
Claims (7)
1. combustion chamber fuel oil sprays and a mixing arrangement, it is characterized in that, described device comprises pre-combustion grade, around the intergrade of described pre-combustion grade with around the main combustion stage of described intergrade, wherein:
Described pre-combustion grade comprises conical inner body (13), around the one-level cyclone (14) of described conical inner body (13), around the pre-membrane type nozzle (12) of described one-level cyclone (14) and around the second cyclone (15) of described pre-membrane type nozzle (12);
Fuel feeding path (8), lining (17) in the middle of described intergrade comprises, around the intergrade cyclone (9) of described lining (17) and around the sleeve (11) of described intergrade cyclone (9), described in the middle of fuel feeding path (8) supply fuel to described intergrade cyclone (9) downstream and be positioned at the space between described sleeve (11) and described lining (17);
Described main combustion stage comprises main fuel feeding path (6), main combustion stage inwall (19), around the main combustion stage cyclone (3) of described main combustion stage inwall (19) and around the main combustion stage outer wall (18) of described main combustion stage cyclone (3), described main fuel feeding path (6) supplies fuel to described main combustion stage cyclone (3) downstream and is positioned at the space between described main combustion stage inwall (19) and main combustion stage outer wall (18); And
The end of described main combustion stage inwall (19) is connected with the end (21) of described sleeve (11) and forms a cavity between described sleeve (11) and described main combustion stage inwall (19), the end of described main combustion stage inwall (19) is provided with at least one Cooling Holes (20), upstream air enters described cavity and impacts the end (21) of described sleeve (11), the end (21) of the end of cooling described main combustion stage inwall (19) and described sleeve (11) thus through described Cooling Holes (20).
2. combustion chamber according to claim 1 fuel oil sprays and mixing arrangement, it is characterized in that, described main fuel feeding path (6) and/or middle fuel feeding path (8) are provided with nozzle (7,10).
3. combustion chamber according to claim 2 fuel oil sprays and mixing arrangement, it is characterized in that, described nozzle (7,10) adopts pressure atomization structure or pneumatic nebulization structure.
4. combustion chamber according to claim 3 fuel oil sprays and mixing arrangement, it is characterized in that, described nozzle (7,10) comprises at least one spray site or adopts domain liquid film to spray.
5. spray and mixing arrangement according to the combustion chamber fuel oil described in any one in claim 1 to 4, it is characterized in that, described pre-combustion grade, described intergrade and described main combustion stage inwall (19) form an entirety by welding, and coordinate with described main combustion stage cyclone (3) axial float.
6. combustion chamber according to claim 5 fuel oil sprays and mixing arrangement, it is characterized in that, described main combustion stage inwall (19) has installs the radially expansion wall (5) arranging with guiding slope wall (51) with described guiding slope wall (51) next-door neighbour, and the described wall (5) that radially expands coordinates with fixed wall (4) axial float of described main combustion stage cyclone (3).
7. a combustion chamber, is characterized in that, comprises according to the combustion chamber fuel oil described in any one in claim 1 to 6 and spraying and mixing arrangement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210452038.3A CN103807878B (en) | 2012-11-13 | 2012-11-13 | A kind of combustion chamber fuel oil sprays and mixing arrangement and the combustion chamber comprising this device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210452038.3A CN103807878B (en) | 2012-11-13 | 2012-11-13 | A kind of combustion chamber fuel oil sprays and mixing arrangement and the combustion chamber comprising this device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103807878A true CN103807878A (en) | 2014-05-21 |
| CN103807878B CN103807878B (en) | 2016-04-20 |
Family
ID=50705027
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210452038.3A Active CN103807878B (en) | 2012-11-13 | 2012-11-13 | A kind of combustion chamber fuel oil sprays and mixing arrangement and the combustion chamber comprising this device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103807878B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN114877377A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Outer ring detonation combustion chamber |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
| EP2051010A1 (en) * | 2007-10-18 | 2009-04-22 | Rolls-Royce Deutschland Ltd & Co KG | Lean pre-mixture reactor for a gas turbine engine |
| US7878000B2 (en) * | 2005-12-20 | 2011-02-01 | General Electric Company | Pilot fuel injector for mixer assembly of a high pressure gas turbine engine |
| JP4997018B2 (en) * | 2007-08-09 | 2012-08-08 | ゼネラル・エレクトリック・カンパニイ | Pilot mixer for a gas turbine engine combustor mixer assembly having a primary fuel injector and a plurality of secondary fuel injection ports |
-
2012
- 2012-11-13 CN CN201210452038.3A patent/CN103807878B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7878000B2 (en) * | 2005-12-20 | 2011-02-01 | General Electric Company | Pilot fuel injector for mixer assembly of a high pressure gas turbine engine |
| JP4997018B2 (en) * | 2007-08-09 | 2012-08-08 | ゼネラル・エレクトリック・カンパニイ | Pilot mixer for a gas turbine engine combustor mixer assembly having a primary fuel injector and a plurality of secondary fuel injection ports |
| EP2051010A1 (en) * | 2007-10-18 | 2009-04-22 | Rolls-Royce Deutschland Ltd & Co KG | Lean pre-mixture reactor for a gas turbine engine |
| CN101169252A (en) * | 2007-11-29 | 2008-04-30 | 北京航空航天大学 | Aerial engine lean premixed preevaporated low contamination combustion chamber |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN114877377A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Outer ring detonation combustion chamber |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103807878B (en) | 2016-04-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102200291B (en) | Pneumatic primary level graded low-pollution combustion chamber | |
| EP2481982B2 (en) | Mixer assembly for a gas turbine engine | |
| CN101709884B (en) | Premixing and pre-evaporating combustion chamber | |
| CN101275750B (en) | Radial swirler turning zone direct injection premixing and prevapourising low pollution burning chamber | |
| CN103123122B (en) | The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays | |
| CN101799174B (en) | Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber | |
| CN102506446B (en) | Fuel and air mixing device for low-pollution burning chamber of gas turbine | |
| CN202303463U (en) | Fuel oil and air mixing device for low-pollution combustion chamber | |
| CN103629696B (en) | A kind of combustion chamber fuel oil sprays and mixing arrangement and combustion chamber thereof | |
| CN102889618B (en) | Annular combustion chamber based on Venturi pre-mixing bispin nozzle | |
| CN102889616B (en) | Multi-point direct spray combustion chamber based on venturi premixing double spiral nozzle | |
| CN100557318C (en) | A kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber | |
| CN104456628A (en) | Layered part premixing low-pollution combustor of main combustion level lean oil premixing | |
| CN107143880B (en) | Lean oil multi-point direct injection head for low-pollution combustion chamber of gas turbine | |
| CN105157062A (en) | Low-emission combustion chamber with double-layer axial hydrocyclone adopted at precombustion stage | |
| CN103791518B (en) | A kind of combustion chamber fuel oil sprays and mixing arrangement and aero-engine | |
| CN203671655U (en) | Combustor fuel injecting and mixing system | |
| CN203671653U (en) | Combustor for gas turbine | |
| CN101285591A (en) | Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber | |
| CN107143881B (en) | Multi-point direct injection head structure for low-pollution combustion chamber of gas turbine | |
| CN103486617B (en) | A kind of dual-fuel low-emission burner for gas turbine | |
| CN202675358U (en) | Mixing device, combustion chamber and aeroengine | |
| CN101275751A (en) | Radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution burning chamber | |
| CN103807878B (en) | A kind of combustion chamber fuel oil sprays and mixing arrangement and the combustion chamber comprising this device | |
| CN102997281A (en) | System and method for conditioning a working fluid in a combustor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |