CN103629696B - A kind of combustion chamber fuel oil sprays and mixing arrangement and combustion chamber thereof - Google Patents
A kind of combustion chamber fuel oil sprays and mixing arrangement and combustion chamber thereof Download PDFInfo
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- CN103629696B CN103629696B CN201210306279.7A CN201210306279A CN103629696B CN 103629696 B CN103629696 B CN 103629696B CN 201210306279 A CN201210306279 A CN 201210306279A CN 103629696 B CN103629696 B CN 103629696B
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Abstract
The invention provides a kind of combustion chamber fuel oil to spray and mixing arrangement, comprise pre-combustion grade, intergrade and main combustion stage.Pre-combustion grade comprises swirl atomizer, one-level cyclone, Venturi tube and second cyclone; Intergrade comprises middle fuel feeding path, lining, intergrade cyclone and sleeve, and middle fuel feeding path supplies fuel to the space of cyclone downstream between sleeve and lining; Main combustion stage comprises main fuel feeding path, main combustion stage inwall, main combustion stage cyclone and main combustion stage outer wall, and main fuel feeding path supplies fuel to the space of cyclone downstream between main combustion stage inwall and main combustion stage outer wall; The end of main combustion stage inwall is connected with the end of sleeve and forms a cavity, the end of main combustion stage inwall is provided with at least one Cooling Holes, upstream air is entered cavity and is carried out the end of impingement sleeve by Cooling Holes, cools the end of main combustion stage inwall and the end of sleeve thus.The present invention also provides a kind of above-mentioned combustion chamber fuel oil that comprises to spray the combustion chamber with mixing arrangement.
Description
Technical field
The invention belongs to energy and power engineering burner field, particularly a kind of combustion chamber fuel oil of aero-engine sprays and mixing arrangement and combustion chamber thereof.
Background technology
Along with atmospheric environment problem worldwide receives increasing concern, require more and more stricter especially for aero-engine pollutant emission.The Aeroengine Products market demand of future generation shows, the discharge capacity of nitrogen oxide (NOx) also will reduce about 50% than existing International Civil Aviation Organization (ICAO) required standard, and the discharge index that other emission such as carbon monoxide (CO) and unburned carbon hydrogen (UHC) all specifies than ICAO simultaneously retains certain nargin.
Research shows, the maximum gas temperature of control combustion indoor and combustion zone temperature uniformity, is the key of control NOx disposal of pollutants, and one of Major Technology of control combustion district temperature is exactly adopt lean premixed combustion mode.But under the duty such as ground idle speed, starting ignition, need again combustion zone employing close to the diffusion combustion fuel-air matching mode of stoichiometric ratio, to ensure combustibility, also can reduce CO and the UHC discharge under small-power state simultaneously.In order to solve the contradiction of CO, UHC discharge under NOx emission and small-power state under high-power state, can adopt the pattern of fractional combustion, under ensureing engine different capacity, combustion chamber regional area burns with best fuel-air match pattern.Grading combustion technology has been succeeded application on aeroengine combustor buring room, more work has been done in the low emission combustor of this type by GE company, devise can realize poor oil firing fuel injection equipment (FIE) for engine engineer applied, such as: some engine adopt dicyclo cavity combustion chamber grading combustion technology; The center grading combustion technology etc. that some engine adopts.
Due to advantages such as compact conformation, subregion poor oil firing control NOx effect are better, center grading combustion technology is adopted to be the trend of low emission combustor development.But existing grading combustion technology, not can solve between subregion interact, the low inferior problem of efficiency of combustion near classification point.And three grades interact at fuel oil jet segment for oil firing, oil gas allotment will meet combustion requirements and the emission request realization comparatively difficulty of each combustion zone simultaneously.
Summary of the invention
The technical problem to be solved in the present invention is the discharge capacity of CO and UHC under 30% thrust rating of reduction ICAO regulation, and the problem that the 30% thrust rating efficiency of combustion occurred in solution fractional combustion is on the low side, can not weaken the NOx emission under high-power state simultaneously.
According to a first aspect of the invention, provide a kind of combustion chamber fuel oil to spray and mixing arrangement, it is characterized in that, described device comprises pre-combustion grade, intergrade and main combustion stage, described intergrade around described pre-combustion grade, described main combustion stage around described intergrade, wherein:
Described pre-combustion grade comprises swirl atomizer, around the one-level cyclone of described swirl atomizer, around the Venturi tube of described one-level cyclone and the second cyclone around described Venturi tube;
Described intergrade comprises middle fuel feeding path, lining, around the intergrade cyclone of described lining and the sleeve around described intergrade cyclone, described middle fuel feeding path supplies 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 the main combustion stage outer wall around 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, the end of described main combustion stage inwall is provided with at least one Cooling Holes, upstream air is entered described cavity and is impacted the end of described sleeve by described Cooling Holes, cools the end of described main combustion stage inwall and the end of described sleeve thus.
Wherein, described main fuel feeding path and/or middle fuel feeding path are provided with nozzle.
Wherein, described nozzle adopts pressure atomization structure or pneumatic nebulization structure.
Wherein, described nozzle comprises at least one spray site or adopts domain liquid film to spray.
Wherein, described pre-combustion grade, described intergrade and described main combustion stage inwall form an entirety by welding and/or monoblock cast, and coordinate with described main combustion stage cyclone axial float.
According to a second aspect of the invention, provide a kind of combustion chamber, comprise aforesaid combustion chamber fuel oil and spray and mixing arrangement.
Beneficial effect of the present invention:
1. simple and compact for structure, have employed level Four cyclone, three combustion zone independent oil supplies, fuel-air matching is very convenient, and fuel oil regulates freely.
2. according to the demand of engine different capacity, 3 grades of independent partitions fuel feeding such as pre-combustion grade, intergrade, main combustion stage of radially having arranged from center.Wherein, main combustion stage and intergrade adopt direct-injection type multi-point fuel injection or domain liquid film injection design respectively, and fuel oil sprays in the swirling eddy of cyclone generation, and atomizing effect is good.
3. interact between three grades of fuel feeding less, avoid producing near combustion chamber classification status point the air-fuel mixture district that local is unfavorable for burning, can compared with the contradiction solving classification status point NOx emission and CO, UHC discharge performance faced in grading combustion technology in wide operating range well.
Accompanying drawing explanation
Describe in detail according to a preferred embodiment of the invention below in conjunction with accompanying drawing, wherein:
Fig. 1 shows and sprays the sectional view with the preferred embodiment of mixing arrangement according to combustion chamber of the present invention fuel oil;
Fig. 2 shows combustion chamber fuel oil in Fig. 1 and sprays the assembling schematic diagram with mixing arrangement.
Description of reference numerals
1 mating surface 2 mating surface
3 main combustion stage cyclone 4 walls
The main fuel feeding path of 5 wall 6
The middle fuel feeding path of 7 nozzle 8
9 intergrade cyclone 10 nozzles
11 sleeve 12 swirl atomizers
13 Venturi tube 14 one-level cyclones
15 second cyclone 16 spray orifices
17 lining 18 main combustion stage outer walls
19 main combustion stage inwall 20 Cooling Holes
21 end 22 main combustion stage passages
Detailed description of the invention
First some terms of the art are introduced, wherein:
Cyclone: make gas generation tangential velocity carry out the device of rotational flow;
Venturi tube: accelerate the annular tubular structure that air-flow prevents tempering, fuel oil liquid mist is beaten form liquid film assisted atomization on Venturi tube wall;
Fractional combustion: refer to fuel oil, the mixed combustion of air subregion, burn in zones of different;
Nozzle: the device of fuel-oil atmozation;
Fuel-oil atmozation: utilize nozzle that liquid fuel is become the process of oil droplet group;
Stoichiometric ratio: fuel oil and air are according to the pro rate of burning completely;
Oil-poor: fuel ratio is less than stoichiometric ratio mixed proportion, i.e. air excess, and fuel oil is on the low side;
Premixed combustion: fuel oil and air carry out mixed uniformly combustion system before combustion;
Diffusion combustion: fuel oil sprays into combustion zone and is atomized mixing and contacts with air and the combustion system carrying out chemical reaction.
Shown in Fig. 1 and Fig. 2, spray according to combustion chamber of the present invention fuel oil and adopt that the fuel oil be made up of fuel nozzle system and cyclone sprays, air-fuel mixture system with mixing arrangement, and be provided with 3 grades of independent partitions fuel feeding according to the arrangement of center classification.Whole device is connected by the group section and splash pan installing mating surface 1 and mating surface 2 and combustion chamber flame drum head end wall.
Fig. 1 shows the sectional view of whole device centrally axis.Combustion chamber fuel oil sprays and comprises pre-combustion grade, intergrade and main combustion stage with mixing arrangement, and intergrade is around pre-combustion grade, and main combustion stage is around intergrade.
Pre-combustion grade adopts eddy flow cup structure air atomizer spray nozzle, comprises swirl atomizer 12, the one-level cyclone 14 around swirl atomizer 12, the Venturi tube 13 around one-level cyclone 14 and the second cyclone 15 around Venturi tube 13.Fuel oil sprays from the spray orifice 16 of swirl atomizer 12 and forms spray cone and beat on Venturi tube 13 wall, and is atomized under the swirling eddy shear action of the one-level cyclone 14 of inner side and the second cyclone 15 in outside and sprays into combustion chamber.
Intergrade comprises middle fuel feeding path 8, lining 17, the intergrade cyclone 9 around lining 17 and the sleeve 11 around intergrade cyclone 9, middle fuel feeding path 8 is connected with fuel system, supplies fuel to the space of intergrade cyclone 9 downstream between sleeve 11 and lining 17.Fuel oil sprays in the passage that formed between the wall of lining 17 and sleeve 11 from nozzle 10, under the swirling eddy effect going out interruption-forming of intergrade cyclone 9, atomization sprays into combustion chamber.The multi-point injection that fuel system adopts circumferential Central Symmetry to arrange or employing domain liquid film spray.
Main combustion stage comprises main fuel feeding path 6, main combustion stage inwall 19, the main combustion stage cyclone 3 around main combustion stage inwall 19 and the main combustion stage outer wall 18 around main combustion stage cyclone 3, main combustion stage passage 22 is formed between main combustion stage inwall 19 and main combustion stage outer wall 18, main fuel feeding path 6 is connected with fuel system, supplies fuel in the main combustion stage passage 22 in main combustion stage cyclone 3 downstream.Fuel oil sprays the multi-point injection adopting circumferential Central Symmetry to arrange or the nozzle 7 adopting domain liquid film to spray, and under the swirling eddy effect that the fuel oil sprayed into goes out interruption-forming at main combustion stage cyclone 3, atomization sprays into combustion chamber.
The end 20 of main combustion stage inwall 19 is connected with the end 21 of sleeve 11 and forms a cavity, the end 20 of main combustion stage inwall 19 is provided with at least one Cooling Holes 20, upstream air is entered cavity and is carried out the end 21 of impingement sleeve 11 by Cooling Holes 20, cool the end 20 of main combustion stage inwall 19 and the end 21 of sleeve 11 thus, that is, the group section between main combustion stage and intergrade is cooled.
In certain 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, the cyclone at different levels of the pre-combustion grade of fuel injection equipment (FIE), intergrade, main combustion stage is connected group section and main combustion stage inwall is designed to adopt welding and/or monoblock cast to form an entirety with assembly.This component integration can centrally move and carries out dismounting in line direction, and coordinate with main combustion stage cyclone axial float, assemblage gap mating surface is between wall 5 and the wall 4 of outermost main combustion stage cyclone 3.In figure, dashed region is can the component integration of dismounting, during assembling by the slope outer wall of wall 5 centrally line to slide axially from left to right importing.
The present invention is according to the demand of engine different capacity, and radially arranged 3 grades of independent partitions fuel feeding such as pre-combustion grade, intergrade, main combustion stage in direction.Interact between 3 grades of fuel feeding less, avoid producing near combustion chamber classification status point the air-fuel mixture district that local is unfavorable for burning, can compared with the contradiction well solving classification status point NOx emission and CO, UHC discharge performance faced in grading combustion technology in wide operating range.
Described in the present invention, concrete case study on implementation is only better case study on implementation of the present invention, is not used for limiting practical range of the present invention.Namely all equivalences done according to the content of the present patent application the scope of the claims change and modify, and all belong to protection scope of the present invention.
Claims (6)
1. combustion chamber fuel oil spray and a mixing arrangement, it is characterized in that, described device comprises pre-combustion grade, intergrade and main combustion stage, described intergrade around described pre-combustion grade, described main combustion stage around described intergrade, wherein:
Described pre-combustion grade comprises swirl atomizer (12), one-level cyclone (14), the Venturi tube (13) around described one-level cyclone (14) and the second cyclone (15) around described Venturi tube (13) around described swirl atomizer (12);
Described intergrade comprise middle fuel feeding path (8), lining (17), around described lining (17) intergrade cyclone (9) and be connected to the sleeve (11) of described intergrade cyclone (9) rear end, described middle fuel feeding path (8) supplies fuel to described intergrade cyclone (9) downstream and is positioned at space between described sleeve (11) and described lining (17);
Described main combustion stage comprise main fuel feeding path (6), main combustion stage inwall (19), around described main combustion stage inwall (19) main combustion stage cyclone (3) and be connected to the main combustion stage outer wall (18) of described main combustion stage cyclone (3) rear end, described main fuel feeding path (6) supplies fuel to described main combustion stage cyclone (3) downstream and is positioned at 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, the end of described main combustion stage inwall (19) is provided with at least one Cooling Holes (20), upstream air is entered described cavity and is impacted the end (21) of described sleeve (11) by described Cooling Holes (20), cools the end of described main combustion stage inwall (19) and the end (21) of described sleeve (11) thus.
2. combustion chamber according to claim 1 fuel oil sprays and mixing arrangement, and 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. the combustion chamber fuel oil according to any one of claim 1 to 4 sprays and mixing arrangement, it is characterized in that, described pre-combustion grade, described intergrade and described main combustion stage inwall (19) form an entirety by welding or monoblock cast, and coordinate with described main combustion stage cyclone (3) axial float.
6. a combustion chamber, is characterized in that, the combustion chamber fuel oil comprised according to any one of claim 1 to 5 sprays and mixing arrangement.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210306279.7A CN103629696B (en) | 2012-08-24 | 2012-08-24 | A kind of combustion chamber fuel oil sprays and mixing arrangement and combustion chamber thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210306279.7A CN103629696B (en) | 2012-08-24 | 2012-08-24 | A kind of combustion chamber fuel oil sprays and mixing arrangement and combustion chamber thereof |
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| Publication Number | Publication Date |
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| CN103629696A CN103629696A (en) | 2014-03-12 |
| CN103629696B true CN103629696B (en) | 2015-09-09 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240847A (en) * | 2015-11-19 | 2016-01-13 | 哈尔滨东安发动机（集团）有限公司 | Anti-backfire structure of combustion chamber |
| CN108204604B (en) * | 2018-03-13 | 2023-05-23 | 中国航空发动机研究院 | Combustion chamber multi-stage swirl nozzle with periodically varying outlet structure |
| CN111425887B (en) * | 2019-01-10 | 2021-10-15 | 中国航发商用航空发动机有限责任公司 | Gas turbine combustion chamber and gas turbine |
| CN110131065A (en) * | 2019-05-15 | 2019-08-16 | 燕山大学 | A kind of novel tangential combined internal combustion engine cylinder based on eddy flow secondary injection |
| CN111006243B (en) * | 2019-12-03 | 2021-03-30 | 哈尔滨工程大学 | Anti-backfire fuel flash evaporation and rotational flow integrated nozzle |
| CN113137638B (en) * | 2021-04-29 | 2022-07-05 | 中国航发湖南动力机械研究所 | Double-stage axial swirler with concave cavity for strengthening oil-gas mixing and aero-engine |
| CN113154449B (en) * | 2021-05-06 | 2022-05-31 | 中国航发湖南动力机械研究所 | Low-pollution combustion chamber for efficient mixing of oil and gas |
| CN118129187B (en) * | 2024-05-08 | 2024-07-12 | 四川鸿鹏航空航天装备智能制造有限公司 | Fuel nozzle of aeroengine combustion chamber |
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| JP2004101105A (en) * | 2002-09-11 | 2004-04-02 | Mitsubishi Heavy Ind Ltd | Combustor |
| CN102032598A (en) * | 2010-12-08 | 2011-04-27 | 北京航空航天大学 | Circumferentially graded low-pollution combustion chamber with multiple middle spiral-flow flame stabilizing stages |
| KR20120078636A (en) * | 2010-12-30 | 2012-07-10 | 누보 피그노네 에스피에이 | Sculpted trailing edge swirler combustion premixer and method |
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2012
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004101105A (en) * | 2002-09-11 | 2004-04-02 | Mitsubishi Heavy Ind Ltd | Combustor |
| CN102032598A (en) * | 2010-12-08 | 2011-04-27 | 北京航空航天大学 | Circumferentially graded low-pollution combustion chamber with multiple middle spiral-flow flame stabilizing stages |
| KR20120078636A (en) * | 2010-12-30 | 2012-07-10 | 누보 피그노네 에스피에이 | Sculpted trailing edge swirler combustion premixer and method |
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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. |
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