CN115597089B - Cyclone assembly, multi-point staged lean direct injection combustor and control method thereof - Google Patents
Cyclone assembly, multi-point staged lean direct injection combustor and control method thereof Download PDFInfo
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- CN115597089B CN115597089B CN202110784890.XA CN202110784890A CN115597089B CN 115597089 B CN115597089 B CN 115597089B CN 202110784890 A CN202110784890 A CN 202110784890A CN 115597089 B CN115597089 B CN 115597089B
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- fuel injection
- fuel
- swirler
- combustion chamber
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- 238000002347 injection Methods 0.000 title claims abstract description 100
- 239000007924 injection Substances 0.000 title claims abstract description 100
- 238000000034 method Methods 0.000 title claims abstract description 18
- 239000000446 fuel Substances 0.000 claims abstract description 131
- 238000002485 combustion reaction Methods 0.000 claims abstract description 74
- 230000000712 assembly Effects 0.000 claims abstract description 44
- 238000000429 assembly Methods 0.000 claims abstract description 44
- 238000000889 atomisation Methods 0.000 claims abstract description 28
- 239000003595 mist Substances 0.000 claims description 9
- 230000008520 organization Effects 0.000 claims description 4
- 230000008602 contraction Effects 0.000 claims description 3
- 239000003921 oil Substances 0.000 description 12
- 239000007788 liquid Substances 0.000 description 4
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 239000003344 environmental pollutant Substances 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- XURIQWBLYMJSLS-UHFFFAOYSA-N 1,4,7,10-tetrazacyclododecan-2-one Chemical compound O=C1CNCCNCCNCCN1 XURIQWBLYMJSLS-UHFFFAOYSA-N 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
- 230000003245 working effect Effects 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The cyclone component comprises a venturi tube and a fuel injection tube, wherein the fuel injection tube comprises a primary fuel injection flow passage and a secondary fuel injection flow passage, the primary fuel injection flow passage and the secondary fuel injection flow passage face towards the constriction section wall and the sudden expansion section of the venturi tube respectively, different atomization modes of injected fuel are realized, and fuel injection of the primary fuel injection flow passage and the secondary fuel injection flow passage is controlled independently. A multi-point staged lean direct injection combustor includes a combustor head including a plurality of swirler assemblies distributed about a combustor axis. A control method for multi-point staged lean direct injection combustion involves a combustion chamber having a plurality of swirler assemblies providing at least two different fuel atomization modes, with separate control of the individual swirler assembly atomization modes and fuel injection to the swirler assemblies at different locations.
Description
Technical Field
The invention belongs to the field of aero-engines, in particular to a cyclone component, a multi-point graded lean oil direct injection combustion chamber and a control method thereof.
Background
With the continuous release of stricter emission regulations and the increasing public environmental awareness, how to reduce pollutant emissions and improve combustion efficiency is an important research topic in the field of aeroengines. At present, in order to reduce the emission of nitrogen oxides and simultaneously control the concentration of carbon monoxide and unburned hydrocarbons in combustion tail gas, lean premixed pre-evaporation, rich quenching lean combustion and other low-emission combustion forms are widely studied and applied in the field of aeroengines. In the technical schemes, the lean oil direct injection technology forms flame by directly injecting fuel oil into a combustion chamber and mixing the fuel oil with air for a very short time, and the combustion organization mode reduces pollutant emission and simultaneously reduces the occurrence risks of spontaneous combustion, tempering and unstable combustion, thereby realizing more stable working effect in a high-pressure than aero-engine.
However, the power change of the combustion chamber of the existing lean oil direct injection combustion chamber under different working conditions is mainly realized by adjusting the opening and closing of different cyclone components, the mode of adjusting the fuel injection atomization is single, the equivalence ratio and the fuel distribution of the combustion chamber can not be flexibly adjusted when the combustion conditions are met, and the pollution emission is further reduced and the stable combustion under different powers is not maintained.
Disclosure of Invention
It is an object of the present invention to provide a swirler assembly for an engine combustion chamber that enables different modes of fuel atomization and staged combustion at a single assembly.
A swirler assembly includes a venturi and a fuel injection tube.
The venturi tube comprises a cylindrical section, a contraction section and a sudden expansion section, and the fuel injection tube comprises a primary fuel injection flow passage and a secondary fuel injection flow passage.
The fuel injection pipe is arranged in the venturi tube, and an annular flow passage formed between the fuel injection pipe and the venturi tube is provided with an air cyclone. The injection port of the primary fuel injection runner faces the wall surface of the contraction section, the injection port of the secondary fuel injection runner faces the abrupt expansion section, and the primary fuel injection runner and the secondary fuel injection runner can respectively perform independent fuel injection according to control instructions.
Optionally, the number of air swirler vanes of the swirler assembly is 6-20, and the angle value is 45 ° -80 °.
Optionally, the primary fuel injection runner and the secondary fuel injection runner of the swirler assembly are respectively provided with fuel swirlers, the number of blades of the fuel swirlers is 3-12, and the angle value is 35-80 degrees.
The present invention also provides a multi-point staged lean direct injection combustor comprising a combustor head including a plurality of said swirler assemblies distributed about an engine axis.
According to one embodiment, the swirler assemblies of the multi-point staged lean direct injection combustion chamber are annularly arranged in the form of a plurality of concentric circles.
According to another embodiment, the swirler assemblies of the multi-point staged lean direct injection combustor are aligned on the concentric circle with a closer distance between the swirler assemblies on adjacent concentric circles of the engine combustor.
According to another embodiment, the swirler assemblies of the multi-point staged lean direct injection combustor are arranged in staggered intervals on the concentric circle, with a distance between the swirler assemblies on adjacent concentric circles of the engine combustor being relatively large.
Optionally, the number of swirler assemblies of the multi-point staged lean direct injection combustor is 12 to 36. The number of swirler assemblies depends on the design power and design size of the multi-point staged lean direct injection combustor.
The invention also provides a control method of the multi-point graded lean oil direct injection combustion, which is used for an annular combustion chamber, the combustion chamber related by the method comprises a combustion chamber head part, a plurality of swirler assemblies are arranged in the combustion chamber head part, the swirler assemblies at least provide two fuel atomization modes, each atomization mode forms an oil mist field with different fuel distribution characteristics, further, unburned components with different local equivalent ratio distribution are formed, and finally, flames with different shapes and combustion characteristics are formed in the combustion chamber.
According to one embodiment, the control method controls the fuel supply amounts of the at least two fuel atomization modes respectively for a single cyclone assembly so as to adjust the fuel flow of different fuel atomization modes, and further control the participation degree of the oil mist field formed by the different fuel atomization modes in the combustion process.
According to another embodiment, the control method involves a combustion chamber wherein the swirler assemblies are circumferentially arranged evenly or at intervals to form a combustion pattern within the annular combustion chamber. According to the control method, for different working conditions, the staged combustion with spatial distribution is realized in the annular combustion chamber by adjusting different fuel atomization modes and fuel flows of the cyclone assemblies at different annular radius positions.
The invention provides a swirler assembly and a multi-point graded lean oil direct injection combustion chamber and a control method provided with the swirler assembly aiming at an annular combustion chamber of an aeroengine and a gas turbine with high pressure ratio, and the beneficial effects are as follows:
1. The single cyclone assembly can provide at least two different fuel atomization modes, so that the regulation of the combustion organization form is more flexible;
2. The annular combustion chamber can respectively control fuel injection of the swirler assemblies in different areas according to different working conditions so as to achieve the purpose of changing fuel distribution and combustion characteristics;
3. By adjusting the fuel atomization pattern of the individual swirler assemblies and the fuel flow rates of the different regions of the swirler assemblies, a more stable, less polluting staged combustion can be achieved.
Drawings
FIG. 1 is a cross-sectional view of a cyclone assembly;
FIG. 2A is a schematic illustration of an arrangement of swirler assemblies in a combustion chamber;
FIG. 2B is a schematic illustration of another arrangement of swirler assemblies in a combustion chamber.
Reference numerals meaning:
1-a cyclone assembly; 2-a venturi; 21-a venturi cylindrical section; 22-venturi constriction; 23-venturi abrupt expansion section; 3-fuel injection pipe; 31-primary fuel injection flow path; 32-secondary fuel injection flow passages; 33 first stage fuel injection ports; 34-secondary fuel injection ports; 35 a fuel swirler; 36-a fuel swirler; 4-an air cyclone; 5-swirling air; 61-first-stage injection of fuel; 62-an oil mist field formed by primary injection of fuel; 7-secondary injection of fuel; 8-cyclone assembly nozzle.
The drawings are provided to illustrate the invention in more detail, and are not intended to limit the embodiments of the invention to the exact scale and to precisely illustrate the complete equipment and system structure.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. The following description is provided in detail to fully explain the principles and technical aspects of the present invention and is not intended to limit the invention. For convenience of description, the drawings include only some, but not all, structures related to the present invention.
A swirler assembly for an aircraft engine combustion chamber as shown in fig. 1, the swirler assembly 1 comprises a venturi 2 and a fuel injection tube 3, wherein the venturi 2 is divided into a cylindrical section 21, a converging section 22 and a converging section 23. The air swirler 4 is arranged in an annular flow passage between the venturi cylindrical section 21 and the fuel injection pipe 3. The fuel injection pipe 3 includes an annular primary fuel injection flow passage 31, a secondary fuel injection flow passage 32 in which fuel swirlers 35, 36 are provided, respectively. The swirler assembly 1 is capable of fuel injection in two different modes of atomization: the primary fuel injection port 33 faces the pipe wall of the venturi constriction section 22, the primary injection fuel 61 is sprayed from the primary fuel injection port 33 through the fuel cyclone 35, a liquid film is formed on the wall of the constriction section 22, the liquid film is pre-film atomized under the action of the cyclone air 5, then secondary atomization and crushing are carried out when the liquid film flows from the constriction section 22 to the sudden expansion section 23 to form an oil mist field 62, and the primary injection fuel 61 can firstly form the liquid film on the wall of the constriction section 22 without being directly blown into the sudden expansion section 23 by the cyclone air 5 by designing the distance between the primary fuel injection port 33 and the pipe wall of the venturi constriction section 22; the secondary fuel injection ports 34 face the sudden expansion section 23, and the secondary injection fuel 7 is directly injected into the sudden expansion section 23 from the secondary fuel injection ports 34 through the fuel swirler 36 and is mixed with the swirling air 5. The opening and closing of the primary fuel injection flow channel 31 and the secondary fuel injection flow channel 32 and the fuel flow rate can be independently and respectively controlled according to working conditions, so that the swirler assembly 1 can respectively inject the fuels in two different atomization modes or inject the mixed oil mist fields in which the fuels in the two atomization modes are mixed in different proportions. The fuel with different atomization modes leaves the nozzle 8 of the cyclone assembly to participate in the combustion organization of the engine, so that the combustion modes with different flame characteristics are formed.
The number of blades of the air swirler 4 is 6, and the angle value is 45 degrees. The number of vanes of the fuel swirlers 35, 36 is 3, and the angle value is 35 °.
In one embodiment, the ratio of the fuel flow injected from the primary fuel injection ports 33 to the secondary fuel injection ports 34 to the total injection flow of the entire swirler assembly 1 is 100%/0, 50%/50%,0/100%, respectively, depending on the operating conditions.
In another embodiment, the number of blades of the air swirler 4 is 20, and the angle value is 80 °. The number of vanes of the fuel swirlers 35, 36 is 12, and the angle value is 80 °.
As shown in fig. 2A and 2B, 36 swirler assemblies 1 are distributed in the combustion chamber around the engine axis in concentric circles R1, R2, R3 of different radii, each concentric circle being provided with 12 swirler assemblies 1. The swirler assemblies 1 in the combustion chamber shown in fig. 2A are arranged at intervals in a manner of being offset from each other in the radial direction, and the swirler assemblies 1 in the combustion chamber shown in fig. 2B are arranged in a straight line in the radial direction.
The arrangement of the swirler assemblies in the combustion chamber is not limited to the form disclosed in fig. 2A and 2B. In another embodiment, there are 6 on R1 swirler assemblies 1, 12 on R2 swirler assemblies 1, and 18 on R3 swirler assemblies 1.
In one embodiment, during operation of the combustion chamber, the swirler assembly 1 on R1 injects fuel from only the primary fuel injection ports 33, the primary fuel injection ports 33 of the swirler assembly 1 on R2 inject fuel at a 1:1 fuel flow rate simultaneously with the secondary fuel injection ports 34, and the swirler assembly 1 on R3 injects fuel from only the secondary fuel injection ports 34.
In another embodiment, the swirler assemblies 1 on R1, R2, R3 each have only one stage of fuel injection ports 33 for injecting fuel at the maximum flow rate permitted by the fuel injection tube 3 during operation of the combustion chamber.
In another embodiment, the swirler assembly 1 on each of the combustion chamber working chambers, R1, R2, has only one primary fuel injection port 33 injecting fuel at the maximum flow rate permitted by the fuel injection tube 3, and the secondary fuel injection port 34 of the swirler assembly 1 on R3 injects fuel at the maximum flow rate permitted by the fuel injection tube 3.
In a further embodiment, 12 swirler assemblies 1 are arranged in the combustion chamber to accommodate smaller volume and lower power engine design requirements.
In a further embodiment, the 12 swirler assemblies 1 arranged in the burner are distributed on two concentric circles of different radii.
A control method of multi-point staged lean direct injection combustion is used for an annular combustion chamber, the annular combustion chamber comprises a combustion chamber head, a plurality of swirler assemblies 1 are arranged in the annular combustion chamber, the swirler assemblies 1 are used for injecting fuel from different fuel ports in different injection modes and mixing with air in different modes at different positions, at least two different fuel atomization modes are provided, each atomization mode forms an oil mist field with different fuel distribution characteristics, and further, unburned components with different local equivalence ratio distribution are formed, and finally flames with different shapes and combustion characteristics are formed in the combustion chamber.
According to one embodiment, the control method controls the fuel supply amounts of the two fuel atomization modes respectively for the single cyclone assembly 1 so as to adjust the fuel flow of different fuel atomization modes, and further control the participation degree of the oil mist field formed by the different atomization modes in the combustion process.
According to another embodiment, the control method involves a combustion chamber wherein the swirler assemblies 1 are circumferentially uniform as in fig. 2B or spaced apart as in fig. 2A to form a combustion pattern within the annular combustion chamber. According to the control method, for different working conditions, the staged combustion with spatial distribution is realized in the annular combustion chamber by adjusting different fuel atomization modes and fuel flows of the swirler assembly 1 at the positions of different annular radiuses R1, R2 and R3.
The present invention has been described above with reference to the embodiments, but the scope of the present invention is not limited thereto. Various modifications may be made without departing from the scope of the invention, equivalent structures may be substituted for elements in the systems and devices described herein, and equivalent steps or operations may be substituted for the methods described herein.
Claims (11)
1. A cyclone assembly comprising:
a venturi tube comprising a cylindrical section, a converging section and a converging section;
the fuel injection pipe comprises a primary fuel injection flow passage and a secondary fuel injection flow passage;
the fuel injection pipe is arranged in the venturi tube, an annular air flow passage is formed between the fuel injection pipe and the venturi tube, and an air swirler is arranged in the air flow passage at a position corresponding to the cylindrical section;
the first-stage fuel injection runner injection port faces the wall surface of the contraction section;
The jet orifice of the secondary fuel jet runner faces the sudden expansion section;
the primary fuel injection runner and the secondary fuel injection runner are used for respectively carrying out fuel injection according to control instructions.
2. The cyclone assembly according to claim 1, wherein the air cyclone has an angle of 45 ° -80 ° and a number of blades of 6-20 °.
3. The swirler assembly as claimed in claim 1, wherein the primary fuel injection runner and the secondary fuel injection runner of the fuel injection pipe further comprise a fuel swirler having an angle value of 35 ° -80 ° and a number of vanes of 3-12.
4. A multi-point staged lean direct injection combustor comprising a combustor head comprising a plurality of swirler assemblies distributed about an engine axis, wherein the swirler assemblies are the swirler assemblies of any one of claims 1 to 3.
5. The multi-point staged lean direct injection combustor of claim 4, wherein the plurality of swirler assemblies are annularly arranged in a plurality of concentric circles.
6. The multi-point staged lean direct injection combustor of claim 5, wherein the plurality of swirler assemblies are aligned radially of the concentric circles.
7. The multi-point staged lean direct injection combustor of claim 5, wherein the plurality of swirler assemblies are arranged in a staggered spacing from each other in a radial direction of the concentric circles.
8. The multi-point staged lean direct injection combustor as defined in claim 4, wherein the number of swirler assemblies disposed in the combustor is 12-36.
9. A control method of multi-point staged lean direct injection combustion for an annular combustion chamber including a combustion chamber head including a plurality of swirler assemblies, characterized by: providing at least two fuel atomization modes on a single swirler assembly, respectively forming oil mist fields with different fuel distribution characteristics, wherein the oil mist fields form unburned components with different local equivalent ratio distribution, and finally, flames with different shapes and combustion characteristics are formed in a combustion chamber;
a cyclone assembly according to any one of claims 1 to 3.
10. The control method of claim 9, further controlling respective fuel supplies in the at least two fuel atomization modes for a single swirler assembly to adjust fuel flow rates for different fuel atomization modes.
11. A control method as claimed in claim 10, characterized in that the combustion organization in the annular combustion chamber is formed by arranging the swirler assemblies uniformly or at intervals in the circumferential direction of the annular combustion chamber, and that the staged combustion with spatial distribution is formed in the annular combustion chamber by adjusting different fuel atomization patterns and fuel flows of the swirler assemblies at different annular radius positions for different operating conditions.
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CN202110784890.XA CN115597089B (en) | 2021-07-12 | 2021-07-12 | Cyclone assembly, multi-point staged lean direct injection combustor and control method thereof |
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CN202110784890.XA CN115597089B (en) | 2021-07-12 | 2021-07-12 | Cyclone assembly, multi-point staged lean direct injection combustor and control method thereof |
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Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103123122A (en) * | 2012-12-31 | 2013-05-29 | 南京航空航天大学 | Lean oil pre-mixing and pre-evaporating low-pollution combustion chamber capable of ejecting main-stage fuel oil directly |
CN103256633A (en) * | 2012-02-16 | 2013-08-21 | 中国科学院工程热物理研究所 | Low-pollution combustion chamber adopting fuel-grading and three-stage cyclone air inlet |
CN109737451A (en) * | 2019-01-23 | 2019-05-10 | 南方科技大学 | A kind of fuel gas is prewhirled the low emission combustor of injection |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
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JP4959524B2 (en) * | 2007-11-29 | 2012-06-27 | 三菱重工業株式会社 | Burning burner |
US11149941B2 (en) * | 2018-12-14 | 2021-10-19 | Delavan Inc. | Multipoint fuel injection for radial in-flow swirl premix gas fuel injectors |
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- 2021-07-12 CN CN202110784890.XA patent/CN115597089B/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103256633A (en) * | 2012-02-16 | 2013-08-21 | 中国科学院工程热物理研究所 | Low-pollution combustion chamber adopting fuel-grading and three-stage cyclone air inlet |
CN103123122A (en) * | 2012-12-31 | 2013-05-29 | 南京航空航天大学 | Lean oil pre-mixing and pre-evaporating low-pollution combustion chamber capable of ejecting main-stage fuel oil directly |
CN109737451A (en) * | 2019-01-23 | 2019-05-10 | 南方科技大学 | A kind of fuel gas is prewhirled the low emission combustor of injection |
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