CN115597089A - Swirler assembly, multipoint staged lean oil direct injection combustion chamber and control method thereof - Google Patents
Swirler assembly, multipoint staged lean oil direct injection combustion chamber and control method thereof Download PDFInfo
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- CN115597089A CN115597089A CN202110784890.XA CN202110784890A CN115597089A CN 115597089 A CN115597089 A CN 115597089A CN 202110784890 A CN202110784890 A CN 202110784890A CN 115597089 A CN115597089 A CN 115597089A
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- swirler
- fuel
- fuel injection
- combustor
- combustion chamber
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- 238000002347 injection Methods 0.000 title claims abstract description 98
- 239000007924 injection Substances 0.000 title claims abstract description 98
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 70
- 238000000034 method Methods 0.000 title claims abstract description 18
- 239000000446 fuel Substances 0.000 claims abstract description 126
- 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
- 230000008602 contraction Effects 0.000 claims abstract description 9
- 238000009826 distribution Methods 0.000 claims description 11
- 239000003595 mist Substances 0.000 claims description 9
- 239000003921 oil Substances 0.000 description 12
- 239000007788 liquid Substances 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 239000003344 environmental pollutant Substances 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 230000008520 organization Effects 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 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
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
Images
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
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- 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 swirler assembly 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 which respectively face to the contraction section wall and the sudden expansion section of the Venturi tube to realize different atomization modes of injected fuel, and the fuel injection of the primary fuel injection flow passage and the fuel injection of the secondary fuel injection flow passage are respectively and independently controlled. A multi-point staged lean direct injection combustor includes a combustor head including a plurality of swirler assemblies distributed about a combustor axis. A method for controlling multi-point staged lean direct injection combustion involves a combustion chamber having a plurality of swirler assemblies providing at least two different fuel atomization patterns, and separately controlling the atomization patterns of a single swirler assembly and the fuel injection of the swirler assembly at different positions.
Description
Technical Field
The invention belongs to the field of aeroengines, and particularly relates to a swirler assembly, a multipoint graded lean oil direct injection combustion chamber and a control method thereof.
Background
With the continuous emergence of stricter emission regulations and increasingly stronger public environmental awareness, how to reduce pollutant emission and improve combustion efficiency becomes a more 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, low-emission combustion forms such as lean premixed pre-evaporation and rich quenched lean combustion are widely researched and applied in the field of aeroengines. In the technical scheme, 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 the emission of pollutants, reduces the occurrence risks of spontaneous combustion, backfire and unstable combustion and realizes a more stable working effect in a high-pressure ratio aeroengine.
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 swirler assemblies, the mode of adjusting fuel injection atomization is single, the equivalence ratio and the fuel distribution of the combustion chamber can not be flexibly adjusted when different combustion working conditions are met, and the further reduction of pollutant emission and the maintenance of stable combustion under different powers are not facilitated.
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 includes a cylindrical section, a converging section and a diverging section, and the fuel injection tube includes a primary fuel injection flow passage and a secondary fuel injection flow passage.
The fuel injection pipe is arranged in the venturi pipe, and an annular flow passage formed between the fuel injection pipe and the venturi pipe is provided with an air swirler. The injection port of the first-stage fuel injection flow passage faces the wall surface of the contraction section, the injection port of the second-stage fuel injection flow passage faces the sudden expansion section, and the first-stage fuel injection flow passage and the second-stage fuel injection flow passage can respectively carry out independent fuel injection according to a control command.
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 a fuel swirler, the number of vanes of the fuel swirler is 3-12, and the angle value is 35-80 °.
The invention also provides a multipoint staged lean direct injection combustor comprising a combustor head comprising a plurality of said swirler assemblies distributed about an engine axis.
According to one embodiment, the swirler assembly of the multi-point staged lean direct injection combustor is annularly arranged in the form of a plurality of concentric circles.
According to another embodiment, said swirler assemblies of said multi-point staged lean direct injection combustion chamber are aligned on said concentric circles with a closer distance between said swirler assemblies on adjacent said concentric circles of said engine combustion chamber.
According to another embodiment, said swirler assemblies of said multi-point staged lean direct injection combustor are arranged in a mutually staggered spacing on said concentric circles, with a greater distance between said swirler assemblies on adjacent ones of said concentric circles of said engine combustor.
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 multipoint staged lean direct injection combustion, which is used for an annular combustion chamber and relates to the combustion chamber comprising a combustion chamber head part, wherein 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 forms unburned components with different local equivalence ratio distribution, and finally forms flames with different shapes and combustion characteristics in the combustion chamber.
According to one embodiment, the control method controls the fuel supply amount in each of the at least two fuel atomization modes for a single swirler assembly, so as to adjust the fuel flow rate in different fuel atomization modes, and further control the participation degree of the oil mist fields 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 are circumferentially uniformly or spaced to form a combustion pattern within the annular combustion chamber. According to the control method, for different working conditions, staged combustion with spatial distribution is realized in the annular combustion chamber by adjusting different fuel atomization modes and fuel flow rates of the swirler assemblies at different annular radius positions.
The invention provides a swirler assembly, a multipoint graded lean oil direct injection combustion chamber with the swirler assembly and a control method aiming at an annular combustion chamber of an aircraft engine and a gas turbine with a high pressure ratio, and the following beneficial effects are realized:
1. a single swirler assembly can provide at least two different fuel atomization modes, so that the adjustment of the combustion organization form is more flexible;
2. the annular combustion chamber can respectively control the fuel injection of the swirler assemblies in different areas according to different working conditions so as to achieve the purpose of changing the fuel distribution and the combustion characteristics;
3. by adjusting the fuel atomization mode of a single swirler assembly and the fuel flow of swirler assemblies in different areas, more stable and lower-pollution staged combustion can be achieved.
Drawings
FIG. 1 is a cross-sectional view of a swirler assembly;
FIG. 2A is a schematic illustration of one arrangement of swirler assemblies in a combustor;
FIG. 2B is a schematic view of another arrangement of swirler assemblies in a combustor.
The reference numerals mean:
1-a swirler assembly; 2-a venturi tube; 21-a cylindrical section of a venturi tube; 22-a venturi constriction section; 23-venturi sudden expansion section; 3-a fuel injection pipe; 31-primary fuel injection flow path; 32-secondary fuel injection flow path; 33 primary fuel injection ports; 34-secondary fuel injection ports; 35 a fuel swirler; 36-a fuel swirler; 4-an air swirler; 5-swirling air; 61-primary injection fuel; 62-oil mist field formed by primary fuel injection; 7-secondary injection of fuel; 8-swirler assembly nozzle.
The drawings are intended to depict only the structures associated with the present invention in more detail than as they are presently considered to be illustrative, and not to scale, of the full scope of equipment and system construction, nor is the contents of the drawings intended to be limiting.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. The following description describes specific details for the purpose of fully explaining the principles and technical aspects of the present invention, and is not intended to limit the present invention. For purposes of illustration, the drawings include only those features relevant to the present disclosure and not all features.
A swirler assembly for an aircraft engine combustion chamber as shown in figure 1, the swirler assembly 1 comprises a venturi tube 2 and a fuel injection tube 3, wherein the venturi tube 2 is divided into a cylindrical section 21, a converging section 22 and a diverging section 23. The air swirler 4 is arranged in the annular flow passage between the venturi cylindrical section 21 and the fuel injection pipe 3. The fuel injection pipe 3 includes annular primary and secondary fuel injection flow passages 31, 32 in which fuel swirlers 35, 36 are provided, respectively. The swirler assembly 1 is capable of fuel injection in two different atomization modes: the primary fuel injection port 33 faces the pipe wall of the Venturi pipe contraction section 22, the primary injection fuel 61 is ejected from the primary fuel injection port 33 through the fuel swirler 35, a liquid film is formed on the wall of the contraction section 22, the liquid film is pre-filmed and atomized under the action of swirl air 5, then secondary atomization and crushing are carried out when the liquid film flows from the contraction section 22 to the sudden expansion section 23 to form an oil mist field 62, and the distance between the primary fuel injection port 33 and the pipe wall of the Venturi pipe contraction section 22 is designed to realize that the primary injection fuel 61 forms the liquid film on the wall of the contraction section 22 firstly and cannot be directly blown into the sudden expansion section 23 by the swirl air 5; the secondary fuel injection ports 34 are directed toward the flare 23 and the secondary injection fuel 7 is injected from the secondary fuel injection ports 34 directly into the flare 23 through fuel swirlers 36 and blended with the swirl air 5. The opening and closing of the primary fuel injection passage 31 and the secondary fuel injection passage 32 and the fuel flow rate can be independently and respectively controlled according to working conditions, so that the swirler assembly 1 can realize the purpose of respectively injecting two kinds of fuels with different atomization modes or injecting a mixed oil mist field in which the two kinds of fuels with different atomization modes are mixed in different proportions. The fuel with different atomization modes leaves the nozzle 8 of the swirler assembly to participate in the combustion organization of the engine, so that combustion modes with different flame characteristics are formed.
Wherein, the number of the vanes of the air swirler 4 is 6, and the angle value is 45 degrees. The fuel swirler 35, 36 has 3 vanes and an angle value of 35 °.
In one embodiment, the fuel flow rates injected by the primary and secondary fuel injection ports 33, 34 are 100%/0, 50%/50%,0/100% of the total injection flow rate of the entire swirler assembly 1, respectively, depending on various operating conditions.
In another embodiment, the air swirler 4 has 20 vanes and an angular value of 80 °. The fuel swirlers 35, 36 have a vane count of 12 and an angle value of 80 °.
A multi-point staged lean direct injection combustion chamber 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 are spaced apart in a radially staggered manner in the combustor shown in fig. 2A, and the swirler assemblies 1 are aligned in a radially aligned manner in the combustor shown in fig. 2B.
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 rotor assemblies 1 on R1, 12 rotor assemblies 1 on R2, and 18 rotor assemblies 1 on R3.
In one embodiment, during operation of the combustor, swirler assembly 1 at R1 injects fuel only through primary fuel injection ports 33, swirler assembly 1 at R2 injects fuel simultaneously through primary fuel injection ports 33 and secondary fuel injection ports 34 at a fuel flow rate of 1:1, and swirler assembly 1 at R3 injects fuel only through secondary fuel injection ports 34.
In another embodiment, the swirler assemblies 1 on each of R1, R2, R3 are operated such that only the primary fuel injection ports 33 inject fuel at the maximum flow rate allowed by the fuel injection tubes 3.
In another embodiment, the combustor chamber, and the swirler assemblies 1 on R1 and R2 each have only the primary fuel injection ports 33 injecting fuel at the maximum flow rate allowed by the fuel injection tubes 3, and the secondary fuel injection ports 34 of the swirler assemblies 1 on R3 injecting fuel at the maximum flow rate allowed by the fuel injection tubes 3.
In yet another 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, 12 swirler assemblies 1 arranged in the combustion chamber 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 part, a plurality of swirler assemblies 1 are arranged in the combustion chamber head part, the swirler assemblies 1 inject fuel from different fuel ports in different injection modes and are mixed 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 therefore unburned components with different local equivalence ratio distributions 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 amount in each of the two fuel atomization modes for a single swirler assembly 1, so as to adjust the fuel flow in different fuel atomization modes, and further control the participation degree of the oil mist fields 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 as in fig. 2A to form a combustion pattern within the annular combustion chamber. According to the control method, for different working conditions, staged combustion with spatial distribution is realized in the annular combustion chamber by adjusting different fuel atomization modes and fuel flow rates of the swirler assemblies 1 at different annular radiuses R1, R2 and R3.
The invention has been described above with reference to examples, but the scope of protection of the invention is not limited thereto. Various modifications may be made without departing from the scope of the invention, and equivalent structures may be substituted for elements of the system and apparatus, and equivalent steps or operations may be used to modify the method.
Claims (11)
1. A swirler assembly, comprising:
the Venturi tube comprises a cylindrical section, a contraction section and a sudden expansion section;
a fuel injection tube including a primary fuel injection flow passage and a secondary fuel injection flow passage;
the fuel injection pipe is arranged in the Venturi pipe, an annular air flow channel is formed between the fuel injection pipe and the Venturi pipe, and an air swirler is arranged in the air flow channel at a position corresponding to the cylindrical section;
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 flow passage faces the sudden expansion section;
the primary fuel injection flow passage and the secondary fuel injection flow passage are used for respectively injecting fuel according to control instructions.
2. The swirler assembly of claim 1, wherein the air swirler has an angle of 45 ° to 80 ° and a vane count of 6 to 20.
3. The swirler assembly of claim 1, wherein the primary and secondary fuel injection runners of the fuel injection tube further comprise a fuel swirler having an angle value of 35 ° -80 ° and a vane count 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 as claimed in any one of claims 1 to 3.
5. The multi-point staged lean direct injection combustor according to claim 4, wherein the plurality of swirler assemblies are arranged annularly in a plurality of concentric circles.
6. The multi-point staged lean direct injection combustor according to claim 5, wherein the plurality of swirler assemblies are radially aligned in a line on the concentric circles.
7. The multi-point staged lean direct injection combustor according to claim 5, wherein the plurality of swirler assemblies are arranged in a staggered spaced relationship relative to each other in a radial direction of the concentric circles.
8. The multipoint staged lean direct injection combustor according to claim 4, wherein the number of swirler assemblies arranged in the combustor is 12-36.
9. A method of controlling multipoint staged lean direct injection combustion for an annular combustor, the annular combustor comprising a combustor head including a plurality of swirler assemblies, the method comprising:
at least two fuel atomization modes are provided on a single swirler assembly, oil mist fields with different fuel distribution characteristics are formed respectively, the oil mist fields form unburned components with different local equivalence ratio distributions, and finally flames with different shapes and combustion characteristics are formed in a combustion chamber.
10. The control method of claim 9, wherein the fuel supply in each of the at least two fuel atomization modes is also controlled separately for a single swirler assembly to adjust the fuel flow for different fuel atomization modes.
11. The control method of claim 10, wherein the combustion pattern in the annular combustion chamber is formed by arranging swirler assemblies circumferentially uniformly or at intervals in the annular combustion chamber, and wherein staged combustion with spatial distribution is formed in the annular combustion chamber by adjusting different fuel atomization patterns and fuel flow rates of the swirler assemblies at different annular radius positions for different operating conditions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110784890.XA CN115597089B (en) | 2021-07-12 | 2021-07-12 | Cyclone assembly, multi-point staged lean direct injection combustor and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Publication Number | Publication Date |
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| CN115597089A true CN115597089A (en) | 2023-01-13 |
| CN115597089B CN115597089B (en) | 2024-04-19 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100269508A1 (en) * | 2007-11-29 | 2010-10-28 | Mitsubishi Heavy Industries, Ltd. | Combustion burner |
| 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 |
| US20200191383A1 (en) * | 2018-12-14 | 2020-06-18 | Delavan Inc. | Multipoint fuel injection for radial in-flow swirl premix gas fuel injectors |
-
2021
- 2021-07-12 CN CN202110784890.XA patent/CN115597089B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100269508A1 (en) * | 2007-11-29 | 2010-10-28 | Mitsubishi Heavy Industries, Ltd. | Combustion burner |
| 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 |
| US20200191383A1 (en) * | 2018-12-14 | 2020-06-18 | Delavan Inc. | Multipoint fuel injection for radial in-flow swirl premix gas fuel injectors |
| 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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| Publication number | Publication date |
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| CN115597089B (en) | 2024-04-19 |
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