CN105757716B - A kind of nozzle, nozzle array and burner for premixed combustion - Google Patents
A kind of nozzle, nozzle array and burner for premixed combustion Download PDFInfo
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- CN105757716B CN105757716B CN201610096132.8A CN201610096132A CN105757716B CN 105757716 B CN105757716 B CN 105757716B CN 201610096132 A CN201610096132 A CN 201610096132A CN 105757716 B CN105757716 B CN 105757716B
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- 238000002485 combustion reaction Methods 0.000 title abstract description 60
- 239000012530 fluid Substances 0.000 claims abstract description 61
- 238000002156 mixing Methods 0.000 claims description 23
- 239000000446 fuel Substances 0.000 claims description 22
- 239000007921 spray Substances 0.000 claims description 10
- 239000003344 environmental pollutant Substances 0.000 abstract description 7
- 231100000719 pollutant Toxicity 0.000 abstract description 7
- 238000005496 tempering Methods 0.000 abstract description 5
- 230000010349 pulsation Effects 0.000 abstract description 3
- 238000010790 dilution Methods 0.000 abstract 1
- 239000012895 dilution Substances 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 12
- 238000005516 engineering process Methods 0.000 description 7
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000003801 milling Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007084 catalytic combustion reaction Methods 0.000 description 1
- 238000003889 chemical engineering Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 230000000737 periodic effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The present invention provides a kind of nozzles for premixed combustion, dilution zone is formed between the top of the intermediate air intake structure of the fluid outlet of internal layer air intake structure, the outer layer cylinder of outer layer air intake structure and M layers, influence of the tempering phenomenon to nozzle and burner is reduced, tempering nargin is improved；Between adjacent two layers wave rotational structure, oblique flow channel is formed between wave rotational structure and inner layer cylinder and outer layer cylinder, efficiency of combustion is improved, reduces pollutant emission, is prevented flame-out and flame pulsation phenomenon generation, is improved the stability of burning；Support cylinder, inner layer cylinder and outer layer cylinder form drainage channel, interior side runner and outer side runner, further improve the stability, completeness and efficiency of burning.
Description
Technical Field
The invention relates to the technical field of combustion devices, in particular to a nozzle and a nozzle array for premixed combustion, which are particularly suitable for various industrial combustors such as gas turbines, boilers, chemical furnaces and the like.
Background
The gas turbine is widely applied to industries such as electric power, aviation, petrochemical industry and the like due to the characteristics of small single machine volume, large output power and the like. Due to energy crisis and environmental deterioration, there is an urgent need to develop efficient and clean combustion chambers, which are required to have the characteristics of reliable ignition, stable combustion, high efficiency, low emission, etc. At present, the environmental pollution problem in China is very serious, and the development of clean combustion technology of a gas turbine is very urgent. Gas turbine manufacturers have developed various clean combustion technologies, such as lean premixed combustion technology, dilute premixed pre-evaporation technology, lean direct injection technology, catalytic combustion technology, etc., which are effective in reducing pollutant emissions but are all confronted with the problem of unstable combustion. A radial staged combustion technique for liquid fuel combustion, as developed by the united states general company, is effective in reducing nitric oxide emissions. However, since the main flame is stabilized at the low-speed edge of the shear layer, periodic vortex shedding occurs near the low-speed region of the shear layer, oscillation occurs easily near the stable point, and unstable combustion occurs easily when the fuel tank is operated under off-design conditions. Similar to gas turbine combustors, other types of industrial combustors also face the contradiction between stable combustion and reduced pollutant emissions. In addition, since fuels such as hydrogen gas are fast in combustion speed and easy to backfire, most industrial hydrogen combustors are in a diffusion combustion mode, and the backfire problem is a technical challenge faced by the hydrogen premixing combustor. Therefore, how to improve the prevention of the backfire phenomenon, improve the combustion stability and efficiency, and reduce the pollutant discharge is a topic to be researched urgently in the field.
Disclosure of Invention
Technical problem to be solved
In order to solve the above problems of the prior art, the present invention provides a nozzle, a nozzle array and a combustor for premixed combustion.
(II) technical scheme
The invention provides a nozzle for premixed combustion, which comprises an inner layer air inlet structure, an outer layer air inlet structure and an M-layer middle air inlet structure, wherein: one side of the inner layer air inlet structure, which is close to the fluid outlet, is a fluid outlet end, and one side of the inner layer air inlet structure, which is close to the fluid inlet, is an inner layer cylinder 11; the side of the outer layer air inlet structure close to the fluid outlet is provided with an outer layer cylinder 31; the M layers of middle air inlet structures are clamped between the inner layer cylinder 11 and the outer layer cylinder 31 and are sequentially arranged along the radial direction of the periphery of the cylinders, and airflow channels are formed between every two adjacent layers of middle air inlet structures, between the innermost layer of middle air inlet structure and the inner layer cylinder 11, between the outermost layer of middle air inlet structure and the outer layer cylinder 31 and inside the inner layer of middle air inlet structures; the fluid outlet end of the inner air inlet structure protrudes out of the M layers of middle air inlet structures along the fluid outlet direction, the outer layer cylinder 31 of the outer air inlet structure protrudes out of the fluid outlet end of the inner air inlet structure along the fluid outlet direction, and a mixing region 41 is formed among the fluid outlet end of the inner air inlet structure, the outer layer cylinder 31 of the outer air inlet structure and the top ends of the M layers of middle air inlet structures, wherein M is more than or equal to 1 and less than or equal to 100.
Preferably, the wave rotating structures 21 are arranged on one side of the middle air inlet structure close to the fluid outlet, and oblique flow channels are formed between two adjacent layers of wave rotating structures 21, between the innermost wave rotating structure and the inner cylinder 11, and between the outermost wave rotating structure and the outer cylinder 31, and extend from the bottom ends to the top ends of the wave rotating structures, and form a certain angle with the axial direction.
Preferably, the wave rotating structure 21 is formed by arranging N wave crests 22 and N wave troughs 23 which fluctuate along the radial direction at intervals along the circumferential direction, and diagonal flow channels are formed between the wave crests 22 and the wave troughs 23 of the adjacent two layers of wave rotating structures, between the wave trough of the wave rotating structure at the outermost layer and the outer layer cylinder 31, and between the wave crest of the wave rotating structure at the innermost layer and the inner layer cylinder 11, wherein N is more than or equal to 2 and less than or equal to 10000.
Preferably, the intermediate air intake structure further comprises support cylinders 24, the top ends of which are connected with the bottom ends of the wave crests and the wave troughs of the wave rotary structure, flow guide channels are formed between adjacent support cylinders 24, the flow guide channels are communicated with the diagonal flow channel formed by the wave rotary structure 21, an inner flow channel 42 is formed between the innermost support cylinder and the inner cylinder 11, the inner flow channel 42 is communicated with the wave crests of the innermost wave rotary structure and the diagonal flow channel formed by the inner cylinder 11, an outer flow channel 43 is formed between the outermost support cylinder and the outer cylinder 31, and the outer flow channel 43 is communicated with the wave troughs of the outermost wave rotary structure and the diagonal flow channel formed by the outer cylinder 31.
Preferably, the bottom end of the supporting cylinder of the middle air intake structure is connected with the first air intake structure 26, the bottom surface of the first air intake structure is provided with a plurality of first gas inlets 25, fuel or air enters the inner side flow channel 42 and the diversion channel from the first gas inlets 25 and flows out to the blending area 41 from the wave rotating structure 21; the bottom end of the outer layer cylinder of the outer layer air inlet structure is connected with a second air inlet structure 34, the bottom surface of the second air inlet structure is provided with a plurality of second air inlets 33, fuel or air enters an outer side flow channel 43 from the second air inlets 33 and flows out to the blending area 41 from the wave rotating structure 21; the bottom surface of the inner cylinder of the inner air inlet structure is provided with a third air inlet 15, and fuel or air enters the airflow channel 14 of the inner air inlet structure from the third air inlet 15 and flows out to the mixing region 41 from the spray hole at the fluid outlet end of the inner air inlet structure.
Preferably, the fluid outlet end of the inner layer air inlet structure is a conical fluid outlet end 12, and the conical fluid outlet end 12 is provided with K circles of spray holes at different axial positions; or, the fluid outlet end of the inner layer air inlet structure is a cylindrical fluid outlet end 13, and the top surface of the cylindrical fluid outlet end is provided with K rings of spray holes; wherein K is more than or equal to 1 and less than or equal to 100.
Preferably, the wave rotary structures 21 of the M-level intermediate air intake structure are arranged in axial alignment or are arranged axially offset from each other.
Preferably, the inclined flow channel of the wave rotating structure forms an included angle of-89 degrees to 89 degrees with the axial direction, and the rotating direction of the wave rotating structure is clockwise or anticlockwise.
The invention also provides a nozzle array comprising a plurality of nozzles for premixed combustion as described in any of the above embodiments; the nozzle array is a circular array, the circular array comprises P circles of nozzles, each circle of nozzles comprises Q nozzles, and the number of the nozzles is not less than 1 and not more than P, Q and not more than 100; or the nozzle array is a rectangular array which comprises P rows of nozzles, each row of nozzles comprises Q nozzles, wherein 1 is equal to or less than P, Q is equal to or less than 100.
The invention also provides a combustor comprising a nozzle for premixed combustion as described in any one of the above, or an array of nozzles as described.
(III) advantageous effects
According to the technical scheme, the nozzle array and the combustor for premixed combustion have the following beneficial effects:
(1) a blending area is formed among the fluid outlet end of the inner layer air inlet structure, the outer layer cylinder of the outer layer air inlet structure and the top end of the M layers of middle air inlet structures, fuel and air are not blended before entering the nozzle, but are blended in the blending area at the outlet end of the nozzle, and the tempering phenomenon can only occur in the blending area and cannot spread to the whole nozzle, so that the influence of the tempering phenomenon on the nozzle and a combustor is greatly reduced, and the tempering margin is improved;
(2) oblique flow channels are formed between two adjacent layers of wave rotating structures and between the wave rotating structures and the inner-layer cylinder and the outer-layer cylinder, and the oblique flow channels enable fuel and air to be mixed more fully, so that the combustion efficiency is improved, the pollutant emission is reduced, and the combustion state is improved;
(3) the oblique flow channel enables a low-speed area to be generated near the central axis of the mixing area, the low-speed area enables the flame combustion rate to be balanced with the flow field rate of the reaction fluid, flameout and flame pulsation phenomena are prevented, the combustion stability is improved, and the stable operation range of the nozzle is widened;
(4) the support cylinder, the inner cylinder and the outer cylinder of the middle air inlet structure form a diversion channel, an inner runner and an outer runner, and under the diversion action, the fuel and air flow rate is more stable, the flow field is more stable, and the stability, the completeness and the efficiency of combustion can be further improved.
Drawings
FIG. 1 is a three-dimensional schematic view of a nozzle for premixed combustion of a first embodiment of the present invention;
FIG. 2 is a top view of the nozzle shown in FIG. 1;
FIG. 3 is a schematic half-section view of the nozzle of FIG. 1;
FIG. 4 is a schematic drawing showing the partial dimensions of the nozzle of FIG. 1;
FIG. 5 is a schematic view of the wave-spinning structure and inner cylinder of the nozzle of FIG. 1;
FIG. 6 is a schematic view of the cylindrical fluid outlet end of the nozzle of FIG. 1.
[ notation ] to show
11-inner cylinder; 12-a conical fluid outlet end; 13-a cylindrical fluid outlet end; 14-gas flow channels of the inner air intake structure; 15-a third gas inlet;
21-wave rotating structure; 22-wave peak; 23-a trough; 24-a support cylinder; 25-a first gas inlet; 26-a first air intake structure;
31-outer cylinder; 32-nozzle outlet; 33-a second gas inlet; 34-a second air intake structure;
41-a mixing region; 42-inner flow channel; 43-outer flow channel;
a-the distance between the outermost wave-shaped rotating structure and the outer cylinder; b-the distance between the innermost wave-like rotating structure and the inner cylinder; c-radial width of the outer runner; d-inner side runner radial width; the axial distance between the top end of the E-wave rotating structure and the top end of the fluid outlet end of the inner layer air inlet structure is calculated; the axial distance between the top end of the F-wave rotating structure and the outlet of the nozzle; g is the axial distance between the top end of the fluid outlet end of the inner layer air inlet structure and the outlet of the nozzle.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings.
As shown in fig. 1 to 6, a nozzle for premixed combustion according to a first embodiment of the present invention includes an inner layer air intake structure, an outer layer air intake structure, and M layers of intermediate air intake structures, wherein a side of the inner layer air intake structure near a fluid outlet is a fluid outlet end, a side of the inner layer air intake structure near a fluid inlet is an inner layer cylinder 11, a side of the outer layer air intake structure near the fluid outlet is an outer layer cylinder 31, the M layers of intermediate air intake structures are sandwiched between the inner layer cylinder 11 and the outer layer cylinder 31 and are sequentially arranged along a radial direction of the periphery of the cylinders, a fluid outlet end of the inner layer air intake structure protrudes from the M layers of intermediate air intake structures along a fluid outlet direction, the outer layer cylinder 31 of the outer layer air intake structure protrudes from the fluid outlet end of the inner layer air intake structure along the fluid outlet direction, a mixing area 41 is formed among the fluid outlet end of the inner layer air inlet structure, the outer layer cylinder 31 of the outer layer air inlet structure and the top ends of the M layers of middle air inlet structures, wherein M is more than or equal to 1 and less than or equal to 100. In FIGS. 1-6, M is 1.
Preferably, the fuel participating in combustion may be a gas, a solid or a liquid.
Preferably, as shown in fig. 3, the fluid outlet end of the inner air inlet structure is a conical fluid outlet end 12, the conical fluid outlet end 12 is provided with K rings of spray holes at different axial positions, wherein K is greater than or equal to 1 and less than or equal to 100, and the diameter of the spray holes is 0.01 mm-100 mm; as shown in FIG. 6, the fluid outlet end of the inner layer air inlet structure is a cylindrical fluid outlet end 13, K rings of spray holes are arranged on the top surface of the cylindrical fluid outlet end, wherein K is more than or equal to 1 and less than or equal to 100, and the diameter of the spray holes is 0.01 mm-100 mm.
In the nozzle for premixed combustion according to the first embodiment of the present invention, the fuel participating in combustion enters the blending region 41 through at least one of the airflow passages, the air participating in combustion enters the blending region 41 through at least one of the airflow passages different from the fuel, the fuel and the air are blended in the blending region 41, and the blended mixture is ejected from the nozzle outlet 32 and premixed combusted. It can be seen that, in the nozzle for premixed combustion according to the first embodiment of the present invention, the fuel and the air are not mixed before entering the nozzle, but are mixed in the mixing region 41 at the outlet end of the nozzle, and the flashback phenomenon can only occur in the mixing region 41 and does not spread to the entire nozzle, so that the influence of the flashback phenomenon on the nozzle and the combustor is greatly reduced, and the flashback margin is improved.
For the purpose of brief description, any technical features of the first embodiment that can be applied to the nozzle for premixed combustion are described herein, and the same description need not be repeated.
The nozzle for premixed combustion is characterized in that one side, close to a fluid outlet, of the middle air inlet structure is a wave rotating structure 21, oblique flow channels are formed between two adjacent layers of wave rotating structures 21, between the innermost layer of wave rotating structure and the inner layer cylinder 11 and between the outermost layer of wave rotating structure and the outer layer cylinder 31, extend from the bottom end to the top end of the wave rotating structure, and form a certain angle with the axial direction.
Preferably, the wave rotating structure 21 is formed by arranging N wave crests 22 and N wave troughs 23 which fluctuate along the radial direction at intervals along the circumferential direction, and oblique flow channels are formed between the wave crests 22 and the wave troughs 23 of the adjacent two layers of wave rotating structures, between the outermost layer of wave rotating structure and the outer layer cylinder 31 and between the innermost layer of wave rotating structure and the inner layer cylinder 11, wherein N is more than or equal to 2 and less than or equal to 10000.
Preferably, the cross-sectional shape of the wave-rotating structure may be a circular ring shape or a polygonal ring shape. The processing mode of the wave rotating structure can be integral extrusion forming, integral casting or integral turning and milling; or carrying out block extrusion forming, block casting, block turning and milling, and then welding into a whole. The inclined flow channel of the wave rotating structure has an included angle of-89 degrees with the axial direction, and the rotating direction of the wave rotating structure can be clockwise or anticlockwise.
Preferably, the wave rotating structures 21 of the M layers of intermediate air intake structures are arranged coaxially; the wave rotating structures 21 can be arranged in an axial alignment mode, the axial distance F between the top ends of the wave rotating structures and the nozzle outlets is 1-1000 mm, and the wave rotating structures can also be arranged in an axial staggered mode at a certain distance; the axial distance E between the top end of the wave rotating structure and the top end of the fluid outlet end of the inner layer air inlet structure is 0-1000 mm; the axial distance G between the top end of the fluid outlet end of the inner layer air inlet structure and the nozzle outlet is 0-1000 mm; the distance A between the outermost wave rotating structure and the outer cylinder 31 is 0 mm-1000 mm; the distance B between the innermost wave-shaped rotating structure and the inner cylinder 11 is 0 mm-1000 mm.
Preferably, the radial widths of the wave rotating structures of the M layers of the middle air intake structure may be all the same, or may be partially the same, or may be different; the wave crest and the wave trough of the wave rotating structure of the M layers of middle air inlet structures can be the same in number, can also be partially the same in number, and can also be different from each other; the wave crest and the wave trough of the wave rotating structure of the M layers of middle air inlet structures can be all the same, can also be partially the same, and can also be different.
According to the nozzle for premixed combustion in the second embodiment of the invention, fuel and air respectively pass through the oblique flow channel, flow along the axial direction under the action of the oblique flow channel 31, and simultaneously rotate along the circumferential direction, so that the fuel and the air can be more fully mixed, the combustion efficiency is improved, the pollutant emission is reduced, and the combustion state is improved; and under the action of the circumferential rotation motion, a low-speed area is generated near the central axis of the mixing area 41, the low-speed area enables the flame combustion rate to be balanced with the flow field rate of the reaction fluid, the phenomena of flameout and flame pulsation are prevented, the combustion stability is improved, and the stable operation range of the nozzle is widened.
For the purpose of brief description, any technical features of any one of the above embodiments that can be applied to the premixed combustion nozzle of the third embodiment of the present invention are described herein, and the same description need not be repeated.
The nozzle for premixed combustion further comprises a support cylinder 24, the top end of the support cylinder is connected with the bottom ends of the wave crest and the wave trough of the wave rotating structure, a drainage channel is formed between the adjacent support cylinders 24 and is communicated with an oblique flow channel formed by the wave rotating structure 21, an inner side flow channel 42 is formed between the innermost support cylinder and the inner cylinder 11, the inner side flow channel 42 is communicated with the oblique flow channel formed by the innermost wave rotating structure and the inner cylinder 11, an outer side flow channel 43 is formed between the outermost support cylinder and the outer cylinder 31, and the outer side flow channel 43 is communicated with the oblique flow channel formed by the outermost wave rotating structure and the outer cylinder 31.
Preferably, the ratio of the radial width C of the outer runner to the radial width D of the inner runner is 0.1-10.
In the nozzle for premixed combustion according to the third embodiment of the present invention, the support cylinder 24 plays a role in guiding flow, so that the flow velocity of fuel and air is more stable, the flow field is more stable, and the stability, completeness and efficiency of combustion can be further improved.
For the purpose of brief description, any technical features of any of the above embodiments that can be applied to premix combustion are described herein, and the same description need not be repeated.
In the nozzle for premixed combustion, the bottom end of a supporting cylinder of a middle air inlet structure is connected with a disc-shaped first air inlet structure 26, the bottom surface of the first air inlet structure is provided with a plurality of first air inlets 25, fuel or air enters an inner side flow channel 42 and a flow guide channel from the first air inlets 25 and flows out to an blending area 41 from a wave rotating structure 21; the bottom end of the outer layer cylinder of the outer layer air inlet structure is connected with a disc-shaped second air inlet structure 34, the bottom surface of the second air inlet structure is provided with a plurality of second air inlets 33, fuel or air enters an outer side flow channel 43 from the second air inlets 33 and flows out to the blending area 41 from the wave rotating structure 21; the bottom surface of the inner cylinder of the inner air inlet structure is provided with a third air inlet 15, and fuel or air enters the airflow channel 14 of the inner air inlet structure from the third air inlet 15 and flows out to the mixing region 41 from the spray hole at the fluid outlet end of the inner air inlet structure.
A fifth embodiment of the present invention provides a nozzle array for premixed combustion, including a plurality of nozzles for premixed combustion as described in any of the above embodiments.
The nozzle array for premixed combustion is a circular array, the circular array comprises P circles of nozzles, each circle of nozzles comprises Q nozzles, and the number of the nozzles is more than or equal to 1 and less than or equal to P, Q and less than or equal to 100.
The nozzle array for premixed combustion is a rectangular array, the rectangular array comprises P rows of nozzles, each row of nozzles comprises Q nozzles, and the number of the nozzles is more than or equal to 1 and less than or equal to P, Q and less than or equal to 100.
A fifth embodiment of the present invention provides a combustor including the nozzle for premixed combustion described in any one of the first to fourth embodiments described above, or the nozzle array for premixed combustion described in the fifth embodiment.
Up to this point, the present embodiment has been described in detail with reference to the accompanying drawings. From the above description, those skilled in the art should clearly recognize that the nozzle for premixed combustion of the present invention.
It is to be noted that, in the attached drawings or in the description, the implementation modes not shown or described are all the modes known by the ordinary skilled person in the field of technology, and are not described in detail. In addition, the above definitions of the various elements are not limited to the specific structures, shapes or modes mentioned in the embodiments, and those skilled in the art may easily modify or replace them, for example:
(1) the wave rotating structure can also adopt other structures;
(2) directional phrases used in the embodiments, such as "upper", "lower", "front", "rear", "left", "right", etc., refer only to the orientation of the attached drawings and are not intended to limit the scope of the present invention;
(3) the embodiments described above may be mixed and matched with each other or with other embodiments based on design and reliability considerations, i.e. technical features in different embodiments may be freely combined to form further embodiments.
In conclusion, the nozzle array and the combustor for premixed combustion can be used in the fields of aviation, chemical engineering, power generation, metallurgy and the like, the influence of a backfire phenomenon on the nozzle and the combustor can be reduced, the backfire margin can be improved, the combustion efficiency can be improved, the pollutant emission can be reduced, the combustion state can be improved, and the combustion stability can be improved.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A nozzle, characterized in that, it includes inner layer air inlet structure, outer layer air inlet structure and M layer middle air inlet structure, wherein:
one side of the inner layer air inlet structure, which is close to the fluid outlet, is a fluid outlet end, and one side of the inner layer air inlet structure, which is close to the fluid inlet, is an inner layer cylinder (11);
one side of the outer layer air inlet structure close to the fluid outlet is provided with an outer layer cylinder (31);
the M layers of middle air inlet structures are clamped between the inner layer cylinder (11) and the outer layer cylinder (31) and are sequentially arranged along the radial direction of the periphery of the cylinders, and airflow channels are formed between two adjacent layers of middle air inlet structures, between the innermost layer of middle air inlet structure and the inner layer cylinder (11), between the outermost layer of middle air inlet structure and the outer layer cylinder (31) and inside the inner layer of air inlet structure;
the fluid outlet end of the inner layer air inlet structure protrudes out of the M layers of middle air inlet structures along the direction of the fluid outlet, the outer layer cylinder (31) of the outer layer air inlet structure protrudes out of the fluid outlet end of the inner layer air inlet structure along the direction of the fluid outlet, and a mixing region (41) is formed among the fluid outlet end of the inner layer air inlet structure, the outer layer cylinder (31) of the outer layer air inlet structure and the top ends of the M layers of middle air inlet structures, wherein M is more than or equal to 1 and less than or equal to 100;
the fluid outlet end of the inner layer air inlet structure is a cylindrical fluid outlet end (13), and K rings of spray holes are formed in the top surface of the cylindrical fluid outlet end; wherein K is more than or equal to 1 and less than or equal to 100;
one side of the middle air inlet structure, which is close to the fluid outlet, is provided with a wave rotating structure (21), and the axial distance E between the top end of the wave rotating structure and the top end of the fluid outlet end of the inner air inlet structure is 0-1000 mm; the axial distance G between the top end of the fluid outlet end of the inner layer air inlet structure and the nozzle outlet is 0-1000 mm; the distance A between the outermost wave rotating structure and the outer layer cylinder (31) is 0 mm-1000 mm; the distance B between the innermost wave rotating structure and the inner cylinder (11) is 0 mm-1000 mm;
the bottom end of a supporting cylinder of the middle air inlet structure is connected with a first air inlet structure (26), the bottom surface of the first air inlet structure is provided with a plurality of first air inlets (25), fuel or air enters an inner side flow passage (42) and a flow guide channel from the first air inlets (25) and flows out to the blending area (41) from the wave rotating structure (21); the bottom end of an outer layer cylinder of the outer layer air inlet structure is connected with a second air inlet structure (34), the bottom surface of the second air inlet structure is provided with a plurality of second air inlets (33), and fuel or air enters an outer side flow channel (43) from the second air inlets (33) and flows out to the blending area (41) from the wave rotating structure (21); the bottom surface of the inner cylinder of the inner air inlet structure is provided with a third air inlet (15), and fuel or air enters the airflow channel (14) of the inner air inlet structure from the third air inlet (15) and flows out to the mixing area (41) from the spray hole at the fluid outlet end of the inner air inlet structure.
2. The nozzle of claim 1, wherein between adjacent layers of wave turns (21), between the innermost wave turn and the inner cylinder (11), and between the outermost wave turn and the outer cylinder (31) form diagonal flow channels extending from the bottom end to the top end of the wave turns and at an angle to the axial direction.
3. The nozzle according to claim 2, wherein the wave rotating structures (21) are formed by arranging N wave crests (22) and N wave troughs (23) which fluctuate along the radial direction at intervals along the circumferential direction, and oblique flow channels are formed between the wave crests (22) and the wave troughs (23) of the wave rotating structures at two adjacent layers, between the wave troughs of the wave rotating structures at the outermost layer and the outer layer cylinder (31), and between the wave crests of the wave rotating structures at the innermost layer and the inner layer cylinder (11), wherein N is more than or equal to 2 and less than or equal to 10000.
4. The nozzle according to claim 3, wherein the intermediate air inlet structure further comprises support cylinders (24) having top ends connected to bottom ends of crests and troughs of the wave rotation structure, flow guide channels are formed between adjacent support cylinders (24) and communicating with the diagonal flow channel formed by the wave rotation structure (21), an inner flow passage (42) is formed between the innermost support cylinder and the inner cylinder (11), the inner flow passage (42) communicates with the diagonal flow channel formed by the crests of the innermost wave rotation structure and the inner cylinder (11), an outer flow passage (43) is formed between the outermost support cylinder and the outer cylinder (31), and the outer flow passage (43) communicates with the troughs of the outermost wave rotation structure and the diagonal flow channel formed by the outer cylinder (31).
5. Nozzle according to claim 2, wherein the wave-like rotary structures (21) of the M-level intermediate air inlet structure are arranged axially aligned or axially offset from each other.
6. The nozzle of claim 2, wherein the diagonal flow channels of the wave rotating structure are angled from-89 ° to 89 ° from the axial direction, and wherein the direction of rotation of the wave rotating structure is clockwise or counterclockwise.
7. A nozzle array comprising a plurality of nozzles of any one of claims 1-6;
the nozzle array is a circular array, the circular array comprises P circles of nozzles, each circle of nozzles comprises Q nozzles, and the number of the nozzles is not less than 1 and not more than P, Q and not more than 100; or,
the nozzle array is a rectangular array, the rectangular array comprises P rows of nozzles, each row of nozzles comprises Q nozzles, and the number of the nozzles is greater than or equal to 1 and less than or equal to P, Q and less than or equal to 100.
8. A burner comprising the nozzle of any one of claims 1-6, or the nozzle array of claim 7.
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| CN201610096132.8A CN105757716B (en) | 2016-02-22 | 2016-02-22 | A kind of nozzle, nozzle array and burner for premixed combustion |
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| CN201610096132.8A CN105757716B (en) | 2016-02-22 | 2016-02-22 | A kind of nozzle, nozzle array and burner for premixed combustion |
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| CN105757716B true CN105757716B (en) | 2019-04-30 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106247408B (en) * | 2016-07-27 | 2019-01-18 | 中国科学院工程热物理研究所 | A kind of nozzle, nozzle array and burner for widening tempering nargin |
| CN106705122B (en) * | 2016-12-09 | 2019-02-01 | 中国科学院工程热物理研究所 | A kind of nozzle, nozzle array and burner having both inside and outside dilution zone |
| CN110081716B (en) * | 2018-01-26 | 2024-04-23 | 中国瑞林工程技术股份有限公司 | Top-blowing spray gun for electronic waste smelting device |
| CN114856827B (en) * | 2022-05-12 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Detachable fan-shaped nozzle capable of adjusting nozzle position and spraying direction |
| WO2023227547A1 (en) * | 2022-05-23 | 2023-11-30 | Casale Sa | Burner for a reforming reactor |
| CN116293802B (en) * | 2023-03-14 | 2024-05-14 | 中国空气动力研究与发展中心空天技术研究所 | Super-combustion ramjet engine combustion chamber based on shock wave system ignition and backflow flame stabilization |
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| US6179608B1 (en) * | 1999-05-28 | 2001-01-30 | Precision Combustion, Inc. | Swirling flashback arrestor |
| CN102165258A (en) * | 2008-09-29 | 2011-08-24 | 西门子公司 | Fuel nozzle |
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| US20030058737A1 (en) * | 2001-09-25 | 2003-03-27 | Berry Jonathan Dwight | Mixer/flow conditioner |
| WO2004020902A1 (en) * | 2002-08-30 | 2004-03-11 | Alstom Technology Ltd | Method and device for mixing fluid flows |
| US8443607B2 (en) * | 2009-02-20 | 2013-05-21 | General Electric Company | Coaxial fuel and air premixer for a gas turbine combustor |
| RU2550370C2 (en) * | 2011-05-11 | 2015-05-10 | Альстом Текнолоджи Лтд | Centrifugal nozzle with projecting parts |
| EP2604919A1 (en) * | 2011-12-12 | 2013-06-19 | Siemens Aktiengesellschaft | Fuel injector for two combustible materials |
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| US6179608B1 (en) * | 1999-05-28 | 2001-01-30 | Precision Combustion, Inc. | Swirling flashback arrestor |
| CN102165258A (en) * | 2008-09-29 | 2011-08-24 | 西门子公司 | Fuel nozzle |
| CN102859281A (en) * | 2010-02-23 | 2013-01-02 | 西门子公司 | Fuel injector and swirler assembly with lobed mixer |
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