CN117404686A - Micro-diffusion cyclone combustion device taking hydrogen as fuel - Google Patents
Micro-diffusion cyclone combustion device taking hydrogen as fuel Download PDFInfo
- Publication number
- CN117404686A CN117404686A CN202311620165.4A CN202311620165A CN117404686A CN 117404686 A CN117404686 A CN 117404686A CN 202311620165 A CN202311620165 A CN 202311620165A CN 117404686 A CN117404686 A CN 117404686A
- Authority
- CN
- China
- Prior art keywords
- hydrogen
- air
- micro
- diameter
- inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 116
- 239000001257 hydrogen Substances 0.000 title claims abstract description 112
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 112
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 47
- 238000009792 diffusion process Methods 0.000 title claims abstract description 17
- 239000000446 fuel Substances 0.000 title claims abstract description 12
- 238000004891 communication Methods 0.000 claims description 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 abstract description 15
- 238000005496 tempering Methods 0.000 abstract description 5
- 238000009826 distribution Methods 0.000 description 7
- 239000007789 gas Substances 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 239000002131 composite material Substances 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 238000002679 ablation Methods 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 125000004435 hydrogen atom Chemical group [H]* 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
-
- 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
- F23R3/26—Controlling the air flow
-
- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- 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)
Abstract
The invention relates to the technical field of swirl combustion, in particular to a micro-diffusion swirl combustion device taking hydrogen as fuel. In the device, a first shell is provided with a hydrogen inlet, a first cavity is formed in the first shell, and the hydrogen inlet is communicated with the first cavity; the second shell is provided with an air inlet, a second cavity is formed in the second shell, the air inlet is communicated with the second cavity, the top of the second shell is provided with an end plate used for being connected with the combustion chamber, the end plate is provided with a plurality of air micro-channels, and each air micro-channel is of a zoom structure; the bottom of many hydrogen pipeline is located the top of first casing, every hydrogen pipeline all wears to locate the second cavity with air microchannel and surpass the top surface of end plate, the hydrogen pipeline with first cavity intercommunication. The scheme can solve the problems of unstable tempering, local overtemperature and high emission of nitrogen oxides.
Description
Technical Field
The invention relates to the technical field of swirl combustion, in particular to a micro-diffusion swirl combustion device taking hydrogen as fuel.
Background
The hydrogen has no carbon emission in the combustion process, and can be used as a carbon-free alternative fuel for combustion power generation of a gas turbine.
Hydrogen has extreme physical properties, and is easy to cause unstable tempering, local overtemperature, nitrogen oxide emission rise and other problems of the combustion device. Therefore, there is a need to provide a micro-diffusion swirl combustion device using hydrogen as fuel to solve the above technical problems.
Disclosure of Invention
The embodiment of the invention provides a micro-diffusion cyclone combustion device taking hydrogen as fuel, which can solve the problems of unstable tempering, local overtemperature and increased emission of nitrogen oxides.
The embodiment of the invention provides a micro-diffusion cyclone combustion device taking hydrogen as fuel, which comprises:
the hydrogen gas inlet is communicated with the first cavity;
the second shell is provided with an air inlet, a second cavity is formed in the second shell, the air inlet is communicated with the second cavity, the top of the second shell is provided with an end plate used for being connected with the combustion chamber, the end plate is provided with a plurality of air micro-channels, and each air micro-channel is of a zoom structure;
the bottom is located the top of first casing, every hydrogen pipeline all wears to locate the second cavity with air microchannel and surpass the top surface of end plate, the hydrogen pipeline with first cavity intercommunication.
The embodiment of the invention provides a micro-diffusion cyclone combustion device taking hydrogen as fuel, which can increase the outward diffusion flow state of air by setting each air micro-channel as a scaling structure so as to generate a low-pressure area at the top area of a plurality of hydrogen pipelines, so that the hydrogen and the air are mixed more uniformly at the outlet of a nozzle to form a micro-scale wind-fire-covering structure, and the characteristics of less NOx emission, uniform temperature field distribution, independent flame and the like are taken into consideration. Therefore, the technical scheme can solve the problems of unstable tempering, local overtemperature and increased emission of nitrogen oxides.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a micro-diffusion cyclone burner using hydrogen as fuel according to an embodiment of the present invention;
FIG. 2 is a top view of the composite combustion apparatus shown in FIG. 1;
FIG. 3 is a bottom view of the composite combustion apparatus shown in FIG. 1;
FIG. 4 is a schematic view in section A-A of the composite combustion apparatus shown in FIG. 1;
FIG. 5 is a schematic view in section B-B of the composite combustion apparatus shown in FIG. 1;
fig. 6 is an enlarged schematic view of the composite combustion apparatus shown in fig. 5at C.
Reference numerals:
1-a first housing;
11-hydrogen inlet;
12-a first cavity;
13-supporting columns;
14-a hydrogen guide plate;
2-a second housing;
21-an air inlet;
22-a second cavity;
23-end plates;
24-air microchannel;
25-an air deflector;
3-hydrogen pipeline;
31-thread structure.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any inventive effort based on the embodiments of the present invention are within the scope of protection of the present invention.
As shown in fig. 1 to 6, an embodiment of the present invention provides a micro-diffusion cyclone combustion device using hydrogen as fuel, which includes:
a first housing 1 provided with a hydrogen inlet 11, a first cavity 12 being formed inside, the hydrogen inlet 11 being in communication with the first cavity 12;
the second shell 2 is provided with an air inlet 21, a second cavity 22 is formed in the second shell, the air inlet 21 is communicated with the second cavity 22, the top of the second shell 2 is provided with an end plate 23 used for being connected with a combustion chamber, the end plate 23 is provided with a plurality of air micro-channels 24, and each air micro-channel 24 is of a zoom structure;
the bottom of the plurality of hydrogen pipelines 3 is positioned at the top of the first shell 1, each hydrogen pipeline 3 penetrates through the second cavity 22 and the air micro-channel 24 and exceeds the top surface of the end plate 23, and the hydrogen pipelines 3 are communicated with the first cavity 12.
In this embodiment, by setting each air micro-channel 24 to be a scaled structure, the flow state of air outward diffusion can be increased, so as to generate a low-pressure area in the top area of the plurality of hydrogen pipelines 3, so that the hydrogen and the air are mixed more uniformly at the outlet of the nozzle, and a micro-scale air fire-covering structure is formed, which gives consideration to the characteristics of less NOx emission, uniform temperature field distribution, independent flame and the like. Therefore, the technical scheme can solve the problems of unstable tempering, local overtemperature and increased emission of nitrogen oxides.
In some embodiments, the above-described swirling-combustion device may be applied to gas turbine and gas boiler combustors, which are not particularly limited herein.
In some embodiments, the height of the second cavity 22 is 1.43 times the height of the first cavity 12, which may allow more diffusion space in the axial direction for air passing into the second cavity 22, and uniformly distribute the air in the second cavity 22.
As shown in fig. 5, in one embodiment of the present invention, a support column 13 and a hydrogen deflector 14 are disposed in the first housing 1, the support column 13 is vertically disposed at the bottom of the first housing 1, the hydrogen deflector 14 is a circular plate, the hydrogen inlet 11 is disposed at the bottom of the first housing 1, the hydrogen deflector 14 is opposite to the hydrogen inlet 11, and the hydrogen deflector 14 is perpendicular to the hydrogen flow direction.
In this embodiment, when hydrogen enters the first cavity 12 from the hydrogen inlet 11, after contacting with the hydrogen guide plate 14, the hydrogen flows to the edge along the lower side of the hydrogen guide plate 14, and flows back in the first cavity 12, so as to increase the turbulence degree of the hydrogen flow, further make the hydrogen uniformly distributed in the first cavity 12, and ensure that the hydrogen is uniformly distributed in each hydrogen pipeline 3.
In some embodiments, the support columns 13 are three cylinders with diameters of 8mm and heights of 8mm uniformly arranged along the circumference, and the hydrogen guide plate 14 is a circular baffle plate with a diameter of 100mm and a thickness of 2 mm.
In one embodiment of the present invention, the air inlet 21 is provided at the side of the second housing 2, and the length direction of the hydrogen gas pipe 3 is perpendicular to the air flow direction. This arrangement increases the turbulence of the air flow and thus the air distribution in the second chamber 22.
In one embodiment of the present invention, an air deflector 25 is disposed in the second housing 2, the air deflector 25 is disposed at the bottom of the second housing 2, the air deflector 25 is located at the periphery of the hydrogen pipeline 3, the air deflector 25 is opposite to the air inlet 21, and the air deflector 25 is perpendicular to the air flow direction. The first shell 1 and the second shell 2 are of cylindrical structures, the air guide plates 25 are arc-shaped plates, the plurality of hydrogen pipelines 3 form a plurality of circles which are arranged in a arrayed mode, and the arc centers of the air guide plates 25 face the hydrogen pipelines 3.
In this embodiment, the center of the air deflector 25 is opposite to the air inlet 21, so that the air is firstly blocked by the air deflector 25, flows along the outer diameter surface of the air deflector 25 to reach the edge and then diffuses into the second cavity 22, and is further blocked by the plurality of hydrogen pipelines 3, so that the air diffuses further in the second cavity 22, and the uniformity of distribution is further improved.
In one embodiment of the present invention, the hydrogen pipelines 3 are 312, the 312 hydrogen pipelines 3 are divided into twelve circles and are arranged in a concentric circle array, the diameter difference of the adjacent two concentric circles of the first ten circles outwards from the center is the same, the diameter of the concentric circle of the eleventh circle is 0.15 times larger than that of the concentric circle of the tenth circle, the diameter of the concentric circle of the twelfth circle is 0.35 times larger than that of the concentric circle of the eleventh circle, each circle of the hydrogen pipelines 3 is 4n, and n is the number of circles.
Considering that the size of the combustion chamber is slightly larger than the size of the concentric circle of the outermost ring of the burner, the low-pressure area backflows sprayed to the air flow possibly exist after the hydrogen and the air are sprayed out from the nozzles of the outermost ring, so that the combustion is concentrated. Therefore, this technical problem can be solved by setting the concentric circle diameter of the eleventh turn to be 0.15 times larger than the concentric circle diameter of the tenth turn, and setting the concentric circle diameter of the twelfth turn to be 0.35 times larger than the concentric circle diameter of the eleventh turn.
For example, the diameters of the concentric circles are 10mm, 20mm, 30mm, 40mm, 50mm, 60mm, 70mm, 80mm, 90mm, 100mm, 115mm, 135mm in sequence, and the number z=4n (1.ltoreq.n.ltoreq.12) of the pipes arranged on each layer from inside to outside, that is, the numbers of the pipes of the circles are 4, 8, 12, 16, 20, 24, 28, 32, 36, 40, 44, 48, respectively.
In one embodiment of the invention, each concentric circle outward from the center of the circle is deflected 10 ° clockwise than the concentric circle of the previous circle. By the arrangement, the rotational flow degree of the outlet of the nozzle can be further improved, so that the hydrogen and the air are mixed more uniformly at the outlet of the nozzle.
For a flame tube, the recommended heat capacity strength is 1234-2073 kJ/(m) 3 h.Pa), so that the design heat capacity strength is selected to be 1519 kJ/(m) 3 ·h·Pa), the design power of the combustion device is 100-300 kW, the equivalent ratio is 0.4-0.9, and the pressure is 0.1-3 MPa. In order to meet the requirement of heat capacity intensity, the inner diameter of each hydrogen pipeline 3 in the first ten circles outwards from the circle center is 0.8mm, the outer diameter is 1.2mm, the inner diameter of each hydrogen pipeline 3 in the eleventh circle is 1mm, the outer diameter is 1.5mm, the inner diameter of each hydrogen pipeline 3 in the twelfth circle is 1.5mm, and the outer diameter is 2mm;
the number of the air micro-channels 24 is 312, each air micro-channel 24 coincides with the center of one hydrogen pipeline 3, the inlet and outlet diameter of each air micro-channel 24 in the first ten circles outwards from the center is 3mm, the throat diameter is 2mm, the inlet and outlet diameter of each air micro-channel 24 in the eleventh circle is 3.2mm, the throat diameter is 2.2mm, the inlet and outlet diameter of each air micro-channel 24 in the twelfth circle is 3.4mm, and the throat diameter is 2.4mm.
In one embodiment of the present invention, the outer surface of the portion of each hydrogen pipe 3 located within the air micro-channel 24 is provided with a screw structure 31. The thread section of the thread structure 31 is isosceles trapezoid with the short side length of 0.08mm, the long side length of 0.22mm and the height of 0.12mm, the hydrogen pipeline 3 exceeds the end plate 231mm, the included angle between the thread angle of the thread structure 31 and the horizontal plane is 60 degrees, the hydrogen flow rate in the hydrogen pipeline 3 is 40-70 m/s, and the applicable pressure is 0.5 atm-3 atm. By the arrangement, air can be attached to the hydrogen pipeline 3at the contraction section of the contraction and expansion structure, flow guiding submillimeter-scale threaded movement can be achieved along the pipe wall through rotational flow, and the air can be fully diffused at the expansion section after passing through the throat, so that air flow with rotational flow outwards diffused is formed.
That is, the air is compressed as it passes through the tapered sections of the air micro-channels 24 of the circumferential array, and has a tendency to gather toward the central axis, and flows close to the wall surface of the hydrogen pipe 3 of the circumferential array, and the air near the center portion generates a swirl under the flow guiding action of the swirl flow guiding threads of the wall surface of the hydrogen pipe 3. The hydrogen branch (7) is still provided with threads on the outer wall surface of the part corresponding to the diverging section of the air micro-channel 24, when air enters the diverging section, the air is outwards diffused and has certain rotational flow characteristics, and the diffusion type outward-rotating flow state is presented, so that a low-pressure area is generated in the area, close to the outer wall surface, of the hydrogen pipeline 3, hydrogen and air are more uniformly mixed at the outlet of the nozzle, a micro-scale wind fire-covering structure is formed, and the characteristics of less NOx emission, uniform temperature field distribution, independent flame and the like are considered.
In some embodiments, the end plate 23 is a circular ring with an inner diameter of 162mm and an outer diameter of 320mm, and 6 circular holes with a diameter of 18mm are uniformly distributed on the ring in a circular track with a diameter of 280mm so as to be connected with a connecting plate on the side of the combustion chamber.
In summary, hydrogen plays a great role in the fields of energy storage, chemical industry, aero-engines, gas turbines and the like, and becomes an effective way for reducing carbon emission and slowing down greenhouse effect. With the rapid development of new energy sources such as wind, light, water and the like in China, a large amount of hydrogen is obtained through a hydrogen production and storage system, and combustion is one of the most effective and direct hydrogen utilization modes. Compared with the traditional hydrogen combustion device, the micro-diffusion cyclone combustion device provided by the technical scheme has the advantages of avoiding backfire risk, reducing nozzle ablation hazard, enabling the temperature distribution of a combustion field to be more uniform and the like, and provides powerful technical support and safety guarantee for the hydrogen combustion device in a gas turbine and an aeroengine.
Specifically, a hydrogen gas cylinder is used for providing hydrogen gas to the combustor, an oil-free air compressor is used for providing air to the combustor, a hydrogen guide plate and an air guide plate are respectively utilized to enable gas introduced into the combustor to be distributed uniformly, so that hydrogen/air is distributed uniformly in hydrogen pipelines and air micro-channels of each circumferential array, and is sprayed into the combustion chamber through the hydrogen pipelines and the air micro-channels, and stable combustion is achieved after ignition of a high-voltage high-energy electric arc igniter. When the combustion working condition is changed, when the power is increased, the air quantity is firstly adjusted to reach the required quantity, and after stable combustion, the hydrogen is adjusted to reach the required power; when the power is reduced, firstly reducing the amount of hydrogen to reach the required power and stabilizing the combustion, and then adjusting the amount of air; when the pressure is changed, the supply of the changed hydrogen is firstly cut off, then the combustion chamber is closed, air is introduced or released, and when the pressure in the combustion chamber reaches the required state, hydrogen is introduced and ignited, so that the safe combustion of the hydrogen is realized. Compared with the traditional hydrogen combustion device, the designed micro-diffusion cyclone combustion device has the advantages of avoiding backfire risk, reducing nozzle ablation hazard, ensuring more uniform temperature distribution of a combustion field and the like, and provides powerful technical support and safety guarantee for the hydrogen combustion device in a gas turbine and an aeroengine.
It is noted that relational terms such as first and second, and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one …" does not exclude the presence of additional identical elements in a process, method, article or apparatus that comprises the element.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A micro-diffusion swirl combustion device using hydrogen as fuel, comprising:
a first housing (1) provided with a hydrogen inlet (11) and a first cavity (12) formed therein, the hydrogen inlet (11) being in communication with the first cavity (12);
the combustion chamber comprises a second shell (2), wherein an air inlet (21) is formed in the second shell, a second cavity (22) is formed in the second shell, the air inlet (21) is communicated with the second cavity (22), an end plate (23) used for being connected with the combustion chamber is arranged at the top of the second shell (2), a plurality of air micro-channels (24) are arranged on the end plate (23), and each air micro-channel (24) is of a zoom structure;
the bottom is located the top of first casing (1), every hydrogen pipeline (3) all wear to locate second cavity (22) with air microchannel (24) and surpass the top surface of end plate (23), hydrogen pipeline (3) with first cavity (12) intercommunication.
2. The device according to claim 1, wherein a support column (13) and a hydrogen guide plate (14) are arranged in the first shell (1), the support column (13) is vertically arranged at the bottom of the first shell (1), the hydrogen guide plate (14) is a circular plate, the hydrogen inlet (11) is arranged at the bottom of the first shell (1), the hydrogen guide plate (14) is opposite to the hydrogen inlet (11), and the hydrogen guide plate (14) is perpendicular to the hydrogen flow direction.
3. The device according to claim 1, characterized in that the air inlet (21) is provided at the side of the second housing (2), the length direction of the hydrogen pipe (3) being perpendicular to the air flow direction.
4. A device according to claim 3, characterized in that an air deflector (25) is arranged in the second housing (2), the air deflector (25) is arranged at the bottom of the second housing (2), the air deflector (25) is positioned at the periphery of the hydrogen pipeline (3), the air deflector (25) is opposite to the air inlet (21), and the air deflector (25) is perpendicular to the air flow direction.
5. The device according to claim 4, wherein the first housing (1) and the second housing (2) are both cylindrical structures, the air guide plate (25) is an arc plate, a plurality of hydrogen pipelines (3) form a plurality of circles arranged in a row, and the arc centers of the air guide plate (25) face the hydrogen pipelines (3).
6. The apparatus according to claim 5, wherein the hydrogen gas pipes (3) are 312, 312 hydrogen gas pipes (3) are divided into twelve turns and arranged in a concentric circle array, the diameter differences of the adjacent two concentric circles of the first ten turns from the center to the outside are identical, the concentric circle diameter of the eleventh turn is 0.15 times larger than the concentric circle diameter of the tenth turn, the concentric circle diameter of the twelfth turn is 0.35 times larger than the concentric circle diameter of the eleventh turn, each turn of the hydrogen gas pipes (3) is 4n, and n is the number of turns.
7. The apparatus of claim 6, wherein each concentric circle from the center of the circle is deflected 10 ° clockwise than the concentric circle of the previous circle.
8. The device according to claim 7, wherein the inner diameter of each of the hydrogen pipes (3) in the first ten turns from the center to the outside is 0.8mm, the outer diameter is 1.2mm, the inner diameter of each of the hydrogen pipes (3) in the eleventh turn is 1mm, the outer diameter is 1.5mm, the inner diameter of each of the hydrogen pipes (3) in the twelfth turn is 1.5mm, and the outer diameter is 2mm;
the number of the air micro-channels (24) is 312, each air micro-channel (24) coincides with the center of one hydrogen pipeline (3), the inlet and outlet diameter of each air micro-channel (24) in the first ten circles outwards from the center is 3mm, the throat diameter is 2mm, the inlet and outlet diameter of each air micro-channel (24) in the eleventh circle is 3.2mm, the throat diameter is 2.2mm, the inlet and outlet diameter of each air micro-channel (24) in the twelfth circle is 3.4mm, and the throat diameter is 2.4mm.
9. The device according to any one of claims 1-8, characterized in that the outer surface of the portion of each hydrogen conduit (3) located within the air micro-channel (24) is provided with a screw thread structure (31).
10. The device according to claim 9, characterized in that the thread section of the thread structure (31) is an isosceles trapezoid with a short side length of 0.08mm, a long side length of 0.22mm and a height of 0.12mm, the hydrogen pipe (3) extends beyond the end plate (23) by 1mm, the angle between the thread angle of the thread structure (31) and the horizontal plane is 60 °, the hydrogen flow rate in the hydrogen pipe (3) is 40-70 m/s, and the applicable pressure is 0.5 atm-3 atm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311620165.4A CN117404686A (en) | 2023-11-30 | 2023-11-30 | Micro-diffusion cyclone combustion device taking hydrogen as fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311620165.4A CN117404686A (en) | 2023-11-30 | 2023-11-30 | Micro-diffusion cyclone combustion device taking hydrogen as fuel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117404686A true CN117404686A (en) | 2024-01-16 |
Family
ID=89492718
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311620165.4A Pending CN117404686A (en) | 2023-11-30 | 2023-11-30 | Micro-diffusion cyclone combustion device taking hydrogen as fuel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117404686A (en) |
-
2023
- 2023-11-30 CN CN202311620165.4A patent/CN117404686A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4845952A (en) | Multiple venturi tube gas fuel injector for catalytic combustor | |
| CN114294680B (en) | Micro-premixing combustion chamber of central grading gas turbine | |
| US5299930A (en) | Low nox burner | |
| CN102692017B (en) | Solid-oxide fuel cell (SOFC) power generation system and burner thereof | |
| CN115451432B (en) | Micro-mixing nozzle assembly and system for fuel in combustion chamber of gas turbine | |
| WO2018188211A1 (en) | Gasification burner | |
| CN113310049A (en) | Micro-scale premixing and grading combustor | |
| KR100533926B1 (en) | Supersonic jet burner | |
| TW200411113A (en) | Improved combination of a premixing chamber and a combustion chamber, with low emission of pollutants, for gas turbines running on liquid and/or gas fuel | |
| CN114688561B (en) | High-capacity heat strength gas generator taking air and alcohol as propellants | |
| CN104807044A (en) | Liquefied gas combustion chamber with outlet equipped with swirling vanes | |
| TW200409887A (en) | Main liquid fuel injection device for a single combustion chamber, having a premixing chamber, of a gas turbine with low emission of pollutants | |
| CN103196154B (en) | Burner and the method for distributing fuel in the burner | |
| CN112555829B (en) | Spray gun capable of generating supersonic airflow | |
| US9057524B2 (en) | Shielding wall for a fuel supply duct in a turbine engine | |
| CN117404686A (en) | Micro-diffusion cyclone combustion device taking hydrogen as fuel | |
| JP2019215138A (en) | Multi-nozzle burner and combustor | |
| WO2019163488A1 (en) | Burner device | |
| CN211424382U (en) | Low NOx wide flat flame burner | |
| KR102359001B1 (en) | Swirl stabilized high capacity duct burner | |
| CN117663194A (en) | Building block type micro-diffusion cyclone combustion device taking hydrogen as fuel | |
| CN111998343A (en) | Single-nozzle multi-beam flame nozzle | |
| JP5708119B2 (en) | Pulverized coal burner | |
| US11015810B2 (en) | Combustor nozzle assembly and gas turbine having the same | |
| CN115325569B (en) | Combustion chamber, gas turbine and combustion control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |