CN116557907A - Swirl micro-mixing nozzle and combustion chamber - Google Patents
Swirl micro-mixing nozzle and combustion chamber Download PDFInfo
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- CN116557907A CN116557907A CN202310635297.8A CN202310635297A CN116557907A CN 116557907 A CN116557907 A CN 116557907A CN 202310635297 A CN202310635297 A CN 202310635297A CN 116557907 A CN116557907 A CN 116557907A
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- oxidant
- fuel
- micro
- straight pipe
- swirl
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 54
- 239000007800 oxidant agent Substances 0.000 claims abstract description 114
- 230000001590 oxidative effect Effects 0.000 claims abstract description 113
- 239000000446 fuel Substances 0.000 claims abstract description 110
- 230000008602 contraction Effects 0.000 claims abstract description 21
- 238000003491 array Methods 0.000 claims description 3
- 230000001737 promoting effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 19
- 239000001257 hydrogen Substances 0.000 description 9
- 229910052739 hydrogen Inorganic materials 0.000 description 9
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 230000008676 import Effects 0.000 description 4
- 238000005496 tempering Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 150000002431 hydrogen Chemical class 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 230000036632 reaction speed Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
The invention relates to the technical field of jet propulsion, and provides a rotational flow micro-mixing nozzle and a combustion chamber, wherein the rotational flow micro-mixing nozzle comprises: the gas channel comprises a straight pipe section and a contracted section, a fuel inlet is arranged at the first end of the straight pipe section, and the fuel inlet is used for introducing fuel; the second end of the straight pipe section is communicated with the first end of the contraction section, and the second end of the contraction section is formed as an outlet of the gas channel; the pipe wall of the straight pipe section is obliquely provided with an oxidant inlet to form a rotational flow channel, and the rotational flow channel is used for guiding the flow of the oxidant so as to promote the mixing of the fuel and the oxidant. According to the invention, the oxidant inlet is obliquely arranged on the wall of the straight pipe section, so that the oxidant enters the gas channel through the oxidant inlet to generate rotational flow to guide the oxidant to flow, so that the fuel is fully mixed in the flowing process of the oxidant, the stability is good, the occurrence of a high-temperature area is avoided, and the micro-mixed combustion No is reduced x Is discharged from the reactor; by arranging the outlet at the contraction section, the jet flow speed is increased, and the combustion backfire air is reducedDangerous and high in safety.
Description
Technical Field
The invention relates to the technical field of jet propulsion, in particular to a rotational flow micro-mixing nozzle and a combustion chamber.
Background
In the jet propulsion field, such as aeroengines, both fuel and oxidant are mixed and combusted in a combustion chamber to power an aircraft with high temperature fuel gas. Thus, the nozzle mixing design and combustion organization within the combustion chamber is critical in determining the jet propulsion performance of the aircraft. The traditional equipment mainly uses hydrocarbon fuel as a main raw material, but under the traction of a low-carbon clean target, flexible combustion mainly using hydrogen becomes an important trend of future fuel. Because of the extremely fast reaction speed of hydrogen and the high flame temperature, the conventional combustion chamber and nozzle have difficulty in directly burning hydrogen, the tempering risk is increased, the combustion instability risk is increased, the mixing uniformity is also affected, and a new combustion mode must be considered. The micro-mixed combustion technology realizes ultralow emission by reducing the mixing scale of fuel and air and enhancing the uniformity of an outlet, and meanwhile, the high-speed jet flow of the outlet has strong backfire resistance and flexible fuel adaptability.
The fuel and air in the micro-mixed burner are mixed in the form of cross jet flow or coaxial jet flow, and the micro-mixed burner generally does not have an air or fuel swirl structure, so that the micro-mixed burner has the advantages of inhibiting backfire and self-ignition, and particularly, the micro-mixed burner becomes one of possible choices for realizing dry low-emission combustion for hydrogen-rich fuel with higher flame propagation speed. The micro nozzle in the micro mixed combustion chamber can effectively control the appearance of flame, reduce the size of flame, shorten the residence time in a high temperature area and realize low nitrogen emission, and can greatly reduce carbon emission if clean energy such as hydrogen is used as fuel.
The traditional natural gas combustion chamber cannot realize the safe and efficient combustion of flexible fuel mainly comprising hydrogen fuel. The current developed micro-mixed combustion technology can realize hydrogen fuel combustion, but has the disadvantages of poor low-load stability, insufficient high-efficiency working load range, easy combustion oscillation of flame and NO x The emission is more.
Disclosure of Invention
The invention provides a swirl micro-mixing nozzle and a combustion chamber, which are used for solving the problems that in the prior art, a micro-mixing combustion technology has poor flexible fuel low-load stability and an insufficient high-efficiency working load range in the combustion process, and the flame is easy to generate combustion oscillation and NO x And more emissions are a problem.
The invention provides a rotational flow micro-mixing nozzle, comprising: the gas channel comprises a straight pipe section and a contracted section, wherein a fuel inlet is formed in the first end of the straight pipe section and used for introducing fuel; the second end of the straight pipe section is communicated with the first end of the contraction section, and the second end of the contraction section is formed as an outlet of the gas channel; the wall of the straight pipe section is obliquely provided with an oxidant inlet to form a rotational flow channel, and the rotational flow channel is used for guiding the flow of the oxidant and promoting the mixing of the fuel and the oxidant.
According to the swirl micro-mixing nozzle provided by the invention, a plurality of oxidant inlets are arranged at intervals along the circumferential direction of the straight pipe section; and/or a plurality of oxidant inlets are arranged at intervals along the axial direction of the straight pipe section.
According to the swirl micro-mixing nozzle provided by the invention, a plurality of oxidant inlets are arranged, and the oxidant inlets are spirally distributed along the central axis of the straight pipe section.
According to the swirl micro-mixing nozzle provided by the invention, the axial screw pitch of the oxidant inlet is 5-20mm, and the rotation angle of the oxidant inlet is 30-180 degrees.
According to the swirl micro-mixing nozzle provided by the invention, the cross section of the oxidant inlet is at least one of round, oval and polygonal.
According to the swirl micro-mixing nozzle provided by the invention, an intersection point exists between the central axis of the oxidant inlet and the inner wall of the straight pipe section, the center of the straight pipe section and the intersection point form a radius line, and an included angle exists between the radius line and the central axis of the oxidant inlet and is 0-60 degrees.
According to the swirl micro-mixing nozzle provided by the invention, the distance between the central axis of the fuel inlet and the central axis of the straight pipe section is 0-0.4 times of the diameter of the straight pipe section.
According to the swirl micro-mixing nozzle provided by the invention, a plurality of fuel inlets are arranged, and the distance between the central axes of two adjacent fuel inlets is 0.1-0.6 times of the diameter of the straight pipe section.
The invention also provides a combustion chamber comprising a plurality of the swirl micro-mixing nozzles.
According to the combustion chamber provided by the invention, the combustion chamber further comprises a fuel buffer box, and a plurality of swirl micro-mixing nozzle arrays are distributed on the fuel buffer box.
According to the swirl micro-mixing nozzle and the combustion chamber, the fuel inlet is arranged at the first end of the straight pipe section, and fuel enters the gas channel through the fuel inlet; through setting up the oxidant import at the pipe wall slope of straight tube section, the oxidant enters into in the gas passage through the oxidant import, produces the whirl, and guide the oxidant flows, makes the fuel carry out intensive mixing in the oxidant flow process, can improve the mixing efficiency of the great fuel of density gap and oxidant, and stability is good, avoids high temperature zone to appear to reduce micro-mixed combustion No x Is discharged from the reactor; through the communication of the contraction section and the straight pipe section, and the arrangement of the outlet in the contraction section, the jet flow speed is increased, so that the combustion tempering risk is reduced, the flame structure is changed, the combustion characteristic and the emission are improved, and the safety performance is high.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a swirl micro-mixing nozzle according to the present invention;
FIG. 2 is a front view of the swirl micro-mixing nozzle of FIG. 1 provided by the present invention;
FIG. 3 is a cross-sectional view of the swirl micro-mixing nozzle of FIG. 1 provided by the present invention;
FIG. 4 is a schematic diagram of a second embodiment of the present invention;
FIG. 5 is a third schematic view of a swirl micro-mixing nozzle according to the present invention;
FIG. 6 is a schematic diagram of a swirl micro-mixing nozzle according to the present invention;
FIG. 7 is a schematic diagram of a swirl micro-mixing nozzle according to the present invention;
FIG. 8 is a cross-sectional view of the swirl micro-mixing nozzle of FIG. 5 provided by the present invention;
FIG. 9 is one of the front views of the swirl micro-mixing nozzle provided by the present invention;
FIG. 10 is a top view of a swirl micro-mixing nozzle provided by the present invention;
FIG. 11 is a second front view of a swirl micro-mixing nozzle provided by the present invention;
FIG. 12 is a third front view of a swirl micro-mixing nozzle provided by the present invention;
FIG. 13 is a front view of a swirl micro-mixing nozzle provided by the present invention;
FIG. 14 is a fifth front view of a swirl micro-mixing nozzle provided by the present invention;
FIG. 15 is a cross-sectional view of a swirl micro-mixing nozzle provided by the present invention;
FIG. 16 is one of the schematic illustrations of a first end fuel inlet of a straight pipe section provided by the present invention;
FIG. 17 is a second schematic illustration of a fuel inlet at a first end of a straight tube segment provided by the present invention;
FIG. 18 is a third schematic illustration of a fuel inlet at the first end of a straight tube segment provided by the present invention;
FIG. 19 is a fourth schematic illustration of a first end fuel inlet of a straight pipe section provided by the present invention;
FIG. 20 is a schematic view of a combustion chamber provided by the present invention;
FIG. 21 is a cross-sectional view of the combustion chamber of FIG. 20 provided in accordance with the present invention;
reference numerals:
1: a swirl micro-mixing nozzle; 2: a straight pipe section; 3: a constriction section; 4: a fuel inlet; 5: an oxidant inlet; 6: a radius line; 7: an included angle; 8: a fuel buffer cartridge.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The swirl micro-mixing nozzle and the combustion chamber provided by the invention are described below with reference to fig. 1 to 21.
The present invention provides a swirling micro-mixing nozzle 1 comprising: the gas channel comprises a straight pipe section 2 and a contracted section 3, wherein a fuel inlet 4 is arranged at the first end of the straight pipe section 2, and the fuel inlet 4 is used for introducing fuel; the second end of the straight pipe section 2 is communicated with the first end of the contraction section, and the second end of the contraction section 3 forms an outlet of the gas channel; the pipe wall of the straight pipe section 2 is obliquely provided with an oxidant inlet 5 to form a rotational flow channel which is used for guiding the flow of the oxidant and promoting the mixing of the fuel and the oxidant.
The swirl micro-mixing nozzle 1 provided by the invention comprises a gas channel, wherein the gas channel is of a hollow structure, and the gas channel is also a micro-mixing channel, namely a channel for mixing fuel and oxidant. Specifically, the gas passage includes a straight tube section 2 and a constricted section 3, as shown in fig. 15 and 212 is provided with a fuel inlet 4 at a first end, and fuel enters the gas channel through the fuel inlet 4; the invention also has oxidant inlet 5 on the pipe wall of straight pipe section 2, oxidant inlet 5 is inclined to form a rotational flow channel in the gas channel, oxidant enters the gas channel through the rotational flow channel of oxidant inlet 5, through inclined arrangement of oxidant inlet 5, guide oxidant to flow in rotational flow channel, make fuel mix fully in the flowing process of oxidant, ensure fuel and oxidant mix evenly, offer and mix the effect, avoid the appearance of high-temperature area, thus reduce the micro-mixing combustion No x Is arranged in the air.
Further, the second end of the straight pipe section 2 is communicated with the contraction section 3, wherein the inner diameter of the contraction section 3 gradually decreases along the extending direction from the straight pipe section 2 to the contraction section 3, so that the inner diameter of the first end of the contraction section 3 is larger than the inner diameter of the second end of the contraction section 3, the contraction section 3 is in a contracted shape, an outlet of a gas channel is formed at the second end of the contraction section 3, the jet flow speed is increased, the risk of combustion tempering is reduced, and the safety performance is improved.
According to the swirl micro-mixing nozzle provided by the invention, the fuel inlet is arranged at the first end of the straight pipe section, and the fuel enters the gas channel through the fuel inlet; through setting up the oxidant import at the pipe wall slope of straight tube section, the oxidant enters into in the gas passage through the oxidant import, produces the whirl, and guide the oxidant flows, makes the fuel carry out intensive mixing in the oxidant flow process, can improve the mixing efficiency of the great fuel of density gap and oxidant, and stability is good, avoids high temperature zone to appear to reduce micro-mixed combustion No x Is discharged from the reactor; through the communication of the contraction section and the straight pipe section, and the arrangement of the outlet in the contraction section, the jet flow speed is increased, so that the combustion tempering risk is reduced, the flame structure is changed, the combustion characteristic and the emission are improved, and the safety performance is high.
Referring to fig. 1 and 2, the number of oxidant inlets 5 on the wall of the straight pipe section 2 provided by the invention is multiple, and the multiple oxidant inlets 5 are arranged at intervals along the circumferential direction of the straight pipe section 2; and/or a plurality of oxidant inlets 5 are arranged at intervals along the axial direction of the straight pipe section 2.
M are arranged on the wall of the straight pipe section 2 at intervals along the circumferential direction of the straight pipe section 2, n are arranged at intervals along the axial direction of the straight pipe section 2, wherein n is 1-4, and m is 2-12.
In one embodiment, 2 straight pipe sections 2 are arranged on the pipe wall of the straight pipe section 2 at intervals along the circumferential direction of the straight pipe section 2, and 3 or 4 straight pipe sections 2 are arranged at intervals along the axial direction of the straight pipe section 2.
In another embodiment, 3 straight pipe sections 2 are arranged on the wall of the straight pipe section 2 at intervals along the circumferential direction of the straight pipe section 2, and 3 or 4 straight pipe sections 2 are arranged at intervals along the axial direction of the straight pipe section 2.
The invention provides a straight pipe section 2, wherein a plurality of oxidant inlets 5 are arranged on the wall of the straight pipe section 2, and the oxidant inlets 5 are spirally distributed along the central axis of the straight pipe section 2.
Further, the axial pitch of the oxidant inlet 5 is 5-20mm and the rotation angle of the oxidant inlet 5 is 30-180 °.
In one embodiment, the oxidant inlets 5 on the pipe wall are spirally distributed along the central axis of the straight pipe section 2, wherein the axial distance between the oxidant inlets 5 is 5mm, that is, the distance between the central axes of two adjacent oxidant inlets 5 along the axial direction of the straight pipe section 2 is 5mm, and can be 10mm,15mm or 20mm.
Further, the rotation angle of the oxidant inlet 5 may be 90 °,120 °,180 °.
The invention forms a plurality of swirl channels by arranging a plurality of oxidant inlets 5 on the pipe wall of the straight pipe section 2, and the oxidant enters the gas channel through the swirl channels to be fully mixed with fuel, so that the fuel and the oxidant are ensured to be uniformly mixed, the mixing effect is provided, the occurrence of a high temperature area is avoided, and the micro-mixed combustion No is reduced x Is arranged in the air.
The number and arrangement form of the oxidant inlets 5 obliquely arranged on the pipe wall of the straight pipe section 2 are not particularly limited, and may be defined according to the physical characteristics and actual flow rates of the fuel and the oxidant.
On the basis of the above-described embodiment, the cross-sectional shape of the oxidizer inlet 5 in the present invention is at least one of a circle, an ellipse, and a polygon.
In one embodiment, the pipe wall of the straight pipe section 2 is provided with a plurality of oxidant inlets 5, and the cross section of the oxidant inlets 5 is circular, as shown in fig. 1, 2, 5, 6, 7, 9 and 13, the diameter of the oxidant inlets 5 is 1-6mm, can be 1mm, can be 3mm and can be 6mm; the diameters of the plurality of oxidant inlets 5 are not particularly limited, and may be the same or different.
In another embodiment, a plurality of oxidant inlets 5 are provided on the pipe wall of the straight pipe section 2, and the cross-sectional shape of the plurality of oxidant inlets 5 is elliptical, as shown in fig. 14, the major and minor diameters of the ellipse are 1-6mm, for example, the major diameter is 5mm, and the minor diameter is 1mm. The invention is not particularly limited with respect to the dimensions of the long diameter and the short diameter; and the sizes of the ellipses may be the same or different.
In yet another embodiment, a plurality of oxidant inlets 5 are arranged on the pipe wall of the straight pipe section 2, the cross section of the oxidant inlets 5 is rectangular, as shown in fig. 4 and 11, the length of the oxidant inlets 5 is 1-8mm, and the width of the oxidant inlets 5 is 0.5-5mm; for example, the oxidant inlet 5 has a length of 8mm and a width of 5mm; alternatively, the oxidant inlet 5 has a length of 1mm and a width of 0.5mm.
In addition, the cross section of the oxidant inlets 5 arranged on the wall of the straight pipe section 2 provided by the invention can be round or elliptical, or round or polygonal, or elliptical or polygonal, and the polygonal is not limited to rectangle, but also triangle (as shown in fig. 12), pentagon, hexagon and the like.
Referring to fig. 3, 8 and 10, an intersection point exists between the central axis of the oxidant inlet 5 and the inner wall of the straight pipe section 2, the center of the straight pipe section 2 and the intersection point form a radius line 6, an included angle 7 exists between the radius line 6 and the central axis of the oxidant inlet 5, and the included angle 7 is 0-60 degrees.
The invention is characterized in that an oxidant inlet 5 is obliquely arranged on a straight pipe section 2, wherein an intersection point exists between the central axis of the oxidant inlet 5 and the straight pipe section 2, a connecting line between the center of the straight pipe section 2 and the intersection point is a radius line 6, an included angle 7 exists between the radius line 6 and the central axis of the oxidant inlet 5, and the included angle 7 can be 0 degree, namely, the radius line 6 coincides with the central axis of the oxidant inlet 5; the included angle 7 may be 30 °, 60 °, etc.
In the present inventionThe included angle 7 between the radius line 6 and the central axis of the oxidant inlet 5 is set according to the actual situation, the swirl number generated by the swirl channel is adjusted, so that the oxidant and the fuel are fully mixed, the fuel and the oxidant are ensured to be uniformly mixed, the mixing effect is provided, the occurrence of a high temperature area is avoided, and the micro-mixed combustion No is reduced x Is arranged in the air.
Referring to fig. 16, further, the distance between the central axis of the fuel inlet 4 and the central axis of the straight pipe section 2 is 0 to 0.4 times the diameter of the straight pipe section 2.
Referring to fig. 4, the diameter of the straight pipe section 2 is d, and the fuel inlet 4 is disposed at the center of the first end of the straight pipe section 2, that is, the central axis of the fuel inlet 4 coincides with the central axis of the straight pipe section 2, and the interval between the central axis of the fuel inlet 4 and the central axis of the straight pipe section 2 is 0.
Referring to fig. 16, the straight pipe section 2 has a diameter d, a fuel inlet 4 is provided at a first end of the straight pipe section 2, and a distance between a central axis of the fuel inlet 4 and a central axis of the straight pipe section 2 is 0.4d, or may be 0.2d,0.3d, or the like.
Further, referring to fig. 17, 18 and 19, the number of the fuel inlets 4 is plural, and the space between the central axes of two adjacent fuel inlets 4 is 0.1 to 0.6 times the diameter of the straight pipe section 2.
Referring to fig. 19, in the present invention, 4 fuel inlets 4 are provided at the first end of the straight pipe section 2, the 4 fuel inlets 4 are equally distributed at the first end of the straight pipe section 2 along the circumferential direction of the central axis of the straight pipe section 2, the distances between the central axes of the 4 fuel inlets 4 and the central axis of the straight pipe section 2 are equal, and the distance between the central axes of any two adjacent fuel inlets 4 is 0.1d, or may be 0.3d,0.6d, etc.
The number of the fuel inlets 4 is not particularly limited, and may be 1 to 4, and the positions of the fuel inlets 4 are not particularly limited, and the positional relationship between each fuel inlet 4 and the central axis of the straight pipe section 2 may be the same or different, and may be limited according to practical situations.
The invention adopts the rotational flow micro-mixing nozzle 1, can improve the mixing uniformity degree of the oxidant and the fuel through a plurality of oxidant inlets 5, and simultaneously the oxidant is inclinedThe obliquely arranged oxidant inlets 5 can form rotational flow, so that the mixing efficiency of the oxidant with larger density difference and the fuel can be enhanced, the occurrence of a high-temperature area is reduced, and the NO combustion is effectively reduced x And the emission effectively changes the flame structure and improves the combustion characteristics and the emission.
According to the physicochemical properties of the fuel and the oxidant, the invention can adjust the parameters of the distribution of the fuel inlet 4, the shape, the number, the distribution form and the like of the oxidant inlet 5.
Referring to fig. 20-21, the present invention also provides a combustion chamber comprising a plurality of swirl micro-mixing nozzles 1 according to any of the embodiments described above.
The combustion chamber utilizes the swirl micro-mixing nozzle 1 to fully mix fuel and oxidant, the oxidant flows in the swirl channel, so that the fuel is fully mixed in the flowing process of the oxidant, the fuel and the oxidant are ensured to be uniformly mixed, the fuel and the oxidant are sprayed out through the contraction section 3, the flexible fuel is prevented from being burned and tempered, the flame structure is changed, and the combustion characteristic and the emission are improved.
Further, the combustion chamber of the present invention further comprises a fuel buffer box 8, and a plurality of swirl micro-mixing nozzles 1 are distributed on the fuel buffer box 8 in an array.
It is to be understood that the swirling micro-mixing nozzle 1 is further provided with a mounting structure, the mounting structure comprises a mounting plate and a mounting frame, one end of the mounting frame is connected with the fuel buffer box 8, the other end of the mounting frame is connected with the mounting plate, a plurality of mounting holes are formed in the mounting plate, the mounting holes are provided with internal threads, the peripheral wall of the inlet end of the swirling micro-mixing nozzle 1 is provided with external threads, the inlet end of the swirling micro-mixing nozzle 1 is in threaded connection with the mounting plate through the internal threads and the external threads, the swirling micro-mixing nozzle 1 is arranged on the mounting plate in an array manner, such as 4×4 distribution, the combustion chamber further comprises fuel nozzles, the fuel nozzles are arranged on one side of the fuel buffer box 8 and are arranged opposite to the swirling micro-mixing nozzle 1.
The mounting plate of this embodiment provides fixed support for whirl micro-mixing nozzle 1, and the mounting bracket provides the interval space of relative setting for fuel nozzle and micro-mixing nozzle, the entry end of the little mixing nozzle 1 of fuel admission whirl of being convenient for.
The fuel flows into the fuel buffer box 8, is injected into the swirl micro-mixing nozzle 1 through the fuel nozzle, forms a spraying airflow at the fuel inlet of the straight pipe section 2, and is mixed with the fuel after entering the swirl micro-mixing nozzle 1 due to the fact that the environment outside the combustion chamber is filled with the oxidant and the negative pressure environment formed by the fuel airflow causes the oxidant to be sucked into the oxidant inlet 5 of the straight pipe section 2.
The fuel in the invention can be flexible fuel, such as hydrogen, and the oxidant can be oxygen or air.
For flexible fuel such as hydrogen, the present embodiment can reduce pressure pulsation of the fuel and suppress unstable combustion of the fuel by providing the fuel buffer cartridge 8. The size of the fuel buffer box 8 can be designed according to specific working conditions and the number of arrays of the swirl micro-mixing nozzles 1.
The combustion chamber provided by the invention can be used for an aero-engine combustion chamber of jet propulsion, or an aero-retrofit gas turbine and a heavy-duty gas turbine.
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 swirl micro-mixing nozzle, comprising: the gas channel comprises a straight pipe section and a contracted section, wherein a fuel inlet is formed in the first end of the straight pipe section and used for introducing fuel; the second end of the straight pipe section is communicated with the first end of the contraction section, and the second end of the contraction section is formed as an outlet of the gas channel;
the wall of the straight pipe section is obliquely provided with an oxidant inlet to form a rotational flow channel, and the rotational flow channel is used for guiding the flow of the oxidant and promoting the mixing of the fuel and the oxidant.
2. The swirl micro-mixing nozzle of claim 1, wherein the oxidant inlets are a plurality of, the oxidant inlets being spaced apart along the circumference of the straight tube section;
and/or a plurality of oxidant inlets are arranged at intervals along the axial direction of the straight pipe section.
3. The swirl micro-mixing nozzle of claim 1, wherein the oxidant inlets are a plurality of the oxidant inlets being helically distributed along a central axis of the straight tube section.
4. A swirl micro-mixing nozzle according to claim 3, characterised in that the axial pitch of the oxidant inlet is 5-20mm and the rotation angle of the oxidant inlet is 30-180 °.
5. The swirl micro-mixing nozzle of any one of claims 1-4, wherein the oxidant inlet has a cross-sectional shape that is at least one of circular, elliptical, and polygonal.
6. The swirl micro-mixing nozzle of claim 5, wherein the central axis of the oxidant inlet is at an intersection with the inner wall of the straight tube section, the center of the straight tube section and the intersection form a radius line, and an included angle is formed between the radius line and the central axis of the oxidant inlet, and the included angle is 0-60 °.
7. The swirl micro-mixing nozzle of claim 1, wherein a spacing between a central axis of the fuel inlet and a central axis of the straight tube segment is 0-0.4 times a diameter of the straight tube segment.
8. The swirl micro-mixing nozzle according to claim 1, wherein a plurality of fuel inlets are provided, and a distance between two adjacent central axes of the fuel inlets is 0.1-0.6 times of a diameter of the straight pipe section.
9. A combustion chamber comprising a plurality of swirl micro-mixing nozzles as claimed in any one of claims 1 to 8.
10. The combustor of claim 9, further comprising a fuel buffer cartridge, a plurality of said swirl micro-mixing nozzle arrays being distributed on said fuel buffer cartridge.
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