CN116697405A - Premixing rotational flow micro-mixing nozzle and combustion chamber - Google Patents
Premixing rotational flow micro-mixing nozzle and combustion chamber Download PDFInfo
- Publication number
- CN116697405A CN116697405A CN202310634678.4A CN202310634678A CN116697405A CN 116697405 A CN116697405 A CN 116697405A CN 202310634678 A CN202310634678 A CN 202310634678A CN 116697405 A CN116697405 A CN 116697405A
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- Prior art keywords
- swirl
- inlet
- premixing
- tube
- premix
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- 238000002156 mixing Methods 0.000 title claims abstract description 71
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 45
- 239000000446 fuel Substances 0.000 claims abstract description 82
- 239000007800 oxidant agent Substances 0.000 claims abstract description 60
- 230000001590 oxidative effect Effects 0.000 claims abstract description 60
- 230000000087 stabilizing effect Effects 0.000 claims description 9
- 239000000411 inducer Substances 0.000 claims description 7
- 239000007789 gas Substances 0.000 abstract description 51
- 230000000694 effects Effects 0.000 abstract description 17
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 abstract description 12
- 239000001257 hydrogen Substances 0.000 description 8
- 229910052739 hydrogen Inorganic materials 0.000 description 8
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 5
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 3
- 230000009471 action Effects 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 229910002091 carbon monoxide Inorganic materials 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 150000002431 hydrogen Chemical class 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000005496 tempering Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 239000000126 substance Substances 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
- F23R3/28—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
-
- 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
Abstract
The invention relates to the technical field of jet propulsion, and provides a premixing rotational flow micro-mixing nozzle and a combustion chamber. The premixing rotational flow micro-mixing nozzle comprises a premixing pipe and a rotational flow guide piece; the premixing tube is provided with a first end and a second end, the first end of the premixing tube is provided with a first inlet, the side wall of the premixing tube is provided with a plurality of second inlets, and the second end of the premixing tube is provided with a mixed gas outlet; the second inlets are arranged along the circumferential direction of the premix tube, and each second inlet extends to the central axis of the premix tube; the swirl flow guide piece is arranged in the premixing tube, and a swirl channel is defined between the swirl flow guide piece and the inner wall of the premixing tube; the plurality of second inlets are positioned between the first inlets and the swirl flow guide member along the extending direction from the first end to the second end. According to the invention, the fuel and the oxidant are premixed based on the premixing pipe, and then the fuel and the oxidant are guided to flow along the swirl channel through the swirl guide piece, so that the mixing uniformity of the fuel and the oxidant in the combustion process is improved, the combustion effect is improved, and the emission of nitrogen oxides in the combustion process is reduced.
Description
Technical Field
The invention relates to the technical field of jet propulsion, in particular to a premixing rotational flow micro-mixing nozzle and a combustion chamber.
Background
In the jet propulsion field, such as rocket engines or aeroengines, both fuel and oxidant are mixed and combusted in a combustion chamber, providing high temperature fuel gas as power for the aircraft. Thus, the nozzle mixing design and combustion organization within the combustion chamber is critical in determining the jet propulsion performance of the aircraft. In the future low-carbon clean energy ecological system, the application of flexible fuels such as hydrogen as a main fuel and mixed other fuels or carbon monoxide is a main trend of realizing low-carbon and even zero-carbon emission. Due to the active chemical properties of flexible fuels such as hydrogen, carbon monoxide and the like, the problem of spontaneous combustion tempering oscillation caused by directly using hydrogen fuel in the traditional combustion chamber is remarkable, and a new combustion technology is needed.
The micro-mixed combustion technology has flashback resistance and flexible fuel adaptability through reducing the mixing scale of fuel and oxidant, and becomes one of possible choices for realizing stable and safe combustion especially for hydrogen-rich fuel with higher flame propagation speed.
The traditional combustion chamber cannot realize safe and efficient combustion of flexible fuel mainly comprising hydrogen fuel. The existing micro-mixed combustion technology can realize the combustion of flexible fuel, but the problem that the combustion effect is not ideal due to the fact that the mixing of reaction components is not uniform and the emission is not ideal easily occurs in the combustion process of flexible fuel still exists. The premixed swirl micro-mixing nozzle and the combustion chamber provided by the invention can be used for high-efficiency low-emission combustion of flexible fuel (comprising pure hydrogen) mainly comprising hydrogen, and can be used for an aeroengine combustion chamber of jet propulsion, or an aero-retrofit gas turbine and a heavy gas turbine.
Disclosure of Invention
The invention provides a premixing swirl micro-mixing nozzle and a combustion chamber, which are used for solving the problems that the micro-mixing nozzle of the existing combustion chamber is difficult to fully mix fuel and oxidant and has poor combustion effect.
In a first aspect, the present invention provides a premix swirl micro-mixing nozzle comprising: a premixing tube and a swirl flow guide member;
the premixing tube is provided with a first end and a second end, the first end of the premixing tube is provided with a first inlet for introducing an oxidant, the side wall of the premixing tube is provided with a plurality of second inlets for introducing fuel, and the second end of the premixing tube is provided with a mixed gas outlet;
the second inlets are arranged along the circumferential direction of the premix tube, and each second inlet extends to the central axis of the premix tube;
the swirl flow guide piece is arranged in the premixing tube, and a swirl channel is defined between the swirl flow guide piece and the inner wall of the premixing tube;
wherein, along the extending direction from the first end to the second end, the plurality of second inlets are located between the first inlet and the swirl flow guide.
According to the premixing cyclone micro-mixing nozzle provided by the invention, the second inlet is provided with an extension pipeline;
one end of the extension pipeline is communicated with the air outlet end of the second inlet, and the other end of the extension pipeline extends into the premixing tube along the axial direction of the second inlet.
According to the premixing rotational flow micro-mixing nozzle provided by the invention, the second inlets are uniformly distributed circumferentially relative to the central axis of the premixing tube.
According to the premixing swirl micro-mixing nozzle provided by the invention, at least one of the second inlets is inclined towards one side of the swirl flow guide piece and extends towards the central axis of the premixing tube.
According to the premixing rotational flow micro-mixing nozzle provided by the invention, the first end of the premixing tube is also provided with a third inlet for introducing fuel;
the first inlets are arranged in a plurality, the first inlets are arranged around the third inlets, or the third inlets are arranged in a plurality, and the third inlets are arranged around the first inlets.
According to the premixing cyclone micro-mixing nozzle provided by the invention, the cyclone flow guide piece comprises cyclone blades; the swirl blades are arranged in a spiral line track extending mode relative to the central axis of the premixing tube, so that a swirl channel is formed between the swirl blades and the inner wall of the premixing tube.
The invention provides a premixing rotational flow micro-mixing nozzle, which further comprises: a direct current guide member;
the direct current guide piece is arranged in the premixing tube, and a direct current channel is defined between the direct current guide piece and the inner wall of the premixing tube;
and the direct current guide piece is arranged between the rotational flow guide piece and the mixed gas outlet along the extending direction from the first end to the second end.
According to the premixing rotational flow micro-mixing nozzle provided by the invention, the direct current guide piece comprises a plurality of guide sheets;
the guide plates are connected with each other, and each guide plate is parallel to or coplanar with the central axis of the premixing tube; the flow guide sheets and/or at least two of the flow guide sheets and the inner wall of the premixing tube define the direct current channel.
According to the premixing swirl micro-mixing nozzle provided by the invention, the center distance between the first inlet and the second inlet is 1-2 times of the diameter of the second inlet along the axial direction of the premixing tube, the distance between the center of the second inlet and the inlet end of the swirl flow guide piece is 1-3 times of the diameter of the second inlet, the distance between the outlet end of the swirl flow guide piece and the direct flow guide piece is 3-10 times of the diameter of the second inlet, and the diameter of the mixed gas outlet is 0.6-1 times of the diameter of the second inlet.
In a second aspect, the present invention also provides a combustion chamber comprising: a valve seat and a plurality of premixing swirl micro-mixing nozzles as claimed in any one of the preceding claims;
the air distribution seat is provided with an air inlet and a pressure stabilizing cavity communicated with the air inlet, and the air inlet is used for introducing an oxidant; a plurality of gas nozzles are arranged on one side surface of the gas distribution seat, the gas nozzles are communicated with the pressure stabilizing cavity, and the gas nozzles are communicated with the first inlets of the premixing cyclone micro-mixing nozzles in a one-to-one correspondence mode.
According to the premixing swirling micro-mixing nozzle and the combustion chamber, the premixing pipe and the swirling flow guide piece are arranged on the premixing swirling flow micro-mixing nozzle, the oxidant is introduced into the first end of the premixing pipe through the first inlet, meanwhile, the fuel is simultaneously introduced into the premixing pipe through the plurality of second inlets on the side wall of the premixing pipe, the fuel introduced in different directions simultaneously forms impact on the oxidant flowing along the central axis of the premixing pipe, so that the fuel and the oxidant are premixed based on the premixing pipe, and then the fuel and the oxidant are guided to flow along the swirling flow channel in the premixing pipe through the swirling flow guide piece, so that the mixing uniformity of the fuel and the oxidant in the combustion process is improved, the combustion effect is improved, and the emission of nitrogen oxides in the combustion process is reduced.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic perspective view of a premixing swirl micro-mixing nozzle provided by the invention;
FIG. 2 is one of the schematic cross-sectional structural views of the premix swirl micro-mixing nozzle provided by the invention;
FIG. 3 is a second schematic cross-sectional view of a premix swirl micro-mixing nozzle according to the present invention;
FIG. 4 is a schematic view of a swirl flow guide member according to the present invention;
FIG. 5 is a second schematic view of a swirl flow guide member according to the present invention;
FIG. 6 is a schematic view of a DC flow guide according to the present invention;
FIG. 7 is a second schematic structural view of the DC diversion member according to the present invention;
FIG. 8 is a third schematic structural view of the DC guide member according to the present invention;
FIG. 9 is a schematic view of a combustion chamber based on a premixed swirl micro-mixing nozzle according to one embodiment of the present invention;
FIG. 10 is a second schematic view of a combustion chamber based on a premixed swirl micro-mixing nozzle according to the present invention;
FIG. 11 is a schematic view of the A-A structure of FIG. 10 provided by the present invention.
Reference numerals:
1. a premixing swirl micro-mixing nozzle; 11. a premix tube; 111. a first inlet; 1110. extending the pipeline; 112. a second inlet; 113. a mixed gas outlet; 12. a swirl flow guide; 121. swirl vanes; 13. a direct current guide member; 131. a deflector;
2. a gas distribution seat; 21. an air inlet; 22. a pressure stabilizing cavity; 23. a gas nozzle.
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 premixed swirling micro-mixing nozzle and the combustion chamber provided by the embodiment of the invention are described in detail below by means of specific embodiments and application scenes thereof with reference to fig. 1 to 11.
In a first aspect, as shown in fig. 1 to 3, an embodiment of the present invention provides a premixed swirling micro-mixing nozzle 1, which includes a premix tube 11 and a swirling flow guide 12.
The premix tube 11 has a first end and a second end, the first end of the premix tube 11 is provided with a first inlet 111 for introducing an oxidant, the sidewall of the premix tube 11 is provided with a plurality of second inlets 112 for introducing fuel, and the second end of the premix tube 11 is provided with a mixed gas outlet 113. The shape of the second inlet 112 may be circular, triangular, rectangular, etc., which is not particularly limited.
The second inlets 112 are arranged along the circumferential direction of the premix tube 11, and each second inlet 112 extends to the central axis of the premix tube 11; the swirl flow guide member 12 is arranged in the premix tube 11, a swirl channel is defined between the swirl flow guide member 12 and the inner wall of the premix tube 11, and the swirl channel extends in a spiral track relative to the central axis of the premix tube 11.
Wherein, along the extending direction from the first end to the second end, a plurality of second inlets 112 are located between the first inlets 111 and the swirl flow guide member 12.
It will be appreciated that a gas passage is axially provided in the premix tube 11, the gas passage being formed between the first and second ends of the premix tube 11, with the first inlet 111, the second inlet 112 and the mixed gas outlet 113 communicating with the gas passage, respectively.
Meanwhile, the fuel shown in this embodiment may be flexible fuel such as hydrogen, carbon monoxide, etc., and the oxidant may be air or high-purity oxygen.
In this embodiment, the plurality of second inlets 112 are arranged along the circumferential direction of the premix tube 11, and each second inlet 112 extends to the central axis of the premix tube 11, so that the fuel introduced by each second inlet 112 can be introduced into the premix tube 11 in different directions along the circumferential direction, so as to impact the oxidant flowing at a high speed in the premix tube 11, realize the expanded blending of the fuel with relatively low density into the oxidant with relatively high density, and improve the blending effect of the fuel and the oxidant.
Further, after the fuel and the oxidant are primarily blended, along with the transportation of the mixed gas formed by the fuel and the oxidant to the position of the swirl flow guide member 12, the mixed gas flows along the swirl flow channel under the guidance of the swirl flow guide member 12, so that the fuel and the oxidant in the mixed gas are further promoted to be mixed, the mixing uniformity of the fuel and the oxidant is improved, the blending effect is further improved, and the follow-up better combustion effect is facilitated.
In practical applications, the premix tube 11 may be configured to include a first tube segment and a second tube segment, where the first tube segment and the second tube segment are in communication along an extending direction from the first end to the second end of the premix tube 11. The first inlet 111 is arranged at one end of the first pipe body section far away from the second pipe body section, the plurality of second inlets 112 are circumferentially arranged on the side wall of the first pipe body section, the mixed gas outlet 113 is arranged at one end of the second pipe body section far away from the first pipe body section, the swirl flow guide 12 is arranged in the first pipe body section, and a swirl flow channel is defined between the swirl flow guide 12 and the inner wall of the first pipe body section.
Wherein, along the extending direction from the first end to the second end of the premix tube 11, the inner diameters of all parts of the first tube body section are the same, and the inner diameter of the second tube body section is in a contracted shape.
Thus, the design of this embodiment based on the second body section can change the flow field of the mixed gas that fuel and oxidant are constituteed based on the second body section, can improve the jet velocity of mixed gas, is favorable to reducing the burning tempering risk, improves the security performance.
In some examples, the first pipe section of the premix pipe 11 described above may be further configured to include a tapered pipe section, a throat pipe section, and a diverging pipe section; the gradually-reduced pipe section, the throat pipe section and the gradually-expanded pipe section are sequentially communicated, and one end of the gradually-expanded pipe section, which is far away from the throat pipe section, is communicated with the second pipe body section.
Wherein, the convergent pipe section, the throat pipe section and the divergent pipe section form a Laval nozzle structure, and the first inlet 111 is arranged on the end face of one end of the convergent pipe section far away from the throat pipe section; the second inlets 112 are circumferentially distributed on the side wall of the tapered pipe section, and the swirl inducer 12 is disposed on the throat section.
Thus, in this embodiment, by configuring the first pipe section as a laval nozzle structure, after premixing the fuel and the oxidant in the tapered pipe section, it is ensured that the mixed gas formed by the fuel and the oxidant flows into the throat section at a high speed, and flows along the swirl channel in a swirling manner under the guidance of the swirl guide member 12 in the throat section, and then the mixed gas flowing in the swirling manner is dispersed under the action of the tapered pipe section, so as to achieve the effect of racemizing the mixed gas until the mixed gas is ejected from the second pipe section at a high speed.
As can be seen from the above, according to the present invention, by configuring the premixing tube 11 and the swirl flow guide 12 to the premixing swirl micro-mixing nozzle, while the oxidant is introduced into the first end of the premixing tube 11 through the first inlet 111, the fuel is simultaneously introduced into the premixing tube 11 through the plurality of second inlets 112 on the side wall of the premixing tube 11, so that the fuel introduced in different directions simultaneously forms impact on the oxidant flowing along the central axis of the premixing tube 11, so as to premix the fuel and the oxidant based on the premixing tube 11, and then the fuel and the oxidant are guided to flow along the swirl channel in the premixing tube 11 through the swirl flow guide 12, so that the mixing uniformity of the fuel and the oxidant in the combustion process is improved, the combustion effect is improved, and the emission of nitrogen oxides in the combustion process is reduced.
In some embodiments, as shown in fig. 3, the second inlet 112 of the present embodiment is configured with an extension duct 1110; one end of the extension pipe 1110 communicates with the air outlet end of the second inlet 112, and the other end of the extension pipe 1110 extends into the premix tube 11 in the axial direction of the second inlet 112.
It is understood that the second inlet 112 is a circular hole formed in the inner wall of the premix tube 11, the extension pipe 1110 and the second inlet 112 are coaxially disposed, the inner diameter of the extension pipe 1110 is the same as the inner diameter of the second inlet 112, and a plurality of extension pipes 1110 are disposed in a one-to-one opposite manner to the plurality of extension pipes 1110 and the second inlet 112.
In practice, the length of extension pipe 1110 may be determined based on the physical characteristics of the oxidant and fuel, however, it should be ensured that the length of extension pipe 1110 is less than half the inner diameter of premix tube 11.
Since the density of the oxidant is greater than that of the fuel, the momentum of the fuel is relatively small compared to the oxidant, which is somewhat detrimental to the blending of the fuel and the oxidant.
However, in this embodiment, by providing the extension pipe 1110 at the air outlet end of the second inlet 112, the speed of inputting the fuel into the premix pipe 11 can be further improved based on the extension pipe 1110, so as to improve the penetration of the fuel to the oxidant, thereby improving the mixing effect of the fuel and the oxidant, and being beneficial to obtaining better combustion effect of the mixed gas in the following steps.
In some embodiments, as shown in fig. 1 to 3, the second inlets 112 may be configured to be circumferentially and uniformly distributed with respect to the central axis of the premix tube 11, so as to ensure that the fuel introduced in different directions circumferentially impacts the oxidant flowing along the inside of the premix tube 11 uniformly, so as to ensure the mixing effect of the fuel and the oxidant, and ensure that the mixed gas formed by the fuel and the oxidant flows along the axial direction of the premix tube 11 as much as possible, so that the mixed gas is further mixed in a swirling flow manner in the process of further passing through the swirling flow guide member 12.
In order to further ensure the blending effect of the fuel and the oxidant, four second inlets 112 may be specifically configured in this embodiment, and the central angle of two adjacent second inlets 112 is 90 °.
In some embodiments, in order to reduce the impact of the fuel to affect the flow of the mixed gas of the oxidant and the fuel in the premix tube 11, at least one of the plurality of second inlets 112 may be configured to extend obliquely toward one side of the swirl inducer 12 toward the central axis of the premix tube 11.
Alternatively, in this embodiment, each second inlet 112 may be configured to be inclined toward one side of the swirl inducer 12, and the included angle between the central axis of each second inlet 112 and the central axis of the premix tube 11 may be 30 ° to 60 °.
Alternatively, in the case where each of the second inlets 112 is configured with an extension pipe 1110, the length of the extension pipe 1110 corresponding to each of the second inlets 112 may be the same, and the extension pipes 1110 corresponding to the second inlets 112 may be inclined at the same angle toward one side of the swirl flow guide 12.
In some embodiments, to ensure the mixing effect of the fuel and the oxidant, this embodiment may also be provided with a third inlet for introducing fuel at the first end of the premix tube 11.
Alternatively, the present embodiment may provide a plurality of first inlets 111, and a plurality of first inlets 111 may be provided around the third inlet. In practical application, in the case of introducing fuel into the premix tube 11 through the third inlet, the oxidant layer can be formed on the periphery of the fuel at the central position based on the fuel introduced through the plurality of first inlets 111, and the fuel layer can be formed on the periphery of the oxidant layer based on the fuel introduced through the plurality of second inlets 112, so that the fuel-oxidant-fuel layer-by-layer distribution is realized, and the blending effect of the fuel and the oxidant is improved.
Alternatively, the present embodiment may also provide a plurality of third inlets disposed around the first inlet 111. In practical application, in the case of introducing the oxidant into the premix tube 11 through the first inlet 111, the first fuel layer can be formed on the periphery of the oxidant at the center based on the fuel introduced through the plurality of third inlets, and the second fuel layer can be formed on the periphery of the first fuel layer based on the fuel introduced through the plurality of second inlets 112, so that the oxidant-fuel layer-by-layer distribution is realized, and the blending effect of the fuel and the oxidant is also improved.
In some embodiments, as shown in fig. 2 and 3, the swirl inducer 12 includes swirl vanes 121; the swirl vanes 121 are disposed in a spiral path extending with respect to the central axis of the premix tube 11 such that a swirl passage is formed between the swirl vanes 121 and the inner wall of the premix tube 11, the swirl passage extending in a spiral path with respect to the central axis of the premix tube 11.
The angle of the swirl vane 121 twisted along the spiral line track may be 45 ° to 180 °, and the pitch of the swirl vane 121 may be 1.5 to 6 times of the inner diameter of the first pipe section corresponding to the premix pipe 11.
As shown in fig. 4, the swirl inducer 12 may be a single swirl vane 121.
As shown in fig. 5, the swirl flow guide member 12 may include two swirl blades 121, where the two swirl blades 121 are disposed at intervals along the axial direction of the premix tube 11, and the interval between the two swirl blades 121 may be 0 to 1.5 times the inner diameter of the first tube segment corresponding to the premix tube 11.
The two swirl blades 121 may be designed in a forward-reverse rotation manner along the axial direction of the premix tube 11, so that after the mixed gas composed of the fuel and the oxidant flows through one forward swirl blade 121, a forward-rotation gas flow around the central axis of the premix tube 11 is formed, and when the forward-rotation gas flow flows through the next reverse swirl blade 121, the direction of swirl guiding is opposite to the forward-rotation gas flow due to the two swirl blades 121, when the forward-rotation gas flow enters the next swirl blade 121, the suddenly changed swirl direction causes the fuel and the oxidant to generate strong impact mixing, so that the fuel and the oxidant are mixed more uniformly.
In some embodiments, as shown in fig. 2 and 3, the premixed swirling micro-mixing nozzle of the present embodiment is further configured with a dc guide 13.
The direct current guide piece 13 is arranged in the premix tube 11, a direct current channel is defined between the direct current guide piece 13 and the inner wall of the premix tube 11, and the direct current channel extends along the axial direction of the premix tube 11. The direct current guide member 13 is disposed between the swirl guide member 12 and the mixed gas outlet 113 along the extending direction from the first end to the second end.
It will be appreciated that, based on the guiding action of the swirl flow guide member 12, the mixed gas of fuel and oxidant flows in the pre-mixing pipe 11 in a predetermined swirl direction while flowing through the swirl flow guide member 12, and rapidly reaches the position of the direct flow guide member 13.
Then, based on the guiding action of the direct current guide piece 13, the mixed gas flowing in the rotational flow flows through the direct current channel so as to realize the elimination of the rotational flow; the mixed gas subjected to the swirling removal treatment is ejected at a high speed through the second pipe body section of the premix pipe 11.
In this embodiment, by providing the dc guide member 13, the swirl strength of the mixed gas output from the swirl guide member 12 can be reduced, so as to reduce ablation caused by the swirl on the inner wall of the premix tube 11, and increase the service life of the premix tube 11.
In some embodiments, the dc guide 13 includes a plurality of guide vanes 131. The guide vanes 131 are connected with each other, and each guide vane 131 is parallel or coplanar with the central axis of the premixing tube 11; a direct flow channel is defined between the plurality of baffles 131 and/or between at least two of the plurality of baffles 131 and the inner wall of the premix tube 11.
As shown in fig. 6, the dc guide 13 is provided with four guide plates 131, and the four guide plates 131 form a "well" structure, so that a dc channel is enclosed between the four guide plates 131, and two adjacent guide plates 131, or three adjacent guide plates 131 and the inner wall of the premix tube 11 may also form a dc channel.
As shown in fig. 7, the dc guide member 13 is provided with two guide plates 131, where the two guide plates 131 are disposed along the same axis and are disposed in a crossed manner according to an included angle of 90 ° to form a cross-shaped structure, and a dc channel is formed between two adjacent guide plates 131 and the inner wall of the premix tube 11.
As shown in fig. 8, the dc guide 13 is provided with three guide plates 131, the three guide plates 131 are disposed along the same axis in a crossing manner, and a dc channel is formed between two adjacent guide plates 131 and the inner wall of the premix tube 11.
Of course, in the case that the dc guide 13 is provided with a plurality of guide vanes 131, the plurality of guide vanes 131 may take other arrangements.
For example, in the case that the direct current guide piece 13 is provided with four guide pieces 131, the four guide pieces 131 may also be disposed along the same axis and intersect at an included angle of 45 ° to form a "m" structure, and a direct current channel is formed between two adjacent guide pieces 131 and the inner wall of the premix tube 11.
Based on the scheme of the above embodiment, as shown in fig. 2, along the axial direction of the premix tube 11, the center distance between the first inlet 111 and the second inlet 112 is 1-2 times the diameter of the second inlet 112, the distance between the center of the second inlet 112 and the inlet end of the swirl flow guide 12 is 1-3 times the diameter of the second inlet 112, the distance between the outlet end of the swirl flow guide 12 and the direct flow guide 13 is 3-10 times the diameter of the second inlet 112, the diameter of the mixed gas outlet 113 is 0.6-1 times the diameter of the second inlet 112, and the total length of the premix tube 11 may be 5-30 times the diameter of the second inlet 112.
In FIG. 2, D1 represents the diameter of the first inlet 111, D2 represents the diameter of the second inlet 112, D represents the diameter of the mixed gas outlet 113, L1 represents the center distance between the first inlet 111 and the second inlet 112, L2 represents the distance between the center of the second inlet 112 and the inlet end of the swirl flow guide 12, L3 represents the distance between the outlet end of the swirl flow guide 12 and the straight flow guide 13, L4 represents the length of the straight flow guide 13 in the axial direction of the premix tube 11, L5 represents the distance between the end of the straight flow guide 13 and the large end of the second tube section corresponding to the premix tube 11, L Total (S) Indicating the total length of the premix tube 11.
According to practical conditions, the diameter of the first inlet 111 may be 4-25mm, the diameter of the second inlet 112 may be 0.5-3mm, the length of the direct current guide member 13 along the axial direction of the premix tube 11 may be 3-20mm, and the distance between the tail end of the direct current guide member 13 and the large opening end of the second tube body section corresponding to the premix tube 11 may be 0-20mm.
In a second aspect, as shown in fig. 9 to 11, an embodiment of the present invention further provides a combustion chamber including: a gas distribution seat 2 and a plurality of premixing swirl micro-mixing nozzles 1 as described in any one of the above.
The air distribution seat 2 is provided with an air inlet 21 and a pressure stabilizing cavity 22 communicated with the air inlet 21, and the air inlet 21 is used for introducing an oxidant; a plurality of gas nozzles 23 are arranged on one side surface of the gas distribution seat 2, the plurality of gas nozzles 23 are communicated with the pressure stabilizing cavity 22, and the plurality of gas nozzles 23 are communicated with the first inlets 111 of the plurality of premixing cyclone micro-mixing nozzles 1 in a one-to-one correspondence manner.
It can be understood that after the oxidant with the preset pressure enters the pressure stabilizing cavity 22 through the air inlet 21, the pressure stabilizing cavity 22 can uniformly distribute the oxidant to each gas nozzle 23, and then each gas nozzle 23 distributes the oxidant to the first inlet 111 of the corresponding premixed cyclone micro-mixing nozzle 1.
Meanwhile, a plurality of premixing swirling micro-mixing nozzles may be disposed in the fuel supply environment to uniformly supply fuel to the second inlet 112 of each premixing swirling micro-mixing nozzle, and then mixing and high-speed transportation of fuel and oxidant are achieved based on each premixing swirling micro-mixing nozzle.
The plurality of premixed swirling micro-mixing nozzles shown in the embodiment may be arranged in an array manner or may be arranged in a concentric circle manner, which is not particularly limited.
As can be seen from the above, the present embodiment is based on the arrangement of the premixing swirl micro-mixing nozzle, and can fully mix the fuel and the oxidant in the flowing process, so as to improve the combustion effect and reduce the emission of nitrogen oxides in the combustion process; meanwhile, the embodiment is based on the structural design of the premixing swirl micro-mixing nozzle, so that the jet flow speed and jet flow length of an outlet end can be increased, the residence time of a high-temperature area is shortened, the flame structure is effectively changed, tempering is prevented, and the combustion characteristic and emission are further improved.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; while the invention has been described in detail with reference to the foregoing embodiments, it will be appreciated by those skilled in the art that variations may be made in the techniques described in the foregoing embodiments, or equivalents may be substituted for elements thereof; 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 premix swirl micro-mixing nozzle, comprising: a premixing tube and a swirl flow guide member;
the premixing tube is provided with a first end and a second end, the first end of the premixing tube is provided with a first inlet for introducing an oxidant, the side wall of the premixing tube is provided with a plurality of second inlets for introducing fuel, and the second end of the premixing tube is provided with a mixed gas outlet;
the second inlets are arranged along the circumferential direction of the premix tube, and each second inlet extends to the central axis of the premix tube;
the swirl flow guide piece is arranged in the premixing tube, and a swirl channel is defined between the swirl flow guide piece and the inner wall of the premixing tube;
wherein, along the extending direction from the first end to the second end, the plurality of second inlets are located between the first inlet and the swirl flow guide.
2. The premix swirl micro-mixing nozzle of claim 1, wherein the second inlet is configured with an extension conduit;
one end of the extension pipeline is communicated with the air outlet end of the second inlet, and the other end of the extension pipeline extends into the premixing tube along the axial direction of the second inlet.
3. The premix swirl micro-mixing nozzle of claim 1, wherein the plurality of second inlets are circumferentially and uniformly distributed relative to a central axis of the premix tube.
4. The premix swirl micro-mixing nozzle of claim 1, wherein at least one of the plurality of second inlets extends obliquely toward a side of the swirl inducer toward a central axis of the premix tube.
5. The premix swirl micro-mixing nozzle of claim 1, wherein the first end of the premix tube is further provided with a third inlet for introducing fuel;
the first inlets are arranged in a plurality, the first inlets are arranged around the third inlets, or the third inlets are arranged in a plurality, and the third inlets are arranged around the first inlets.
6. The premix swirl micro-mixing nozzle of claim 1, wherein the swirl inducer comprises swirl vanes; the swirl blades are arranged in a spiral line track extending mode relative to the central axis of the premixing tube, so that a swirl channel is formed between the swirl blades and the inner wall of the premixing tube.
7. The premix swirl micro-mixing nozzle according to any one of claims 1 to 6, further comprising: a direct current guide member;
the direct current guide piece is arranged in the premixing tube, and a direct current channel is defined between the direct current guide piece and the inner wall of the premixing tube;
and the direct current guide piece is arranged between the rotational flow guide piece and the mixed gas outlet along the extending direction from the first end to the second end.
8. The premix swirl micro-mixing nozzle of claim 7, wherein the dc guide comprises a plurality of guide vanes;
the guide plates are connected with each other, and each guide plate is parallel to or coplanar with the central axis of the premixing tube; the flow guide sheets and/or at least two of the flow guide sheets and the inner wall of the premixing tube define the direct current channel.
9. The premix swirl micro-mixing nozzle according to claim 7, wherein a center distance between the first inlet and the second inlet is 1 to 2 times a diameter of the second inlet along an axial direction of the premix tube, a distance between a center of the second inlet and an inlet end of the swirl flow guide is 1 to 3 times a diameter of the second inlet, a distance between an outlet end of the swirl flow guide and the direct flow guide is 3 to 10 times a diameter of the second inlet, and a diameter of the mixed gas outlet is 0.6 to 1 times a diameter of the second inlet.
10. A combustion chamber, comprising: a valve seat and a plurality of premixing swirl micro-mixing nozzles as claimed in any one of claims 1 to 9;
the air distribution seat is provided with an air inlet and a pressure stabilizing cavity communicated with the air inlet, and the air inlet is used for introducing an oxidant; a plurality of gas nozzles are arranged on one side surface of the gas distribution seat, the gas nozzles are communicated with the pressure stabilizing cavity, and the gas nozzles are communicated with the first inlets of the premixing cyclone micro-mixing nozzles in a one-to-one correspondence mode.
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| CN202310634678.4A CN116697405B (en) | 2023-05-31 | 2023-05-31 | Premixing rotational flow micro-mixing nozzle and combustion chamber |
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| CN202310634678.4A CN116697405B (en) | 2023-05-31 | 2023-05-31 | Premixing rotational flow micro-mixing nozzle and combustion chamber |
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| CN116697405B CN116697405B (en) | 2024-01-19 |
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