CN116293816B - Dual fuel lean premixed multi-stage swirl nozzle - Google Patents
Dual fuel lean premixed multi-stage swirl nozzle Download PDFInfo
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- CN116293816B CN116293816B CN202310416219.9A CN202310416219A CN116293816B CN 116293816 B CN116293816 B CN 116293816B CN 202310416219 A CN202310416219 A CN 202310416219A CN 116293816 B CN116293816 B CN 116293816B
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- 239000000446 fuel Substances 0.000 title claims abstract description 142
- 230000009977 dual effect Effects 0.000 title claims description 18
- 238000002485 combustion reaction Methods 0.000 claims abstract description 249
- 239000007788 liquid Substances 0.000 claims abstract description 129
- 230000000149 penetrating effect Effects 0.000 claims abstract description 5
- 238000004891 communication Methods 0.000 claims description 61
- 238000001816 cooling Methods 0.000 claims description 31
- 238000007664 blowing Methods 0.000 claims description 19
- 238000007599 discharging Methods 0.000 claims description 10
- 230000007423 decrease Effects 0.000 claims description 5
- 239000007789 gas Substances 0.000 description 109
- 238000013461 design Methods 0.000 description 6
- 238000002156 mixing Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 3
- 230000000670 limiting effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000008520 organization Effects 0.000 description 2
- 230000002829 reductive effect Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000002269 spontaneous effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000000034 method Methods 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
- 239000003921 oil Substances 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
本发明涉及燃气轮机技术领域并公开一种双燃料贫预混的多级旋流喷嘴，所述双燃料贫预混的多级旋流喷嘴包括预燃级环形壁、中心杆和主燃级环形壁，所述预燃级环形壁具有在其长度方向上贯穿的预燃级通道和在其长度方向上相对设置的进料端和出料端；所述中心杆设在所述预燃级通道内且从所述进料端朝向所述出料端延伸，所述中心杆与所述预燃级环形壁间隔布置以形成环形腔；所述主燃级环形壁围绕所述预燃级环形壁设置，所述主燃级环形壁与所述预燃级环形壁间隔布置以形成主燃级环形通道。所述双燃料贫预混的多级旋流喷嘴能够可以实现气体燃料和液体燃料的实时切换，还可以根据工况的需求控制气体燃料和液体燃料的需求量，从而满足燃烧室的不同需求。
The present invention relates to the technical field of gas turbines and discloses a dual-fuel lean premixed multi-stage swirl nozzle, the dual-fuel lean premixed multi-stage swirl nozzle comprising a precombustion stage annular wall, a center rod and a main combustion stage annular wall, the precombustion stage annular wall having a precombustion stage channel penetrating in its length direction and a feed end and a discharge end arranged oppositely in its length direction; the center rod is arranged in the precombustion stage channel and extends from the feed end toward the discharge end, the center rod and the precombustion stage annular wall are spaced apart to form an annular cavity; the main combustion stage annular wall is arranged around the precombustion stage annular wall, the main combustion stage annular wall and the precombustion stage annular wall are spaced apart to form a main combustion stage annular channel. The dual-fuel lean premixed multi-stage swirl nozzle can realize real-time switching between gas fuel and liquid fuel, and can also control the required amount of gas fuel and liquid fuel according to the requirements of working conditions, thereby meeting different requirements of the combustion chamber.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a dual-fuel lean premixed multi-stage swirl nozzle.
Background
The dual-fuel gas turbine has good fuel adaptability, so that the dual-fuel gas turbine has wide application in the fields of petroleum, chemical industry, electric power, military and the like. The important precondition of the gas-liquid dual-fuel combustion technology is that the switching between oil and gas is realized under the condition that the combustion engine is not stopped, and the performances of ignition/flameout, combustion stability, combustion efficiency, pollution emission, outlet temperature distribution and the like can all meet the design requirements.
Compared with a single-fuel combustion chamber, the design and research and development of the dual-fuel combustion chamber have the following design difficulties that ① is required to realize injection and fuel-air mixing of two fuels, so that the structure is required to be more compact, gas-liquid fuel supply channels are not influenced mutually, the ② gas-liquid dual-fuel combustion chamber simultaneously meets the performance index requirements, so that the design boundary of the combustion chamber is very narrow, the debugging difficulty is increased, the ③ gas-liquid dual-fuel combustion chamber is required to be consistent in the combustion organization mode, the liquid fuel nozzle and the gaseous fuel nozzle are required to ensure that the fuel and the air have good blending effect, the distribution of the mixed gas is basically consistent, the combustion state of the ④ dual-fuel combustion chamber is not well controlled in the gas-liquid fuel switching process, and a wider stable working boundary is required to be ensured. Thus, a related technology for dual fuel gas turbine combustors is the design of the head scheme.
In the related art, a problem of how to improve the combustion efficiency of the gas fuel and the liquid fuel with the increase of the working conditions is to be solved.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems in the related art to some extent. Therefore, the embodiment of the invention provides a dual-fuel lean premixed multi-stage swirl nozzle, which can realize the real-time switching of gas fuel and liquid fuel, and can control the injection quantity of the gas fuel and the liquid fuel according to the requirements of working conditions so as to meet different requirements of a combustion chamber.
The dual fuel lean premixed multi-stage swozzle of the present invention includes:
the precombustion stage annular wall is provided with a precombustion stage channel penetrating in the length direction of the precombustion stage annular wall, and a feeding end and a discharging end which are oppositely arranged in the length direction of the precombustion stage annular wall;
the central rod is arranged in the precombustion stage channel and extends from the feeding end towards the discharging end, and the central rod and the precombustion stage annular wall are arranged at intervals to form an annular cavity;
A main combustion stage annular wall disposed about the pre-combustion stage annular wall, the main combustion stage annular wall being spaced apart from the pre-combustion stage annular wall to form a main combustion stage annular passage;
Wherein the central rod and/or the pre-stage annular wall has a pre-liquid passage communicating with the pre-stage passage and injecting liquid fuel into the pre-stage passage;
The center rod and/or the pre-stage annular wall has a pre-gas passage in communication with the pre-stage passage and injecting a gaseous fuel into the pre-stage passage;
the pre-combustion stage annular wall and/or the main combustion stage annular wall has a main liquid passage communicating with the main combustion stage annular passage and injecting the liquid fuel into the main combustion stage annular passage;
The pre-combustion stage annular wall and/or the main combustion stage annular wall has a main gas passage communicating with the main combustion stage annular passage and injecting the gaseous fuel into the main combustion stage annular passage.
According to the multi-stage swirl nozzle, the multi-stage swirl nozzle can realize the real-time switching of the gas fuel and the liquid fuel, the independent work of the gas fuel and the liquid fuel and the mixed work of the gas fuel and the liquid fuel by controlling the work of the pre-liquid channel, the pre-gas channel, the main liquid channel and the main gas channel. Meanwhile, the demand of the gas fuel and the liquid fuel can be controlled according to the demands of working conditions, so that different demands of the combustion chamber are met. That is, when the working condition is low, only the pre-liquid passage and the pre-gas passage can be operated, so that the combustion chamber can be ensured to have a stable combustion state. Along with the improvement of working conditions, the pre-liquid channel, the pre-gas channel, the main liquid channel and the main gas channel can work simultaneously, and the requirements of higher working conditions can be met.
Optionally, the pre-combustion stage channel and the pre-liquid channel are provided with a plurality of pre-liquid communication ports which are arranged at intervals along the circumferential direction of the pre-combustion stage annular wall, and/or
The precombustion stage channel and the precombustion liquid channel are provided with a plurality of precombustion communication ports which are arranged at intervals along the circumferential direction of the precombustion stage annular wall, and/or
The main liquid communication ports of the main combustion stage annular channel and the main liquid channel are provided with a plurality of main liquid communication ports which are arranged at intervals along the circumferential direction of the precombustion stage annular wall, and/or
The main gas communication ports of the main combustion stage annular channel and the main gas channel are provided with a plurality of main gas communication ports, and the main gas communication ports are arranged at intervals along the circumferential direction of the precombustion stage annular wall.
Optionally, the multi-stage swirl nozzle further comprises swirl vanes, wherein the swirl vanes comprise precombustion stage vanes arranged in the annular cavity and main combustion stage vanes arranged in the main combustion stage annular channel, a precombustion stage flow channel is formed among the precombustion stage vanes, the precombustion stage annular wall and the central rod, and a main swirl flow channel is formed among the main combustion stage vanes, the precombustion stage annular wall and the main combustion stage annular wall.
Optionally, the pre-stage blades are located between the feed end and the free end of the central rod in the length direction of the pre-stage annular wall, and/or
The main combustion stage blades being located between the feed end and the free end of the central rod in the length direction of the pre-combustion stage annular wall, and/or
The precombustion stage blades and/or the main combustion stage blades are arranged in a plurality of mode, the precombustion stage blades and/or the main combustion stage blades are arranged at intervals along the circumferential direction of the precombustion stage annular wall, and/or
The pre-liquid channel and/or the pre-gas channel is/are in communication with the pre-swirl flow channel, and/or
The primary liquid channel and/or the primary gas channel is in communication with the primary swirl flow channel.
Optionally, a first annular convergence protrusion is arranged on the inner wall surface of the precombustion stage annular wall and is positioned between the precombustion stage blades and the free end of the center rod in the length direction of the precombustion stage annular wall, the protrusion distance of the first annular convergence protrusion gradually increases in the direction from the feeding end to the discharging end, and/or
The inner wall surface of the main combustion stage annular wall and/or the outer wall surface of the precombustion stage annular wall are/is provided with second annular convergence protrusions which are positioned between the main combustion stage blades and the end face of the discharge end in the length direction of the precombustion stage annular wall, and the protrusion distance of the second annular convergence protrusions is gradually increased in the direction from the feed end to the discharge end.
Optionally, the position of the first annular convergence protrusion with the maximum protrusion distance is set to be the smallest pre-combustion stage channel section, and the end face of the free end of the center rod is flush with the smallest pre-combustion stage channel section in the length direction of the pre-combustion stage annular wall.
Optionally, an annular expansion protrusion is arranged on the inner wall surface of the precombustion stage annular wall and is positioned between the free end of the central rod and the end surface of the discharge end in the length direction of the precombustion stage annular wall, the protrusion distance of the annular expansion protrusion is gradually reduced in the direction from the feed end to the discharge end, and the annular expansion protrusion is connected with the first annular convergence protrusion.
Optionally, the first annular convergence protrusion is provided with a first through hole extending in the length direction of the pre-combustion stage annular wall;
The annular expansion protrusion is provided with a cooling hole communicated with the first through hole and/or
The pre-combustion stage annular wall is provided with a cooling channel for introducing air, and the annular expansion bulge is provided with a cooling hole communicated with the cooling channel.
Optionally, a plurality of first through holes are arranged, a plurality of cooling holes are arranged, the first through holes are in one-to-one correspondence with the cooling holes, and/or
The cooling holes are arranged in a plurality, and the cooling holes are arranged at intervals along the circumference of the precombustion stage annular wall.
Optionally, a plurality of air holes are formed in the main combustion stage annular wall, the air holes are located between the main combustion stage blades and the end face of the discharge end in the length direction of the pre-combustion stage annular wall, and the air holes are used for introducing air into the main combustion stage annular channel.
Optionally, the free end of the center rod is arranged at intervals with the end face of the discharge end in the length direction of the precombustion stage annular wall, the center rod is provided with a blowing-off channel for introducing air, the free end of the center rod is provided with a blowing-off hole communicated with the blowing-off channel, an included angle is formed between the blowing-off direction of the blowing-off hole and the length direction of the precombustion stage annular wall, and the included angle is more than or equal to 0 degree and less than 90 degrees.
Optionally, the included angle between the blowing direction of the blowing hole and the length direction of the precombustion stage annular wall is more than or equal to 15 degrees and less than 45 degrees, and/or
The blowing holes are arranged in a plurality of the blowing holes at intervals along the circumference of the precombustion stage annular wall, and/or
The center rod is located substantially at the center of the prechamber passage in a projection plane orthogonal to the length direction of the prechamber annular wall.
Optionally, at least two main combustion stage annular walls are arranged, and two adjacent main combustion stage annular walls are arranged at intervals to form the main combustion stage sub-annular channel;
the swirl vanes comprise main combustion stage sub-vanes arranged in the main combustion stage sub-annular channels, and main swirl sub-flow passages are formed between the main combustion stage sub-vanes and two adjacent main combustion stage annular walls.
Drawings
FIG. 1 is a schematic illustration of a multi-stage swirl nozzle according to an embodiment of the present invention.
Fig. 2 is a cross-sectional view of a multi-stage swirl nozzle according to an embodiment of the present invention.
Fig. 3 is A-A view of fig. 2.
Fig. 4 is a B-B view in fig. 2.
Reference numerals:
1000-multistage swirl nozzle, 100-prechilled annular wall, 110-prechilled channel, 111-minimum prechilled channel section, 112-straight section, 120-feed end, 130-discharge end, 140-first annular converging projection, 150-annular diverging projection, 151-cooling hole, 200-center rod, 210-annular cavity, 220-free end, 230-blow-off channel, 240-blow-off hole, 300-main combustion stage annular wall, 310-main combustion stage annular channel, 320-second annular converging projection, 330-air hole, 400-swirl vane, 410-prechilled vane, 411-prechilled flow channel, 420-main combustion stage vane, 421-main swirl flow channel, a-prefluid channel, a 1-prefluid communication port, b-prefluid channel, b 1-prefluid communication port, c-main liquid channel, c 1-main liquid communication port, d-main gas channel, d 1-main gas communication port, e-cooling channel.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
The dual fuel lean premixed multi-stage swozzle 1000 of the embodiments of the present invention is described below with reference to the drawings, and as shown in fig. 1 to 4, the dual fuel lean premixed multi-stage swozzle 1000 of the present invention includes a pre-combustion stage annular wall 100, a center rod 200 and a main combustion stage annular wall 300, the pre-combustion stage annular wall 100 having a pre-combustion stage passage 110 penetrating in a length direction thereof and a feeding end 120 and a discharging end 130 oppositely disposed in the length direction thereof. A center rod 200 is disposed within the prechamber passage 110 and extends from the feed end 120 toward the discharge end 130, the center rod 200 being spaced apart from the prechamber annular wall 100 to form an annular cavity 210. A main combustion stage annular wall 300 is disposed around the pre-combustion stage annular wall 100, the main combustion stage annular wall 300 being spaced from the pre-combustion stage annular wall 100 to form a main combustion stage annular passage 310. Wherein the center rod 200 and/or the pre-stage annular wall 100 has a pre-liquid passage a communicating with the pre-stage passage 110 and injecting liquid fuel into the pre-stage passage 110, the center rod 200 and/or the pre-stage annular wall 100 has a pre-gas passage b communicating with the pre-stage passage 110 and injecting gas fuel into the pre-stage passage 110, the pre-stage annular wall 100 and/or the main-stage annular wall 300 has a main liquid passage c communicating with the main-stage annular passage 310 and injecting liquid fuel into the main-stage annular passage 310, and the pre-stage annular wall 100 and/or the main-stage annular wall 200 has a main gas passage d communicating with the main-stage annular passage 310 and injecting gas fuel into the main-stage annular passage 310.
According to the multi-stage swirl nozzle 1000 of the present invention, the multi-stage swirl nozzle 1000 can realize real-time switching of the gas fuel and the liquid fuel, separate operation of the gas fuel and the liquid fuel, and mixing operation of the gas fuel and the liquid fuel by controlling the operation of the pre-liquid channel a, the pre-gas channel b, the main liquid channel c, and the main gas channel d. Meanwhile, the demand of the gas fuel and the liquid fuel can be controlled according to the demands of working conditions, so that different demands of the combustion chamber are met. That is, when the working condition is low, only the pre-liquid passage a and the pre-gas passage b can be operated, so that the combustion chamber can be ensured to have a stable combustion state. Along with the improvement of working conditions, the pre-liquid channel a, the pre-gas channel b, the main liquid channel c and the main gas channel d can work simultaneously, and the requirements of higher working conditions can be met.
As shown in fig. 1 to 4, in order to make the technical solution of the present application more easily understood, the technical solution of the present application will be described in more detail with a specific embodiment of a multi-stage swirl nozzle 1000. The longitudinal direction of the pre-combustion stage annular wall 100 corresponds to the left-right direction as shown in fig. 2.
In some embodiments, the liquid fuel of the present invention is fuel oil and the gaseous fuel of the present invention is natural gas. The swirl nozzle 1000 is one of the main parts of the combustion chamber of the turbine, and the swirl nozzle 1000 has a main function of mixing the gas fuel, the liquid fuel and the air and then spraying the mixed gas into the combustion chamber so as to improve the combustion efficiency of the gas fuel and the liquid fuel.
In some embodiments, as shown in fig. 1-4, the pre-combustion stage annular wall 100 is generally cylindrical in shape. Preferably, the pre-combustion stage annular wall 100 in the present invention is cylindrical. The pre-stage annular wall 100 has a pre-stage passage 110 penetrating in a length direction thereof, and the pre-stage passage 110 can mix the gaseous fuel, the liquid fuel and the air, thereby improving a combustion rate of the gaseous fuel and the liquid fuel. The prechamber passage 110 has a feed end 120 and a discharge end 130 disposed opposite each other along its length.
In some embodiments, as shown in fig. 1-4, a center rod 200 is disposed within the prechamber passage 110 and extends from the feed end 120 toward the discharge end 130, the center rod 200 being spaced apart from the prechamber annular wall 100 to form an annular cavity 210. That is, the center rod 200 is located within the prechamber passage 110, and the center rod 200 extends from the feed end 120 toward the discharge end 130 to the middle of the prechamber passage 110. Wherein the center rod 200 is spaced apart from the inner wall surface of the pre-combustion stage annular wall 100 to form an annular cavity 210.
In some embodiments, as shown in fig. 1-4, the center rod 200 and/or the pre-stage annular wall 100 has a pre-liquid passage a in communication with the pre-stage passage 110 and injecting liquid fuel into the pre-stage passage 110, and the center rod 200 and/or the pre-stage annular wall 100 has a pre-gas passage b in communication with the pre-stage passage 110 and injecting gaseous fuel into the pre-stage passage 110. Specifically, the pre-liquid passage a and the pre-gas passage b may inject the liquid fuel and the gas fuel into the pre-combustion passage 110, and the liquid fuel, the gas fuel and the air are sufficiently mixed in the pre-combustion passage 110 and then enter the combustion chamber, so that the combustion efficiency of the liquid fuel and the gas fuel may be improved. The pre-liquid channel a may be located on the central rod 200 or on the pre-combustion stage annular wall 100. Further, both the center rod 200 and the pre-combustion stage annular wall 100 have pre-liquid passages a. Similarly, the pre-gas channel b is arranged in a similar manner to the pre-liquid channel a, and will not be described again here.
Preferably, both the pre-liquid channel a and the pre-gas channel b of the present invention are located in the central rod 200.
In some specific embodiments, as shown in fig. 1-4, a main combustion stage annular wall 300 is disposed around the pre-combustion stage annular wall 100, i.e., the main combustion stage annular wall 300 is mounted at the periphery of the pre-combustion stage annular wall 100. The main combustion stage annular wall 300 is spaced from the pre-combustion stage annular wall 100 to form a main combustion stage annular passage 310. The shape of the main combustion stage annular wall 300 is similar to the shape of the pre-combustion stage annular wall 100. It should be noted that, when the working conditions are low, the combustion requirements of the combustion chamber can be satisfied by injecting the liquid fuel and the gas fuel into the pre-combustion stage passage 110 through the pre-liquid passage a and the pre-gas passage b, and at this time, the main combustion stage annular passage 310 is mainly used for circulating air, that is, continuously introducing air into the combustion chamber. As the operating conditions continue to increase, the liquid and gaseous fuels required by the combustion chamber continue to increase, and when the required amounts of the liquid and gaseous fuels exceed a certain value, a large amount of the liquid fuel, a large amount of the gaseous fuel, and air may be insufficiently mixed in the pre-combustion stage passage 110, thereby resulting in insufficient combustion of the liquid fuel and the gaseous fuel in the combustion chamber and low combustion efficiency, i.e., not only wasting a large amount of the liquid fuel and the gaseous fuel, but also reducing the combustion efficiency of the liquid fuel and the gaseous fuel in the combustion chamber. In order to avoid the above situation, a part of the liquid fuel and the gas fuel are preferably introduced into the pre-combustion stage channel 110, and the rest of the liquid fuel and the gas fuel are introduced into the main-combustion stage annular channel 310, so that the working efficiency of the pre-combustion stage channel 110 can be ensured, and the combustion efficiency of the liquid fuel and the gas fuel can be improved through the main-combustion stage annular channel 310. Therefore, the pre-combustion stage passage 110 and the main combustion stage annular passage 310 can adapt to the requirements of different working conditions, and can ensure the combustion efficiency of liquid fuel and gas fuel.
In some embodiments, as shown in fig. 1-4, the pre-stage annular wall 100 and/or the main stage annular wall 300 has a main liquid passage c in communication with the main stage annular passage 310 and injecting liquid fuel into the main stage annular passage 310, and the pre-stage annular wall 100 and/or the main stage annular wall 200 has a main gas passage d in communication with the main stage annular passage 310 and injecting gaseous fuel into the main stage annular passage 310. Specifically, the main liquid channel c and the main gas channel d may inject the liquid fuel and the gas fuel into the main combustion stage annular channel 310, and the liquid fuel, the gas fuel and the air are fully mixed in the main combustion stage annular channel 310 and then enter the combustion chamber, so that the combustion efficiency of the liquid fuel and the gas fuel may be improved. Wherein the primary liquid channel c may be located on the pre-combustion stage annular wall 100 or on the primary combustion stage annular wall 300. Further, the main combustion stage annular wall 300 and the pre-combustion stage annular wall 100 each have a main liquid passage c. Similarly, the main gas channel d is arranged in a similar manner to the main liquid channel c, and will not be described here again.
Preferably, the primary gas channel d and the primary liquid channel c of the present invention are both located in the primary combustion stage annular wall 300.
In some embodiments, as shown in fig. 1 to 4, the pre-liquid communication ports a1 of the pre-combustion stage channel 110 and the pre-liquid channel a are provided in plurality, and the plurality of pre-liquid communication ports a1 are arranged at intervals along the circumference of the pre-combustion stage annular wall 100, so that the liquid fuel injected into the pre-combustion stage channel 110 can be more uniform, and meanwhile, the liquid fuel can be more fully and uniformly mixed with air in the pre-combustion stage channel 110.
In some embodiments, as shown in fig. 1 to 4, the pre-gas communication ports b1 of the pre-combustion stage channel 110 and the pre-liquid channel a are provided in plurality, and the plurality of pre-gas communication ports b1 are arranged at intervals along the circumferential direction of the pre-combustion stage annular wall 100. The technical effect of the pre-gas communication port b1 is similar to that of the pre-liquid communication port a1, and will not be described again here.
Optionally, the number of the pre-liquid communication ports a1 or the pre-gas communication ports b1 is 6-18.
Alternatively, the pore diameter of the pre-liquid communication port a1 or the pre-gas communication port b1 is 1-5mm.
Alternatively, the central axis of the pre-liquid communication port a1 or the central axis of the pre-gas communication port b1 is orthogonal to the central axis of the pre-combustion stage passage 110.
In some embodiments, as shown in fig. 1 to 4, the main liquid communication ports c1 of the main liquid passage c and the main combustion stage annular passage 310 are provided in plural, and the plural main liquid communication ports c1 are arranged at intervals along the circumferential direction of the pre-combustion stage annular wall 100. The technical effect of the main liquid communication port c1 is similar to that of the pre-liquid communication port a1, and will not be described again here.
In some embodiments, as shown in fig. 1 to 4, the main gas communication ports d1 of the main gas passage d and the main gas annular passage 310 are provided in plurality, and the plurality of main gas communication ports d1 are arranged at intervals along the circumferential direction of the pre-combustion stage annular wall 100. The technical effect of the main air communication port d1 is similar to that of the pre-liquid communication port a1, and will not be described again here.
Alternatively, the number of the main liquid communication ports c1 or the main gas communication ports d1 is 20 to 40.
Alternatively, the aperture of the main liquid communication port c1 or the main gas communication port d1 is 1 to 5mm.
Alternatively, the central axis of the main liquid communication port c1 or the central axis of the main gas communication port d1 is orthogonal to the central axis of the pre-combustion stage passage 110.
In some embodiments, as shown in fig. 1-4, the multi-stage swozzle 1000 further includes swirl vanes 400, the swirl vanes 400 including pre-stage vanes 410 disposed within the annular chamber 210 and main stage vanes 420 disposed within the main stage annular passage 310, pre-swirl flow passages 411 being formed between the pre-stage vanes 410, the pre-stage annular wall 100 and the central rod 200, and main swirl flow passages 421 being formed between the main stage vanes 420, the pre-stage annular wall 100 and the main stage annular wall 300. Specifically, air having a certain air pressure is guided by the pre-combustion stage blades 410 and the main combustion stage blades 420, so that the air forms swirling air in the pre-swirling flow channel 411 and the main swirling flow channel 421, and the swirling air can form a backflow region in the combustion chamber, thereby improving the stability of flame in the combustion chamber.
In some embodiments, as shown in fig. 1-4, the pre-stage blades 410 are located between the feed end 120 and the free end 220 of the center rod 200 along the length of the pre-stage annular wall 100.
In some embodiments, as shown in fig. 1-4, pre-liquid channel a and/or pre-gas channel b are in communication with pre-swirl flow channel 411. Specifically, when the liquid fuel and the gas fuel are introduced into the pre-swirl flow passage 411, the liquid fuel and the gas fuel may be swirled along with the swirled air, so that the mixing between the liquid fuel, the gas fuel and the air may be made more sufficient and uniform, and thus the combustion efficiency of the liquid fuel and the gas fuel may be improved.
In some embodiments, as shown in fig. 1-4, the prechamber vane 410 is provided in a plurality of prechamber vanes 410 spaced apart along the circumference of the prechamber annular wall 100.
Alternatively, the pre-stage blades 410 are straight blades.
Alternatively, the blade angle of the pre-stage blade 410 is 30 ° -50 °.
Alternatively, the number of precombustion stage blades 410 is 6-18.
Alternatively, the number of pre-stage blades 410 is the same as the number of pre-liquid communication ports a1 and pre-gas communication ports b 1.
In some embodiments, as shown in fig. 1-4, the main combustion stage blades 420 are located between the feed end 120 and the free end 220 of the center rod 200 along the length of the pre-combustion stage annular wall 100.
In some embodiments, as shown in fig. 1-4, the primary liquid channel c and/or the primary gas channel d are in communication with the primary swirl flow channel 421. Specifically, when the liquid fuel and the gas fuel are introduced into the main swirl flow channel 421, the liquid fuel and the gas fuel may be swirled along with the swirled air, so that the liquid fuel, the gas fuel and the air may be mixed more sufficiently and more uniformly, and thus the combustion efficiency of the liquid fuel and the gas fuel may be improved.
In some embodiments, as shown in fig. 1-4, the main combustion stage blades 420 are provided in a plurality, with the plurality of main combustion stage blades 420 being spaced apart along the circumference of the pre-combustion stage annular wall 100.
Alternatively, the main combustion stage blade 420 is a straight blade.
Alternatively, the main combustion stage blades 420 have a blade angle of 30-40.
Alternatively, the number of primary stage blades 420 is 10-20.
Alternatively, the number of main liquid communication ports c1 and main gas communication ports d1 are each twice the number of main combustion stage blades 420.
In some embodiments, as shown in fig. 1 to 4, a first annular convergence protrusion 140 is provided on an inner wall surface of the pre-stage annular wall 100 between the pre-stage blade 411 and the free end 220 of the center rod 200 in the length direction of the pre-stage annular wall 100, and the protrusion distance of the first annular convergence protrusion 140 gradually increases in the direction of the feed end 120 toward the discharge end 130. It should be noted that, the protrusion distance of the first annular convergence protrusion 140 may be understood as the height of the protrusion. The larger the protrusion distance of the first annular converging protrusion 140, the smaller the radial cross section of the prechilled channel 110, i.e. the radial cross section of the prechilled channel 110 gradually decreases in the direction of the feed end 120 towards the discharge end 130. The first annular convergence protrusion 140 may converge the swirling gas flowing out of the pre-swirling flow passage 411, so that the swirling gas may be accelerated, so that the swirling speed of the swirling gas is faster, and thus the mixing of the mixture gas is more sufficient. Meanwhile, the swirling gas is continuously converged at the central axis of the pre-combustion stage passage 110, thereby increasing the air pressure at the central axis of the pre-combustion stage passage 110 and effectively suppressing flashback in the multi-stage swirling nozzle 1000.
In some embodiments, as shown in fig. 2, the inner surface of the first annular converging protrusion 140 is a conical surface, which is more beneficial for guiding the swirling gas.
Optionally, the inner surface of the first annular converging protrusion 140 is a conical surface, and a generatrix of the conical surface is between 30 degrees and 50 degrees from the central axis of the pre-combustion stage passage 110.
In some embodiments, as shown in fig. 2, the first annular converging protrusion 140 that sets the maximum protrusion distance is located at the minimum pre-stage passage section 111, and the end surface of the free end 220 of the center rod 200 is flush with the minimum pre-stage passage section 111 in the length direction of the pre-stage annular wall 100.
In some embodiments, as shown in FIG. 2, the prechamber passage 110 has a straight section 112, which straight section 112 is located between the prechamber vane 411 and the first annular converging projection 140 along the length of the prechamber annular wall 100. The swirling gas flowing out through the pre-swirling flow passage 411 can be sufficiently mixed in the straight section 112. Specifically, the air enters the pre-combustion stage passage 110 to form a strong swirling motion, fully developing in the flat section 112, and then accelerating the flow via the first annular converging protrusion 140, so that flashback can be suppressed.
In some embodiments, as shown in fig. 1 to 4, the inner wall surface of the main combustion stage annular wall 300 and/or the outer wall surface of the pre-combustion stage annular wall 100 is provided with a second annular convergence protrusion 320 located between the main combustion stage vane 420 and the end surface of the discharge end 130 in the length direction of the pre-combustion stage annular wall 100, and the protrusion distance of the second annular convergence protrusion 320 gradually increases in the direction from the feed end toward the discharge end. The function and principle of the second annular convergence protrusion 320 are the same as those of the first annular convergence protrusion 140, and will not be described again here.
In some embodiments, as shown in fig. 2, the inner surface of the second annular converging protrusion 320 is a conical surface, which is more beneficial for guiding the swirling gas.
Optionally, the inner surface of the second annular converging protrusion 320 is a conical surface, and a generatrix of the conical surface is between 15 degrees and 45 degrees from the central axis of the pre-combustion stage passage 110.
Optionally, a second annular converging protrusion 320 is located on the outer wall surface of the pre-combustion stage annular wall 100.
Specifically, the air enters the main swirl flow channel 421 to form a weak swirling motion, and then flows through the second annular convergence protrusion 320 with acceleration, so that flashback can be suppressed.
In some embodiments, as shown in fig. 2, an annular expansion protrusion 150 is provided on the inner wall surface of the pre-combustion stage annular wall 100 between the free end 220 of the center rod 200 and the end surface of the discharge end 130 in the length direction of the pre-combustion stage annular wall 100, and the protrusion distance of the annular expansion protrusion 150 gradually decreases in the direction from the feed end toward the discharge end, and the annular expansion protrusion 150 is connected to the first annular convergence protrusion 140. Specifically, the smaller the protrusion distance of the annular expansion protrusion 150, the larger the radial cross section of the prechilling channel 110, i.e. the radial cross section of the prechilling channel 110 gradually increases in the direction of the feed end 120 towards the discharge end 130. The annular expansion lobe 150 may reduce the swirl gas passing through the first annular convergence lobe 140, thereby promoting the swirl gas at the annular expansion lobe 150 to form a central recirculation zone, which may facilitate improved flame holding capacity of the combustion chamber.
In some embodiments, as shown in fig. 2, the inner surface of the annular expansion protrusion 150 is tapered, which is more beneficial for guiding the swirling gas.
Optionally, the inner surface of the annular expansion protrusion 150 is tapered, and the generatrix of the tapered surface is between 30 degrees and 50 degrees from the central axis of the pre-combustion stage passage 110.
In the present invention, both the pre-combustion stage passage 110 and the main combustion stage annular passage 310 employ a premixed combustion organization to reduce pollutant emission levels. After the liquid fuel and the gas fuel in the pre-combustion stage passage 110 enter the pre-swirl flow passage 411, they are further sufficiently mixed with air in the flat section 112 and the first annular convergence protrusion 140, and then the uniform mixture is introduced into the combustion chamber through the annular expansion protrusion 150 to be combusted.
The liquid fuel and the gas fuel in the main swirl flow channel 421 enter the mixture which is further fully mixed with air by the straight section and the second annular convergence convex 320 to form uniform premixed gas, the combustion equivalent ratio of the main combustion stage is 0.5-0.7, and meanwhile, the main combustion stage premixed gas is combusted at the periphery of the central backflow area due to the weak swirl of the main combustion stage, and the design target of low emission of the main combustion stage is realized by lean premixing and shortening of the gas residence time.
In summary, the precombustion stage channel 110 adopts a convergent-divergent structure, the first annular convergent protrusion 140 increases the flow velocity of the mixture, which is favorable for suppressing flashback and spontaneous combustion of the precombustion stage channel 110, and the annular divergent protrusion 150 of the precombustion stage channel 110 decreases the flow velocity of the mixture, which promotes the formation of a central recirculation zone, which is favorable for improving flame stabilizing capability. The main swirl flow channel 421 also adopts a convergence structure, and the second annular convergence protrusion 320 increases the flow velocity of the mixed gas, which is beneficial to inhibiting the flashback and spontaneous combustion of the main combustion stage.
In some embodiments, the first annular converging protrusion 140 is provided with a first through hole extending in the length direction of the pre-combustion stage annular wall 100, and the annular diverging protrusion 150 is provided with a cooling hole 151 communicating with the first through hole. Specifically, the mixed gas located in the first annular converging protrusion 140 may enter the position of the annular expanding protrusion 150 through the first through hole and the cooling hole 151, so that the annular expanding protrusion 150 may be cooled, and the excessive temperature of the annular expanding protrusion 150 may be effectively avoided.
In some embodiments, as shown in FIG. 2, the pre-combustion stage annular wall 100 has a cooling channel e for air passage, and the annular expansion flange 150 is provided with cooling holes 151 communicating with the cooling channel e. Specifically, the mixed gas may enter the position of the annular expansion protrusion 150 through the cooling passage e and the cooling hole 151, so that the annular expansion protrusion 150 may be cooled, and the excessive temperature of the annular expansion protrusion 150 may be effectively avoided.
Alternatively, the cooling hole 151 has a hole diameter of 1-3mm.
Optionally, the central axis of the cooling hole 151 is parallel to the central axis of the pre-combustion stage channel 110.
In some embodiments, as shown in fig. 2, a plurality of first through holes are provided, a plurality of cooling holes 151 are provided, and the first through holes are in one-to-one correspondence with the cooling holes 151.
In some embodiments, as shown in FIG. 2, a plurality of cooling holes 151 are provided, the plurality of cooling holes 151 being spaced apart along the circumference of the pre-combustion stage annular wall 100.
In some embodiments, as shown in fig. 1 and 2, the main combustion stage annular wall 300 is provided with a plurality of air holes 330 located between the main combustion stage blades 420 and the end face of the discharge end 130 along the length direction of the pre-combustion stage annular wall 100, and the air holes 330 are used for introducing air into the main combustion stage annular channel 310 to prevent the flashback of the boundary layer on the main combustion stage annular wall 300.
Alternatively, the air holes 330 have a diameter of 1-3mm.
Optionally, the central axis of the air hole 330 is perpendicular to the central axis of the pre-combustion stage passage 110.
Optionally, the air holes 330 are provided in plurality, and the plurality of air holes 330 are arranged at intervals along the circumference of the pre-combustion stage passage 110.
In some embodiments, as shown in fig. 2, the free end 220 of the central rod 200 is spaced apart from the end face of the discharge end 130 in the length direction of the pre-combustion stage annular wall 100, the central rod 200 has a blow-off channel 230 for air to pass through, and the free end 220 of the central rod 200 is provided with a blow-off hole 240 communicating with the blow-off channel 230. Specifically, air having a certain pressure enters the pre-combustion stage passage 110 through the blowing-off passage 230 and the blowing-off hole 240, so that the air pressure at the center of the pre-combustion stage passage 110 can be increased, and flashback in the multi-stage swozzle 1000 can be effectively suppressed. That is, in the pre-stage passage 110, the mixed gas is continuously collected toward the inner wall surface of the pre-stage annular wall 100 under the swirling condition, so that the air pressure at the inner wall surface of the pre-stage annular wall 100 is continuously increased, the air pressure at the central position of the pre-stage passage 110 is continuously decreased, and the axial velocity of the mixed gas at the central position of the pre-stage passage 110 is reduced, thereby causing flashback at the position of the discharge end 130. Meanwhile, when the ignition is unsuccessful or a part of premixed gas exists in the combustion chamber after flameout, the central rod 200 is continuously introduced with air through the blowing-out holes 240, and the air can blow out the unburned mixed gas into the combustion chamber, so that the deflagration phenomenon is avoided when the combustion chamber is ignited next time.
In some embodiments, as shown in fig. 2, the blowing direction of the blowing holes 240 forms an angle with the length direction of the pre-combustion stage annular wall 100, and the angle is greater than or equal to 0 degrees and less than 90 degrees. Specifically, the flow direction of the air passing from the blow-off holes 240 into the pre-stage passage 110 is generally toward the discharge end 130.
Optionally, as shown in fig. 2, an included angle between a blowing direction of the blowing holes 240 and a length direction of the pre-combustion stage annular wall 100 is 15 degrees or more and less than 45 degrees.
In some embodiments, as shown in FIG. 2, the center rod 200 is located generally at the center of the prechamber passage 110 in a plane of projection orthogonal to the length of the prechamber annular wall 100. That is, the center rod 200 is located at the centerline of the prechamber passage 110.
The projection plane perpendicular to the length direction of the annular wall 100 of the pre-stage may be understood as a radial cross section of the annular wall 100 of the pre-stage.
In some embodiments, as shown in FIG. 2, the blow-off holes 240 are provided in a plurality, with the plurality of blow-off holes 240 being spaced apart along the circumference of the pre-combustion stage annular wall 100. Specifically, the blowing holes 240 may uniformly blow air into the pre-stage passage 110, thereby making the air pressure in the pre-stage passage 110 more uniform, i.e., making the air pressure in the pre-stage passage 110 more stable.
Alternatively, the number of blow holes 240 is 4-12.
Alternatively, the blowing holes 240 have a diameter of 2-6mm.
In some embodiments, the primary annular wall 300 is provided with at least two, adjacent two primary annular walls 300 being spaced apart to form a primary sub-annular passage. The swirl vanes 400 comprise main stage sub-vanes disposed within the main stage sub-annular passage, the main stage sub-vanes forming main swirl sub-flow passages with adjacent two main stage annular walls.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed, mechanically connected, electrically connected, or communicable with each other, directly connected, indirectly connected through an intervening medium, or in communication between two elements or in an interactive relationship between two elements, unless otherwise explicitly specified. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While the above embodiments have been shown and described, it should be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations of the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the invention.
Claims (13)
1. A dual fuel lean premixed multi-stage swozzle comprising:
the precombustion stage annular wall is provided with a precombustion stage channel penetrating in the length direction of the precombustion stage annular wall, and a feeding end and a discharging end which are oppositely arranged in the length direction of the precombustion stage annular wall;
the central rod is arranged in the precombustion stage channel and extends from the feeding end towards the discharging end, and the central rod and the precombustion stage annular wall are arranged at intervals to form an annular cavity;
A main combustion stage annular wall disposed about the pre-combustion stage annular wall, the main combustion stage annular wall being spaced apart from the pre-combustion stage annular wall to form a main combustion stage annular passage;
Wherein the central rod and/or the pre-stage annular wall has a pre-liquid passage communicating with the pre-stage passage and injecting liquid fuel into the pre-stage passage;
The center rod and/or the pre-stage annular wall has a pre-gas passage in communication with the pre-stage passage and injecting a gaseous fuel into the pre-stage passage;
the pre-combustion stage annular wall and/or the main combustion stage annular wall has a main liquid passage communicating with the main combustion stage annular passage and injecting the liquid fuel into the main combustion stage annular passage;
The pre-combustion stage annular wall and/or the main combustion stage annular wall has a main gas passage communicating with the main combustion stage annular passage and injecting the gaseous fuel into the main combustion stage annular passage.
2. The dual fuel lean premixed multi-stage swozzle according to claim 1,
The pre-combustion stage channel and the pre-liquid channel are provided with a plurality of pre-liquid communication ports which are arranged at intervals along the circumferential direction of the pre-combustion stage annular wall, and/or
The precombustion stage channel and the precombustion liquid channel are provided with a plurality of precombustion communication ports which are arranged at intervals along the circumferential direction of the precombustion stage annular wall, and/or
The main liquid communication ports of the main combustion stage annular channel and the main liquid channel are provided with a plurality of main liquid communication ports which are arranged at intervals along the circumferential direction of the precombustion stage annular wall, and/or
The main gas communication ports of the main combustion stage annular channel and the main gas channel are provided with a plurality of main gas communication ports, and the main gas communication ports are arranged at intervals along the circumferential direction of the precombustion stage annular wall.
3. The dual fuel lean premixed multi-stage swozzle of claim 1 further including swirl vanes including pre-stage vanes disposed within the annular cavity and main stage vanes disposed within the main stage annular passage, wherein a pre-swirl flow passage is formed between the pre-stage vanes, the pre-stage annular wall and the center rod, and wherein a main swirl flow passage is formed between the main stage vanes, the pre-stage annular wall and the main stage annular wall.
4. A dual fuel lean premixed multi-stage swozzle according to claim 3,
The pre-stage blades being located between the feed end and the free end of the central rod in the length direction of the pre-stage annular wall, and/or
The main combustion stage blades being located between the feed end and the free end of the central rod in the length direction of the pre-combustion stage annular wall, and/or
The precombustion stage blades and/or the main combustion stage blades are arranged in a plurality of mode, the precombustion stage blades and/or the main combustion stage blades are arranged at intervals along the circumferential direction of the precombustion stage annular wall, and/or
The pre-liquid channel and/or the pre-gas channel is/are in communication with the pre-swirl flow channel, and/or
The primary liquid channel and/or the primary gas channel is in communication with the primary swirl flow channel.
5. A dual fuel lean premixed multi-stage swozzle according to claim 3, wherein the inner wall surface of the annular wall of the pre-stage is provided with a first annular convergence protrusion located between the vane of the pre-stage and the free end of the center rod in the length direction of the annular wall of the pre-stage, the protrusion distance of the first annular convergence protrusion gradually increases in the direction from the feeding end toward the discharging end, the protrusion distance of the first annular convergence protrusion increases, the radial cross section of the pre-stage passage is smaller, and/or
The main combustion stage annular wall is characterized in that a second annular convergence protrusion is arranged on the inner wall surface of the main combustion stage annular wall and/or the outer wall surface of the pre-combustion stage annular wall and positioned between the main combustion stage blades and the end surface of the discharge end in the length direction of the pre-combustion stage annular wall, the protrusion distance of the second annular convergence protrusion is gradually increased in the direction from the feed end to the discharge end, and the radial section of the pre-combustion stage channel is larger as the protrusion distance of the second annular convergence protrusion is increased.
6. The dual fuel lean premixed multi-stage swozzle of claim 5 wherein the location of the first annular converging lobe setting the maximum lobe distance is a minimum pre-stage passage cross section with the end face of the free end of the center rod being flush with the minimum pre-stage passage cross section in the length direction of the pre-stage annular wall.
7. The dual fuel lean premixed multi-stage swozzle according to claim 5, wherein the inner wall surface of the pre-combustion stage annular wall is provided with an annular expansion protrusion located between the free end of the center rod and the end surface of the discharging end in the length direction of the pre-combustion stage annular wall, the protrusion distance of the annular expansion protrusion gradually decreases in the direction from the feeding end toward the discharging end, the smaller the protrusion distance of the annular expansion protrusion decreases, the larger the radial section of the pre-combustion stage channel is, and the annular expansion protrusion is connected with the first annular convergence protrusion.
8. The dual fuel lean premixed multi-stage swozzle according to claim 7,
The first annular convergence protrusion is provided with a first through hole extending in the length direction of the precombustion stage annular wall;
the annular expansion protrusion is provided with a cooling hole communicated with the first through hole and/or
The pre-combustion stage annular wall is provided with a cooling channel for introducing air, and the annular expansion bulge is provided with a cooling hole communicated with the cooling channel.
9. The dual fuel lean premixed multi-stage swozzle of claim 8, wherein the first through holes are plural, the cooling holes are plural, the first through holes are in one-to-one correspondence with the cooling holes, and/or
The cooling holes are arranged in a plurality, and the cooling holes are arranged at intervals along the circumference of the precombustion stage annular wall.
10. The dual fuel lean premixed multi-stage swozzle according to any of the claims 1 to 9, wherein the main combustion stage annular wall is provided with several air holes between the main combustion stage vanes and the end face of the discharge end in the length direction of the pre-combustion stage annular wall, which air holes are used for introducing the air into the main combustion stage annular channel.
11. The dual fuel lean premixed multi-stage swozzle according to any one of claims 1 to 9, wherein the free end of the center rod is spaced apart from the end face of the discharging end in the length direction of the pre-combustion stage annular wall, the center rod has a blowing off passage for introducing air, the free end of the center rod is provided with a blowing off hole communicating with the blowing off passage, and an included angle is formed between the blowing off direction of the blowing off hole and the length direction of the pre-combustion stage annular wall, and the included angle is 0 degrees or more and less than 90 degrees.
12. The dual fuel lean premixed multi-stage swozzle of claim 11 wherein the included angle between the blowing direction of the blowing holes and the length direction of the pre-combustion stage annular wall is 15 degrees or more and less than 45 degrees, and/or
The blowing holes are arranged in a plurality of the blowing holes at intervals along the circumference of the precombustion stage annular wall, and/or
The center rod is located substantially at the center of the prechamber passage in a projection plane orthogonal to the length direction of the prechamber annular wall.
13. The dual fuel lean premixed multi-stage swozzle of any one of claims 1 to 9, wherein at least two of the main combustion stage annular walls are provided, adjacent two of the main combustion stage annular walls being spaced apart to form the main combustion stage sub-annular passage;
the swirl vanes comprise main combustion stage sub-vanes arranged in the main combustion stage sub-annular channels, and main swirl sub-flow passages are formed between the main combustion stage sub-vanes and two adjacent main combustion stage annular walls.
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| US20130263605A1 (en) * | 2012-04-04 | 2013-10-10 | General Electric | Diffusion Combustor Fuel Nozzle |
| CN103672969B (en) * | 2013-12-13 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine dual-fuel combustion chamber nozzle of combustion |
| CN203595145U (en) * | 2013-12-13 | 2014-05-14 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Double-fuel combustion chamber nozzle for combustion gas turbine |
| CN107575891B (en) * | 2017-07-25 | 2019-08-09 | 西北工业大学 | A low-pollution combustor head structure for a dual-fuel gas turbine |
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| CN109404967B (en) * | 2018-12-04 | 2024-04-05 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of gas turbine and gas turbine |
| CN114034061B (en) * | 2021-09-03 | 2023-06-23 | 东方电气集团科学技术研究院有限公司 | Liquid fuel nozzle for dual-fuel combustion chamber of dual-radial swirler |
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