CN108443912B - Self-priming air-assisted atomization dual-fuel nozzle - Google Patents
Self-priming air-assisted atomization dual-fuel nozzle Download PDFInfo
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- CN108443912B CN108443912B CN201810471003.1A CN201810471003A CN108443912B CN 108443912 B CN108443912 B CN 108443912B CN 201810471003 A CN201810471003 A CN 201810471003A CN 108443912 B CN108443912 B CN 108443912B
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- cyclone
- atomizing
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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
- F23R3/36—Supply of different fuels
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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
Abstract
The invention belongs to the technical field of gas turbine equipment, and particularly relates to a self-priming air-assisted atomization dual-fuel nozzle which comprises a liquid fuel cyclone atomization assembly, an air-assisted cyclone atomization assembly, a detachable compaction fixing assembly, a carbon deposition prevention air cooling assembly and a nozzle shell; the liquid fuel cyclone atomization assembly comprises a liquid fuel cyclone and a liquid fuel nozzle; the air auxiliary cyclone atomization assembly comprises an atomization air cyclone and an air nozzle; the liquid fuel cyclone is arranged in the atomizing air cyclone; the detachable compaction fixing assembly comprises a sealing cover, a gasket and a screw plug; the carbon deposition prevention air cooling assembly comprises a heat insulation inner cover, fins and fin type flow channels at the front part of the nozzle shell; the liquid fuel inlet of the liquid fuel interface and the atomizing air inlet of the atomizing air interface are respectively provided with a gas-liquid dual-purpose filter element and a detachable stop. Solves the problem of low combustion efficiency caused by poor atomization effect of liquid fuel when a gas turbine is used by a slow driver Kuang Yun.
Description
Technical Field
The invention belongs to the technical field of gas turbine equipment, and particularly relates to a self-priming air-assisted atomization dual-fuel nozzle.
Background
With the continuous promotion of the ocean strategy in China, the exploration and exploitation force of the ocean crude oil is continuously increased, and the yield of the ocean crude oil is rapidly increased. In the process of crude oil exploitation, a large amount of petroleum associated gas is often produced, the associated gas has the characteristics of inflammability, explosiveness and difficult storage and transportation, and the associated gas can be directly burnt for treatment at the beginning of exploitation due to safety, so that serious energy waste is caused, and the national ocean strategy brings urgent demands for solving the problem. The dual-fuel gas turbine is power equipment capable of effectively solving the problem, not only can provide power for crude oil development, but also can work by adopting petroleum associated gas as gaseous fuel, and can realize undisturbed online switching between crude liquid fuel and petroleum associated gas under the condition of no shutdown, so that the adaptability of the gas turbine to fuel is improved, the petroleum associated gas is effectively utilized, and the requirements of various fuels in different states in the crude oil development process are met.
The dual fuel nozzle is the most important core component of the dual fuel gas turbine, and with the continuous increase of the demand of the ocean strategy for the high-power gas turbine, the design of the nozzle also has put higher demands. More liquid fuel is needed to meet high power, so that the design of the aperture of the nozzle spout is larger, the liquid fuel atomization effect is poor, the combustion is uneven and the carbon deposition is serious under the condition of slow vehicle working conditions, the combustion efficiency is further influenced, the phenomena of black smoke emission of exhaust and the like are caused, and the service life of the nozzle is seriously threatened even the normal operation of the whole gas turbine. At present, more solutions are adopted, namely, double liquid fuel paths are adopted and designed into different flow rates so as to meet the liquid fuel quantity requirements of different stages of the gas turbine from slow starting to high working conditions, but the auxiliary equipment is increased, the auxiliary system is complex, the congenital advantages of small volume and light weight of the gas turbine are seriously affected, and the application of the dual-fuel gas turbine is limited.
Disclosure of Invention
The invention aims to provide a self-priming air-assisted atomization dual-fuel nozzle which can enable a gas turbine to efficiently burn liquid fuel in the slow car working condition and the high working condition operation process and can also enable gaseous fuel to be used, so that the problem of low combustion efficiency caused by poor atomization effect of the liquid fuel when a gas turbine slow car worker Kuang Yun is solved, and the application range of the gas turbine is widened in a multi-fuel mode.
The invention adopts the technical scheme that: a self-priming air-assisted atomization dual-fuel nozzle comprises a liquid fuel cyclone atomization assembly, an air-assisted cyclone atomization assembly, a detachable compaction fixing assembly, a carbon deposit prevention air cooling assembly, a middle side cover, an upper side cover, an outer cover, a gaseous fuel interface, a liquid fuel interface, an atomization air interface and a nozzle shell; the liquid fuel cyclone atomization assembly comprises a liquid fuel cyclone and a liquid fuel nozzle; the air auxiliary cyclone atomization assembly comprises an atomization air cyclone and an air nozzle; the liquid fuel cyclone is arranged in the atomizing air cyclone; the detachable compaction fixing assembly comprises a sealing cover, a gasket and a screw plug; the carbon deposition prevention air cooling assembly comprises a heat insulation inner cover, fins and fin type flow channels, wherein the fins and the fin type flow channels are arranged at the front part of the nozzle shell; and a liquid fuel inlet of the liquid fuel interface and an atomizing air inlet of the atomizing air interface are respectively provided with a gas-liquid dual-purpose filter element and a detachable stop ring.
Further, the outer cover is welded with the heat-insulating inner cover, 10 gaseous fuel outlets are arranged on the outer cover, and an included angle between the axis direction of the gaseous fuel outlets and the axis direction of the liquid fuel nozzle is 30 degrees; each 2 of the gaseous fuel outlets are in 1 group, and each group of 2 gaseous fuel outlets are at an angle of 12.5 degrees and are circumferentially distributed about the central axis of the liquid fuel nozzle.
Further, the liquid fuel cyclone is inserted and nested in the inner cavity of the atomizing air cyclone, and the liquid fuel cyclone and the atomizing air cyclone are fixed in the nozzle shell in a rated torque mode through the detachable compression fixing assembly; the screw plug of the detachable compression fixing assembly adopts a double-head straight thread connection mode, one end of the screw plug is fixed with the nozzle shell, the liquid fuel cyclone and the atomizing air cyclone are compressed and fixed in an extrusion mode, the other end of the screw plug is connected with the end face of the nozzle shell with the gasket and the sealing cover in a rated torque mode, and a liquid fuel cyclone channel and an auxiliary cyclone atomizing air channel are formed together; the liquid fuel swirler and the inner wall of the atomizing air swirler form a second liquid fuel passage.
Further, a first liquid fuel channel and a first atomization air channel are arranged on the nozzle shell, and a second atomization air channel is formed by the inner wall surface of the inner cavity of the nozzle shell and the outer wall surface of the atomization air cyclone.
Further, the upper side shroud, the middle side shroud, and the nozzle housing form a first gaseous fuel passage, a second gaseous fuel passage, and a third gaseous fuel passage.
Further, an anti-carbon air inlet and 6 fourth gaseous fuel channels which are vertically and alternately arranged with the anti-carbon air inlet are arranged on the heat insulation inner cover.
Further, the swirling direction of the swirling groove of the liquid fuel swirler is the same as that of the swirling groove of the atomizing air swirler.
Further, the gaseous fuel interface, the liquid fuel interface and the atomizing air interface adopt a sealing connection mode of internal conical surface external threads.
Further, the detachable pressing fixing assembly is connected with the nozzle shell in a double-head straight thread mode through the sealing cover gasket and the screw plug, so that the trimming, cleaning and replacement of core working parts are facilitated, the development period of the nozzle is shortened, and the service life of the nozzle is prolonged. The heat-insulating inner cover with the normal air inlet is fixed at the front part of the nozzle shell in a welding mode to form a fin type air cooling channel, so that the temperature of a core working part is effectively reduced; the gaseous fuel supply channels and the normal inlets of the heat-insulating inner cover are alternately distributed and connected with the outer cover in a welding mode, so that the space occupied by the whole nozzle can be effectively reduced while the requirement of supply quantity is met.
The invention has the beneficial effects that: the air auxiliary swirl atomization design is effectively combined to the liquid fuel path, and is characterized in that auxiliary atomization air is actively supplied through the nozzle air path under the slow vehicle condition, so that the ignition performance and the combustion efficiency are improved; the high working condition forms a negative pressure area through the strong swirl of the liquid fuel, air in the combustion chamber is automatically sucked into the nozzle air channel under the action of pressure difference, atomization of the liquid fuel is enhanced, combustion efficiency is further improved, the problem of poor atomization effect under the conditions of ignition and slow vehicle can be conveniently and effectively solved under the condition of a single liquid fuel channel, and meanwhile, the use requirement of dual fuel is met, and important application value is realized.
The detachable pressing fixing assembly is connected with the nozzle shell by the sealing cover gasket and the screw plug in a double-head straight thread mode, so that the core working parts can be conveniently trimmed, cleaned and replaced, the development period of the nozzle is shortened, and the service life of the nozzle is prolonged. The heat-insulating inner cover with the normal air inlet is fixed at the front part of the nozzle shell in a welding mode to form a fin type air cooling channel, so that the temperature of a core working part is effectively reduced; the gaseous fuel supply channels and the normal inlets of the heat-insulating inner cover are alternately distributed and connected with the outer cover in a welding mode, so that the space occupied by the whole nozzle can be effectively reduced while the requirement of supply quantity is met. The main advantages are as follows:
(1) The liquid fuel interface and the atomizing air interface are arranged in a staggered row-to-row mode, so that the installation space is saved;
(2) The liquid fuel inlet and the atomized air inlet channels are internally provided with the gas-liquid dual-purpose universal filter assembly, so that impurities in an incoming flow medium can be effectively removed, the reliability and the service life of the nozzle are improved, and the nozzle is fixed through the detachable stop ring, so that the nozzle is convenient to replace and clean;
(3) The liquid fuel interface, the atomizing air interface and the gaseous fuel interface are in a sealing connection mode of internal conical surface external threads, so that the device is safe and reliable, and the device is convenient to assemble and disassemble;
(4) The axis direction of the gaseous fuel outlet forms an angle of 30 degrees with the axis direction of the liquid fuel nozzle, the number of the gaseous fuel outlets is 10, every 2 gaseous fuel outlets form an angle of 12.5 degrees, and the gaseous fuel outlets are uniformly distributed around the central axis of the liquid fuel nozzle in the circumferential direction, so that a good combustion effect can be obtained;
(5) The heat-insulating inner cover adopts a design form that the axial passage direction of the gaseous fuel is mutually perpendicular to the direction of the carbon deposit-preventing cooling air inlet and is alternately arranged, so that the space is effectively saved;
(6) The front part of the nozzle shell adopts a fin type flow passage design, so that the structural strength, namely the deformation resistance, of the nozzle can be effectively improved, heat exchange is enhanced, the low temperature in the nozzle is maintained, and the service life is prolonged;
(7) The swirling direction of the swirling groove of the liquid fuel swirler is the same as that of the swirling groove of the atomizing air swirler, so that good airflow shearing effect is ensured, and an auxiliary atomizing effect is achieved.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic perspective view of the present invention;
FIG. 3 is a schematic cross-sectional view of M-M of FIG. 1;
FIG. 4 is an enlarged view of a portion of W in FIG. 1;
fig. 5 is a schematic cross-sectional view of N-N in fig. 1.
Detailed Description
Referring to the figures, the self-priming air-assisted atomization dual-fuel nozzle comprises a liquid fuel cyclone atomization assembly, an air-assisted cyclone atomization assembly, a detachable compaction fixing assembly, a carbon deposit prevention air cooling assembly, a middle side cover 3, an upper side cover 5, an outer cover 14, a gaseous fuel interface 4, a liquid fuel interface 1, an atomization air interface 2 and a nozzle shell 8; the liquid fuel swirl atomizing assembly includes a liquid fuel swirler 12 and a liquid fuel nozzle 17; the air-assisted cyclone atomization assembly comprises an atomization air cyclone 13 and an air nozzle 6; the liquid fuel cyclone 12 is arranged in the atomizing air cyclone 13; the detachable pressing and fixing assembly comprises a sealing cover 10, a gasket 9 and a screw plug 11; the carbon deposition prevention air cooling assembly comprises a heat insulation inner cover 7, fins 32 at the front part of a nozzle shell 8 and a fin type flow channel 31; a gas-liquid dual-purpose filter element 28 and a detachable stop ring 29 are respectively arranged at the liquid fuel inlet 23 of the liquid fuel interface 1 and the atomizing air inlet 24 of the atomizing air interface 2; the outer cover 14 is welded with the heat-insulating inner cover 7, 10 gaseous fuel outlets 15 are arranged on the outer cover 14, and an included angle between the axial direction of the gaseous fuel outlets 15 and the axial direction of the liquid fuel nozzle 17 is 30 degrees; each 2 of the gaseous fuel outlets 15 are 1 group, and each group of 2 gaseous fuel outlets 15 are at an angle of 12.5 ° and are circumferentially distributed around the central axis of the liquid fuel nozzle 17; the liquid fuel cyclone 12 is inserted and nested in the inner cavity of the atomizing air cyclone 13, and the liquid fuel cyclone and the atomizing air cyclone are fixed in the nozzle shell 8 in a rated torque mode through a detachable compression fixing assembly; the screw plug 11 of the detachable compression fixing assembly adopts a double-head straight thread connection mode, one end of the screw plug is fixed with the nozzle shell 8, the liquid fuel cyclone 12 and the atomizing air cyclone 13 are compressed and fixed in an extrusion mode, and the other end of the screw plug, the gasket 9 and the sealing cover 10 are connected to the end face of the nozzle shell 8 in a rated torque mode to jointly form a liquid fuel cyclone channel and an auxiliary cyclone atomizing air channel; the liquid fuel swirler 12 and the inner wall of the atomizing air swirler 13 form a second liquid fuel passage 34; the self priming air assisted atomizing dual fuel nozzle as set forth in claim 1, wherein: the nozzle shell 8 is provided with a first liquid fuel channel 25 and a first atomization air channel 26, and a second atomization air channel 33 is formed by the inner wall surface of the inner cavity of the nozzle shell 8 and the outer wall surface of the atomization air swirler 13; the upper side cap 5, the middle side cap 3 and the nozzle housing 8 form a first gaseous fuel passage 20, a second gaseous fuel passage 21 and a third gaseous fuel passage 22; the heat-insulating inner cover 7 is provided with an anti-carbon air inlet 27 and 6 fourth gaseous fuel passages 30 which are vertically and alternately arranged with the anti-carbon air inlet 27; the rotation direction of the rotation groove of the liquid fuel cyclone 12 is the same as that of the rotation groove of the atomizing air cyclone 13; the gaseous fuel interface 4, the liquid fuel interface 1 and the atomizing air interface 2 adopt a sealing connection mode of internal conical surface external threads.
The specific working mode of the self-priming air-assisted atomization dual-fuel nozzle is described as follows:
as shown in fig. 1, the liquid fuel swirler 12 is mounted in the inner cavity of the atomizing air swirler 13 in a plugging manner, and forms a second liquid fuel channel 34 together with the inner wall surface of the liquid fuel swirler, one end of the screw plug 11 is fixed with the nozzle housing 8 in a double-head straight-thread connection manner, and further the liquid fuel swirler 12 and the atomizing air swirler 13 are pressed and fixed in an extrusion manner so as to ensure good tightness, and the other end of the screw plug is connected with the gasket 9 and the sealing cover 10 to the end surface of the nozzle housing 8 in a rated torque manner, so that the liquid fuel swirl channel and the auxiliary swirl atomizing air channel are formed together.
As shown in fig. 2, when the liquid fuel is adopted for operation, the liquid fuel enters the first liquid fuel flow channel 25 through the liquid fuel inlet 23 and the gas-liquid dual-purpose filter element 28 for filtering and removing impurities, flows through the second liquid fuel channel 34 and the swirl groove to reach a swirl state, and finally is injected from the liquid fuel nozzle 17 to form an atomization cone, and enters the combustion space to be mixed and combusted with the compressed air. During this process, the gaseous fuel inlet 19 supplies compressed air to cool the nozzle body while purging, and the auxiliary atomizing air path has two different operating states:
(1) when the gas turbine is in an ignition working condition and a slow turning worker Kuang Yun, auxiliary atomization air is actively supplied from an atomization air inlet 24, an atomization air interface 2 adopts a sealing connection mode of internal conical surface and external threads, impurities are filtered and removed through a gas-liquid dual-purpose filter element 28, the filtered impurities enter a first atomization air channel 26, a second atomization air channel 33 formed by the inner cavity inner wall surface of a nozzle shell 8 and the outer wall surface of an atomization air cyclone 12 and a cyclone tank are in a cyclone state, finally, the atomized liquid is discharged through rotary jet flow of an atomization air outlet 18 and an atomization air nozzle 6, liquid fuel atomization cone liquid film is subjected to rotary shearing to assist liquid drop breaking, a good atomization effect is achieved, and the problem of poor atomization quality of liquid fuel when the gas turbine is in slow turning working condition and ignition working condition is solved;
(2) when the gas turbine operates under the high working condition, the liquid fuel supply quantity is large, after being sprayed out through the high-speed strong swirl of the liquid fuel nozzle 17, a strong negative pressure area is formed behind the nozzle, and the pressure near the auxiliary atomizing air outlet 18 is lower than the pressure in the combustion chamber shell, at the moment, the compressed air in the combustion chamber shell automatically enters from the atomizing air inlet 2 under the action of pressure difference, and the compressed air is discharged through the rotary jet of the atomizing air outlet 18 and the atomizing air nozzle 6 after being intensified and swirled by the first atomizing air channel 26, the second atomizing air channel 33 and the swirl groove, and the liquid fuel atomizing cone liquid film is subjected to rotary shearing auxiliary liquid drop breaking, so that the atomizing air self-priming auxiliary atomizing process is completed, the fineness of atomized particles is reduced, the combustion is enhanced, and the efficiency is improved.
When the gas fuel is used for working, as shown in fig. 3, the gas fuel enters from the gas fuel inlet 19, passes through the first gas fuel channel 20, the second gas fuel channel 21 and the third gas fuel channel 22 formed by the upper side cover 5, the middle side cover 3 and the nozzle shell 8, enters 6 fourth gas fuel channels 30 which are vertically and alternately arranged with the carbon deposit prevention air inlets 27, effectively reduces the occupied space of the nozzle, then enters the annular space formed by the outer cover 14 and the heat insulation inner cover 7, and finally is sprayed out from 10 gas fuel outlets 15 which are uniformly distributed in groups each 2 in the circumferential direction of the central axis of the liquid fuel nozzle 17 at an angle of 12.5 degrees around the central axis of the liquid fuel nozzle 17 by the axial direction, and enters the combustion space, so that good combustion effect is ensured. At this time, the liquid fuel path supplies compressed air to sweep and cool the nozzle body, so that the service life is prolonged.
As shown in fig. 1, the carbon deposition preventing gas cooling module is composed of the heat insulating inner cover 7, the front fins 32 of the nozzle case 8, and the fin type flow passages 31, which are connected by welding. The fin structure has the advantages of improving the structural strength, namely the deformation resistance, of the nozzle, strengthening heat exchange, keeping the low temperature inside the nozzle and prolonging the service life. Cooling air enters into a circulation space formed by the fin-type flow channels 31 of the nozzle shell 8 and the heat-insulating inner cover 7 through 6 normal carbon deposit prevention air inlets 27, and finally is sprayed from the cooling air outlets 16 to form a heat-insulating protective air mold, so that carbon deposit is prevented from forming.
When the gas turbine using the double-material nozzle is started and a driver Kuang Yun runs, air is actively supplied through the auxiliary atomization air path, so that good atomization of the liquid fuel under the condition of a single liquid fuel path can be realized, the ignition performance and the combustion efficiency are improved, and extra auxiliary systems are avoided; when the high-working-condition operation is performed, through the effective combination design of the liquid fuel cyclone atomization assembly and the air auxiliary cyclone atomization assembly, a negative pressure area can be formed at an outlet after the liquid fuel is strongly cyclone, air in the combustion chamber can automatically enter the air auxiliary cyclone atomization assembly under the action of pressure difference in the combustion chamber shell, the sprayed and atomized liquid fuel is subjected to intensified atomization under the shearing action of airflow, self-priming air auxiliary atomization is realized, and the combustion efficiency is further improved. Through the effective combination of good atomization of liquid fuel in the slow-running working condition and the high-working condition operation and the overall design of the gaseous fuel, the high-efficiency operation of the gas turbine with multiple fuels in the full working condition is realized, the congenital advantages of small volume and light weight of the gas turbine are maintained, the application range of the gas turbine is widened, and the reasonable and effective utilization of energy sources is realized.
Claims (6)
1. A self priming air assisted atomizing dual fuel nozzle, characterized by: the device comprises a liquid fuel swirl atomizing assembly, an air-assisted swirl atomizing assembly, a detachable compaction fixing assembly, a carbon deposit prevention air cooling assembly, a middle side cover (3), an upper side cover (5), an outer cover (14), a gaseous fuel interface (4), a liquid fuel interface (1), an atomizing air interface (2) and a nozzle shell (8); the liquid fuel swirl atomizing assembly comprises a liquid fuel swirler (12) and a liquid fuel nozzle (17); the air auxiliary cyclone atomization assembly comprises an atomization air cyclone (13) and an air nozzle (6); the liquid fuel cyclone (12) is arranged in the atomizing air cyclone (13); the carbon deposition prevention air cooling assembly comprises a heat insulation inner cover (7), fins (32) at the front part of a nozzle shell (8) and fin type flow channels (31); a liquid fuel inlet (23) of the liquid fuel interface (1) and an atomization air inlet (24) of the atomization air interface (2) are respectively provided with a gas-liquid dual-purpose filter element (28) and a detachable stop ring (29);
the outer cover (14) is welded with the heat-insulating inner cover (7), 10 gaseous fuel outlets (15) are arranged on the outer cover (14), and an included angle between the axis direction of the gaseous fuel outlets (15) and the axis direction of the liquid fuel nozzle (17) is 30 degrees; each 2 of the gaseous fuel outlets (15) are 1 group, and each group of 2 gaseous fuel outlets (15) are at an angle of 12.5 DEG and are circumferentially distributed around the central axis of the liquid fuel nozzle (17);
the liquid fuel cyclone (12) is inserted and nested in the inner cavity of the atomizing air cyclone (13), and the liquid fuel cyclone and the atomizing air cyclone are fixed in the nozzle shell (8) in a rated torque mode through a detachable compression fixing assembly; the detachable compaction fixing assembly comprises a sealing cover (10), a gasket (9) and a screw plug (11), wherein the screw plug (11) adopts a double-head straight-thread connection mode, one end of the screw plug is fixed with the nozzle shell (8), the liquid fuel cyclone (12) and the atomizing air cyclone (13) are compacted and fixed in an extrusion mode, and the other end of the screw plug, the gasket (9) and the sealing cover (10) are connected to the end face of the nozzle shell (8) in a rated torque mode to jointly form a liquid fuel cyclone channel and an auxiliary cyclone atomizing air channel; the liquid fuel swirler (12) and the inner wall of the atomizing air swirler (13) form a second liquid fuel passage (34).
2. The self priming air assisted atomizing dual fuel nozzle as set forth in claim 1, wherein: the nozzle housing (8) is provided with a first liquid fuel channel (25) and a first atomization air channel (26), and a second atomization air channel (33) is formed by the inner wall surface of the inner cavity of the nozzle housing (8) and the outer wall surface of the atomization air cyclone (13).
3. The self priming air assisted atomizing dual fuel nozzle as set forth in claim 1, wherein: the upper side cover (5), the middle side cover (3) and the nozzle housing (8) form a first gaseous fuel passage (20), a second gaseous fuel passage (21) and a third gaseous fuel passage (22).
4. The self priming air assisted atomizing dual fuel nozzle as set forth in claim 1, wherein: the heat-insulating inner cover (7) is provided with an anti-carbon air inlet (27) and 6 fourth gaseous fuel channels (30) which are vertically and alternately arranged with the anti-carbon air inlet (27).
5. The self priming air assisted atomizing dual fuel nozzle as set forth in claim 1, wherein: the swirling direction of the swirling groove of the liquid fuel swirler (12) is the same as that of the swirling groove of the atomizing air swirler (13).
6. The self priming air assisted atomizing dual fuel nozzle as set forth in claim 1, wherein: the gaseous fuel interface (4), the liquid fuel interface (1) and the atomizing air interface (2) adopt a sealing connection mode of internal conical surface external threads.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2018101268504 | 2018-02-08 | ||
| CN201810126850 | 2018-02-08 |
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| CN108443912A CN108443912A (en) | 2018-08-24 |
| CN108443912B true CN108443912B (en) | 2023-10-03 |
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| CN201810471003.1A Active CN108443912B (en) | 2018-02-08 | 2018-05-17 | Self-priming air-assisted atomization dual-fuel nozzle |
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Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109827192B (en) * | 2019-03-29 | 2024-04-09 | 中国船舶重工集团公司第七0三研究所 | Air atomizing nozzle with double oil ways and double rotational flow structures |
| CN110529879B (en) * | 2019-07-31 | 2020-12-25 | 中国航发南方工业有限公司 | Two-phase fuel nozzle |
| CN110529877B (en) * | 2019-07-31 | 2021-02-09 | 中国航发南方工业有限公司 | Multi-phase fuel nozzle |
| CN110617499A (en) * | 2019-09-19 | 2019-12-27 | 西安成立航空制造有限公司 | Protection method for carbon deposition of fuel nozzle |
| CN111520767B (en) * | 2020-06-03 | 2023-07-25 | 西安热工研究院有限公司 | Pulse detonation combustor capable of adjusting outlet gas energy distribution |
| CN112460636B (en) * | 2020-10-27 | 2022-04-08 | 中国船舶重工集团公司第七0三研究所 | Double-oil-way single-nozzle double-fuel nozzle |
| CN112483262B (en) * | 2020-10-27 | 2022-11-01 | 中国船舶重工集团公司第七0三研究所 | Integrated device for synchronously controlling fuel quantity and air quantity and control method thereof |
| CN112984558A (en) * | 2021-03-17 | 2021-06-18 | 中国航发动力股份有限公司 | Natural gas nozzle of gas turbine |
| CN113251439B (en) * | 2021-06-24 | 2021-11-16 | 成都中科翼能科技有限公司 | Double-stage co-rotating head device for dual-fuel gas turbine |
| CN113790897A (en) * | 2021-09-15 | 2021-12-14 | 中国船舶重工集团公司第七0三研究所 | Integrated test device for fuel nozzle with flow guide pipe |
| CN114811655A (en) * | 2022-04-25 | 2022-07-29 | 中国船舶重工集团公司第七0三研究所 | Low-emission dual-fuel nozzle of gas turbine |
| CN114837823B (en) * | 2022-04-25 | 2023-10-03 | 中国船舶重工集团公司第七0三研究所 | Gas turbine starting logic method based on dual-fuel control system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1623030A (en) * | 2002-01-28 | 2005-06-01 | 金世英 | Wing structure of air swirling device for internal combustion engine |
| CN101095012A (en) * | 2004-11-03 | 2007-12-26 | 阿尔斯托姆科技有限公司 | Premix burner |
| WO2009069426A1 (en) * | 2007-11-29 | 2009-06-04 | Mitsubishi Heavy Industries, Ltd. | Combustion burner |
| CN202852884U (en) * | 2012-09-03 | 2013-04-03 | 中国航空动力机械研究所 | Double-oil-line centrifugal atomization jet device |
| CN103900107A (en) * | 2014-03-11 | 2014-07-02 | 哈尔滨工程大学 | Dual-fuel nozzle for plasma and gas-assisted atomization burning |
| CN208295959U (en) * | 2018-02-08 | 2018-12-28 | 中国船舶重工集团公司第七0三研究所 | A kind of self-priming air-assisted atomization dual fuel nozzle |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10228140B2 (en) * | 2016-02-18 | 2019-03-12 | General Electric Company | Gas-only cartridge for a premix fuel nozzle |
-
2018
- 2018-05-17 CN CN201810471003.1A patent/CN108443912B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1623030A (en) * | 2002-01-28 | 2005-06-01 | 金世英 | Wing structure of air swirling device for internal combustion engine |
| CN101095012A (en) * | 2004-11-03 | 2007-12-26 | 阿尔斯托姆科技有限公司 | Premix burner |
| WO2009069426A1 (en) * | 2007-11-29 | 2009-06-04 | Mitsubishi Heavy Industries, Ltd. | Combustion burner |
| CN202852884U (en) * | 2012-09-03 | 2013-04-03 | 中国航空动力机械研究所 | Double-oil-line centrifugal atomization jet device |
| CN103900107A (en) * | 2014-03-11 | 2014-07-02 | 哈尔滨工程大学 | Dual-fuel nozzle for plasma and gas-assisted atomization burning |
| CN208295959U (en) * | 2018-02-08 | 2018-12-28 | 中国船舶重工集团公司第七0三研究所 | A kind of self-priming air-assisted atomization dual fuel nozzle |
Non-Patent Citations (2)
| Title |
|---|
| 双燃料燃气轮机喷嘴结构及性能研究;李雅军等;舰船科学技术;第37卷(第5期);第47-53页 * |
| 增压锅炉大容量蒸汽机械雾化喷油器的设计及试验研究;张海龙等;热能动力工程;第29卷(第2期);第171-174页 * |
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