CN117989564A - Dual-fuel nozzle for low-pollution gas turbine combustor - Google Patents
Dual-fuel nozzle for low-pollution gas turbine combustor Download PDFInfo
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- CN117989564A CN117989564A CN202410216507.4A CN202410216507A CN117989564A CN 117989564 A CN117989564 A CN 117989564A CN 202410216507 A CN202410216507 A CN 202410216507A CN 117989564 A CN117989564 A CN 117989564A
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- 239000000446 fuel Substances 0.000 title claims abstract description 240
- 239000007788 liquid Substances 0.000 claims abstract description 104
- 230000009977 dual effect Effects 0.000 claims abstract description 16
- 238000002485 combustion reaction Methods 0.000 claims description 26
- 238000000889 atomisation Methods 0.000 claims description 10
- 230000008602 contraction Effects 0.000 claims description 7
- 239000007789 gas Substances 0.000 description 25
- 239000003344 environmental pollutant Substances 0.000 description 8
- 231100000719 pollutant Toxicity 0.000 description 8
- 238000002156 mixing Methods 0.000 description 7
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- 229910052799 carbon Inorganic materials 0.000 description 6
- 230000001105 regulatory effect Effects 0.000 description 6
- 238000002679 ablation Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 230000008021 deposition Effects 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical group C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000002283 diesel fuel Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000002803 fossil fuel Substances 0.000 description 2
- 239000003345 natural gas Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Abstract
A dual fuel nozzle for a low emission gas turbine combustor includes a nozzle housing, a coaxially arranged gaseous fuel quill, and a liquid fuel tube. The downstream of the nozzle housing is provided with a venturi, a gaseous fuel passage is formed between the annular gaseous fuel sleeve inner annular wall and the outer annular wall, a primary air passage is formed between the gaseous fuel sleeve inner annular wall and the outer wall of the liquid fuel pipe, and a secondary air passage is formed between the gaseous fuel sleeve outer annular wall and the nozzle housing. The downstream of the annular gaseous fuel passage is provided with a swirl passage which is a hollow cylinder with a spiral passage through which the gaseous fuel is rotationally ejected. The liquid fuel pipe is internally provided with a liquid fuel channel, an atomizing nozzle is arranged at the downstream of the liquid fuel channel, and liquid fuel is sprayed out from the nozzle. A primary cyclone and a secondary cyclone are arranged at the downstream of the primary air channel and the secondary air channel, and the rotation directions of the primary cyclone and the secondary cyclone are opposite.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a dual-fuel nozzle for a low-pollution gas turbine combustion chamber.
Background
In oil gas transportation and exploitation places such as oil exploitation platforms, western gas east delivery pipeline pressurization stations and the like, an oil gas dual-purpose gas turbine is often used as power equipment. Conventionally, such equipment uses oil-associated gas or natural gas as fuel. In special cases, it may use gasoline, diesel oil, etc. as emergency fuel. The development of gas turbine power plants compatible with both gaseous and liquid fuels allows for more rational utilization of the available fuels while powering these particular sites, reducing energy waste. With the progress of technology and the enhancement of environmental awareness, higher requirements are put on the emission of gas turbines at home and abroad, so that the development of low-emission combined fuel gas turbines is also urgent.
The core differences of gas-liquid two-phase fuel gas turbines compared to conventional single-phase fuel gas turbines are mainly reflected in the fuel injection system. As a key component of a dual fuel gas turbine, the dual fuel nozzle not only has a significant impact on the operating efficiency of the gas turbine, but also determines the extent of gas turbine pollutant emissions. Therefore, developing a dual fuel nozzle that can inject gaseous and liquid fuels separately and ensure high atomization and blending quality while reducing pollutant emissions is of great importance.
Disclosure of Invention
The invention aims to solve the technical problems in the background technology and aims to provide a dual-fuel nozzle for a low-pollution gas turbine combustion chamber, which uses liquid fuel under the starting working condition and special condition and uses gaseous fuel under the normal operation working condition. The invention can accelerate the liquid breaking, strengthen the mixing of liquid fuel and air, optimize the fuel distribution, improve the combustion stability, reduce the pollutant emission, and further improve the performance of the combustion chamber.
In order to solve the technical problems, the technical scheme of the invention is as follows:
A dual fuel nozzle for a low pollution gas turbine combustor, comprising a nozzle housing having a gaseous fuel sleeve disposed therein and an annular gaseous fuel passage in a tube wall, an inlet section within the gaseous fuel sleeve being provided with a liquid fuel tube and a liquid fuel passage within the tube; an atomization nozzle is fixed at the outlet end of the liquid fuel pipe, and a venturi is arranged in the downstream of the nozzle shell;
A primary air passage is formed between the gaseous fuel quill and the liquid fuel tube; a secondary air passage is formed between the gaseous fuel sleeve and the nozzle housing; the outlet ends of the primary air channel and the secondary air channel are provided with a primary cyclone and a secondary cyclone, and the rotation directions of the primary cyclone and the secondary cyclone are opposite;
A downstream section of the gaseous fuel channel is provided with a gaseous fuel swirling channel, and a downstream of the gaseous fuel swirling channel is a gaseous fuel outlet; the gaseous fuel channel, the gaseous fuel swirl channel and the gaseous fuel outlet are sequentially communicated.
Further, the venturi comprises: the venturi tube shrinkage section inlet is flush with the outlets of the primary cyclone and the secondary cyclone, the throat of the venturi tube is flush with the outlet of the atomizing nozzle, the venturi tube is coaxially arranged with the liquid fuel tube, and the outlet of the venturi tube is flush with the bottom plate of the combustion chamber.
Further, the outlet end of the gaseous fuel sleeve is flush with the outlets of the primary and secondary cyclones, and the outlet of the gaseous fuel sleeve is inclined toward the axis.
Further, the liquid fuel tube, gaseous fuel quill and nozzle housing are coaxially distributed.
Further, the atomizing nozzle is coaxially arranged at the rear end of the liquid fuel pipe, the appearance is a round table, and a liquid fuel swirl channel is arranged in the atomizing nozzle; the liquid fuel outlet is arranged at the center of the circular table of the atomizing nozzle, and the horizontal position of the liquid fuel outlet is positioned at the throat part of the venturi.
Further, the liquid fuel channel is sequentially communicated with the liquid fuel swirling channel and the liquid fuel outlet.
Further, the primary cyclone and the secondary cyclone adopt cyclone blades or cyclone holes.
Further, the primary cyclones are evenly distributed along an inner circumference of the liquid fuel tube.
Further, the secondary cyclones are evenly distributed along an outer circumference of the liquid fuel pipe.
Further, the air supply pipelines of the primary cyclone and the secondary cyclone are arranged independently, and the proportion of the primary air and the secondary air can be regulated and controlled.
Compared with the prior art, the invention has the advantages that:
The invention relates to a dual-fuel nozzle for a combustion chamber of a low-pollution gas turbine, which mainly comprises a liquid fuel pipe, a gaseous fuel sleeve, a nozzle shell, a secondary cyclone, a primary cyclone, a venturi pipe and an atomization nozzle. The liquid fuel is atomized through the liquid fuel channel through the nozzle, the gaseous fuel is injected through the gaseous fuel channel and the beveled gaseous fuel outlet, the primary air and the secondary air respectively pass through the primary swirler and the secondary swirler to generate swirling flow, and the swirling directions of the primary air and the secondary air flowing out of the primary swirler and the secondary swirler are opposite because the vane swirling directions of the primary swirler and the secondary swirler are opposite. Air with opposite rotation directions is extruded by the contraction section of the venturi tube, and strong shearing vortex is generated at the intersection of the two air flows. The outlet of the atomizing nozzle is arranged near the throat part of the venturi, atomized liquid drops are injected into the shearing vortex at the expansion section of the venturi, the liquid drops are secondarily crushed to generate small liquid drops under the influence of the shearing vortex, and the small liquid drops move downstream under the drive of the cyclone airflow, so that the liquid drops are more uniformly distributed and have a larger range. The temperature distribution of the combustion chamber is more uniform, the combustion of the fuel is more complete, and local high temperature is not easy to generate, so that the emission of pollutants NOx, CO and UHC is reduced. The venturi contraction section can strengthen the shearing action of the primary air and the secondary air, and the venturi expansion section can prevent liquid drops from being brought back to the outlet of the atomizing nozzle by the backflow air flow, so that the atomizing nozzle is prevented from being ablated and carbon deposit. Because the primary air and the secondary air come from independent channels, the respective air quantity can be regulated and controlled at will, and the risk of unstable combustion caused by the fact that the cyclone air is opposite in direction and close in cyclone strength and the overall cyclone strength is lower after mixing in the prior art can be avoided. The liquid fuel quantity and the gas fuel quantity of the dual-fuel nozzle can be regulated in proportion, so that the application range is wider. The gaseous fuel can be well mixed with the swirling air while ensuring good atomization effect of the liquid fuel. Compared with the prior art, the invention has the advantages of wider application working condition range, better atomization effect, difficult occurrence of ablation and carbon deposition, more stable combustion, more uniform combustion chamber temperature distribution, lower pollutant emission and the like.
Drawings
FIG. 1, a cross-sectional view of the present invention;
FIG. 2 is a schematic cross-sectional perspective view of the present invention;
Fig. 3, a schematic perspective view of the present invention.
FIG. 4 is a schematic view of the present invention with the outer ring of the gaseous fuel quill cut away.
Reference numerals:
1-a liquid fuel pipe; 2-gaseous fuel quill; 3-a nozzle housing; 4-secondary cyclone; 5-primary cyclone; 6-venturi; 7-atomizing nozzles; 8-liquid fuel passages; 9-primary air channels; 10-gaseous fuel passage; 11-secondary air channels; 12-a gaseous fuel swirl passage; 13-venturi constriction; 14-a venturi expansion section; 15-gaseous fuel outlet; 16-liquid fuel swirl passages; 17-liquid fuel outlet; 18-droplets of liquid fuel; 19-gaseous fuel; 20-venturi constriction angle; 21-venturi divergence angle; 22-gaseous fuel outlet angle; 23-gaseous fuel swirl passage swirl angle.
Detailed Description
The following describes specific embodiments of the present invention with reference to examples:
It should be noted that the structures, proportions, sizes and the like illustrated in the present specification are used for being understood and read by those skilled in the art in combination with the disclosure of the present invention, and are not intended to limit the applicable limitations of the present invention, and any structural modifications, proportional changes or size adjustments should still fall within the scope of the disclosure of the present invention without affecting the efficacy and achievement of the present invention.
Also, the terms such as "upper," "lower," "left," "right," "middle," and "a" and the like recited in the present specification are merely for descriptive purposes and are not intended to limit the scope of the invention, but are intended to provide relative positional changes or modifications without materially altering the technical context in which the invention may be practiced.
Example 1:
As shown in fig. 1-4, a dual fuel nozzle for a low pollution gas turbine combustor includes a liquid fuel tube 1, a gaseous fuel sleeve 2, a nozzle housing 3, a secondary swirler 4, a primary swirler 5, a venturi 6, and an atomizing nozzle 7. The liquid fuel can be liquid fossil fuel such as kerosene, diesel oil and the like, and the gaseous fuel can be gaseous fossil fuel such as petroleum exploitation associated gas or natural gas and the like. A venturi 6 is arranged at the downstream of the nozzle housing 3, an annular gas fuel sleeve 2 which is coaxially arranged is arranged inside the nozzle housing 3, a liquid fuel pipe 1 is coaxially arranged in the gas fuel sleeve 2, a primary air passage 9 is formed between the inner annular wall of the gas fuel sleeve 2 and the outer wall of the liquid fuel pipe, and a secondary air passage 11 is formed between the outer annular wall of the gas fuel sleeve 2 and the nozzle housing 3. An annular gaseous fuel channel 10 is formed between the inner annular wall and the outer annular wall of the annular gaseous fuel sleeve 2 and in the pipe wall, a gaseous fuel rotational flow channel 12 is arranged at the downstream section of the annular gaseous fuel channel 10, the rotational flow channel 12 is a hollow cylinder with a spiral channel arranged on the rotational flow channel 12, the inner wall of the hollow cylinder is the inner annular wall of the gaseous fuel sleeve 2, and the outer wall of the cylinder is the outer annular wall of the gaseous fuel sleeve 2; after entering the gaseous fuel quill 2, the gaseous fuel is swirled out through the gaseous fuel passage 10 via the gaseous fuel swirl passage 12, which is a gaseous fuel outlet 15. A liquid fuel channel 8 is arranged in the liquid fuel pipe 1; an atomizing nozzle 7 is fixed downstream of the liquid fuel passage 8, and liquid fuel is discharged from the atomizing nozzle 7. A primary cyclone 5 and a secondary cyclone 4 are arranged downstream of the primary air channel 9 and the secondary air channel 11; the first-stage cyclone 5 and the second-stage cyclone 4 have opposite rotation directions; the air in the primary air passage 9 and the secondary air passage 11 is ejected through the primary cyclone 5 and the secondary cyclone 4, respectively. Primary air passage and secondary air passage
FIG. 1 is a schematic diagram showing the structure of the present invention. In the figure, the double-swirl combined nozzle mainly comprises a liquid fuel pipe 1, a gaseous fuel sleeve 2, a nozzle shell 3, a secondary swirler 4, a primary swirler 5, a venturi 6 and an atomizing nozzle 7. Also shown are liquid fuel passages 8, primary air passages 9, gaseous fuel passages 10, secondary air passages 11, gaseous fuel swirl passages 12, venturi constriction 13, venturi expansion 14, gaseous fuel outlet 15, liquid fuel swirl passages 16, liquid fuel outlet 17, liquid fuel droplets 18, gaseous fuel 19, venturi constriction 20, venturi expansion 21, gaseous fuel outlet 22.
The liquid fuel pipe 1 is arranged at the axis, a liquid fuel channel 8 is arranged inside, the front end is a liquid fuel inlet, and the rear end is in seamless connection with the atomizing nozzle 7. The atomizing nozzle 7 and the liquid fuel pipe 1 are coaxially arranged.
An annular gaseous fuel channel 10 is formed between the inner annular wall and the outer annular wall of the annular gaseous fuel sleeve 2 and in the pipe wall, a gaseous fuel rotational flow channel 12 is arranged at the downstream section of the annular gaseous fuel channel 10, the rotational flow channel 12 is a hollow cylinder with a spiral channel arranged on the rotational flow channel 12, the inner wall of the hollow cylinder is the inner annular wall of the gaseous fuel sleeve 2, and the outer wall of the cylinder is the outer annular wall of the gaseous fuel sleeve 2; after entering the gaseous fuel quill 2, the gaseous fuel is swirled out through the gaseous fuel passage 10 via the gaseous fuel swirl passage 12, which is a gaseous fuel outlet 15. The gaseous fuel outlet 15 is angled at a gaseous fuel outlet angle 22 from the nozzle axis and the gaseous fuel swirl passage 12 is angled at a gaseous fuel swirl passage swirl angle 23 from the nozzle axis.
The gaseous fuel sleeve 2 is sleeved outside the liquid fuel pipe 1, and the two are coaxially arranged. A primary air passage 9 is formed between the inner annular wall of the gaseous fuel quill 2 and the outer wall of the liquid fuel tube. The primary cyclone 5 is arranged coaxially with the liquid fuel pipe 1. The primary swirler 5 is fixed in the primary air passage 9, and the primary swirler 5 is in seamless connection with the outer wall of the liquid fuel pipe 1 and the inner wall of the gaseous fuel sleeve 2 respectively.
The nozzle housing 3 is sleeved outside the gaseous fuel sleeve 2, and the two are coaxially arranged. A secondary air passage 11 is formed between the outer annular wall of the gaseous fuel sleeve 2 and the nozzle housing 3. The secondary cyclone 4 is arranged coaxially with the liquid fuel pipe 1. The secondary swirler 4 is fixed in the secondary air passage 11, and the secondary swirler 4 is seamlessly connected with the outer wall of the gaseous fuel sleeve 2 and the inner wall of the nozzle housing 3 respectively.
The atomizing nozzle 7 is coaxially installed at the rear end of the fuel pipe 1, has a truncated cone shape in appearance, and has a liquid fuel swirl passage 16 therein. The liquid fuel outlet 17 is positioned at the center of the truncated cone of the atomizing nozzle 7, and the liquid fuel outlet 17 is horizontally positioned near the throat of the venturi tube 6.
The venturi 6 is composed of a venturi contraction section 13 and a venturi expansion section 14, wherein the included angle between the venturi contraction section 13 and the axis of the nozzle is a venturi contraction angle 20, and the included angle between the venturi expansion section 14 and the axis of the nozzle is a venturi expansion angle 21. A venturi 6 is arranged coaxially with the liquid fuel pipe 1, the venturi 6 being closely connected to the nozzle housing 3. The outlet end face of the venturi 6 is flush with the floor of the combustion chamber. The venturi 6 throat is approximately the same height as the liquid fuel outlet 17 end face.
Example 2:
The invention relates to a dual-fuel nozzle for a combustion chamber of a low-pollution gas turbine, which has the following working principle:
The liquid fuel enters the liquid fuel channel 8, passes through the nozzle fuel channel 16, generates rotational flow, and is sprayed out from the nozzle outlet 17 to finish primary atomization. The gaseous fuel enters the gaseous fuel passage 10, passes through the gaseous fuel swirl passage 12, generates a swirl flow, and is then ejected from the gaseous fuel outlet 15. The primary air enters from the primary air passage 9, and is changed into primary swirling air by the primary swirler 5 arranged at the end of the primary air passage 9. The secondary air enters from the secondary air passage 11, and is changed into secondary swirling air by the secondary swirler 4 arranged at the end of the secondary air passage 11. After the primary cyclone air and the secondary cyclone air come out of the cyclone, the primary cyclone air and the secondary cyclone air meet at the venturi constriction section 13, and the primary cyclone air and the secondary cyclone air are opposite in rotation direction due to the fact that the primary cyclone air and the secondary cyclone air are opposite in rotation direction, so that the primary cyclone air and the secondary cyclone air are extruded by the venturi constriction section 13 under the action of the primary cyclone air and the secondary cyclone air, and a strong turbulent flow shearing band is generated at the junction of two airflows. The shearing action by the highly turbulent shear band continues to the venturi expansion section 14. The gaseous fuel is ejected from the gaseous fuel outlet 15 and is sheared by the primary and secondary swirl air in the venturi constriction 13 to complete mixing with the air. The liquid fuel outlet 17 is located in the venturi throat and primary atomized droplets produced by the nozzle are injected into the shear band. Under the influence of the strong turbulence shear band, the liquid drops are accelerated to break up, secondary atomization is rapidly carried out, uniform and fine liquid fuel drops 18 are generated, and the liquid fuel drops 18 and the gaseous fuel 19 can be uniformly mixed in the air. The primary swirl air and the secondary swirl air are respectively and independently supplied with air, and the air quantity of the primary swirl air and the secondary swirl air can be independently regulated and controlled, so that the phenomenon that the primary swirl air and the secondary air are close in swirl strength and opposite in swirl direction and are offset is avoided, and further the swirl strength at the outlet of the venturi tube is too small to generate a stable central backflow zone in the combustion chamber. During operation of a conventional nozzle, the central recirculation zone tends to carry liquid fuel droplets 18 back to the nozzle, which may lead to nozzle ablation or carbon build-up, and the venturi expansion section 14 may act to weaken the highly turbulent shear band gas recirculation, preventing atomized droplets from returning to the nozzle. Compared with the prior nozzle, the nozzle has the advantages of good atomization effect, uniform mixing of fuel and air, stable central backflow area, high combustion performance, difficult ablation, carbon deposition, less pollutant discharge and the like, and is suitable for a dual-fuel combustion chamber.
Example 3:
The advantage of adopting above-mentioned structure lies in:
Compared with the existing two-stage cyclone nozzle with the same rotation direction, because the rotation directions of the first-stage cyclone 5 and the second-stage cyclone 4 are opposite, two cyclone airflows with opposite rotation directions can be generated at the outlet of the cyclone, a strong turbulence shear band is generated at the contact position of the two airflows with opposite rotation directions under the extrusion of the venturi constriction section 13, and the shear band is continued to the venturi expansion section. In venturi expansion section 14, atomized droplets 18 from liquid fuel outlet 17 and gaseous fuel 19 from gaseous fuel outlet 15 are injected into a shear zone which enhances droplet secondary atomization and increases fuel to air mixing so that both liquid and gaseous fuel are evenly distributed at the head of the combustion chamber. Compared with the prior art, the two-stage cyclone has the advantages that the two-stage cyclone has opposite rotation directions, the droplet breaking is enhanced, the fuel distribution is improved, the droplets have the effect of near premixed combustion, the local high temperature of the combustion chamber is reduced, and the pollutant emission is further reduced.
Compared with the prior two-stage cyclone nozzle, the two-stage cyclone nozzle has the advantages that the air flow ratio of the first-stage air to the second-stage air can be conveniently regulated and controlled, the reasonable air ratio distribution can prevent the mutual offset of the first-stage air and the second-stage air cyclone, the crushing effect of a shearing band between the first-stage air and the second-stage air on atomized liquid drops and the mixing of fuel and air can be enhanced, and stable strong cyclone can be generated at the head part of a combustion chamber, so that the combustion stability is improved and the pollutant emission is reduced.
In contrast to the prior art nozzle designs, the present invention employs a venturi arrangement at the end of the nozzle. In the present invention, the venturi 6 is composed of a venturi constriction section 13 and a venturi expansion section 14. Because the swirling flow can create a backflow in the combustion chamber, the backflow tends to carry atomized droplets back to the nozzle outlet, causing nozzle ablation and carbon deposition. The venturi expansion section can weaken backflow at the outlet of the nozzle, reduce the probability of liquid drops being brought back to the nozzle, and reduce the risks of nozzle ablation and carbon deposition.
In contrast to the prior art nozzle designs, the present invention uses two mutually independent fuel passages, liquid combustion is provided only by liquid fuel passage 8 and gaseous fuel is provided only by gaseous fuel passage 10, so that the amount of liquid fuel and the amount of gaseous fuel can be regulated at will. Therefore, compared with the traditional single-channel nozzle, the dual-fuel combustion chamber can be used in the dual-fuel combustion chamber, and the working condition applicability is wider.
Example 4:
in an alternative embodiment:
the invention can be integrally formed by 3D printing or can be finished by machining and assembling.
The primary cyclone 5 and the secondary cyclone 4 can be in the form of cyclone blades or cyclone holes.
The primary and secondary cyclones 5, 4 may be seamlessly attached to the walls of the gaseous fuel sleeve 2, nozzle housing 3 and liquid fuel tube 1 in any manner.
The venturi 6 may be attached to the housing 3 by welding, threading, etc., or the venturi 6 and the housing 3 may be integrated.
The atomizing nozzle 7 may be connected to the liquid fuel pipe 1 by welding, screw threads, or the like, or the atomizing nozzle 8 and the liquid fuel pipe 1 may be integrated.
The atomizing nozzle 7 may be of a pressure atomizing type, a pneumatic atomizing type or a combination type.
The ratio of the internal and external air is set between 10:1 and 1:10; the cyclone number of the primary cyclone 6 is between 0.7 and 1.1; the swirl number of the secondary cyclone 4 is between 0.55 and 1.05; the venturi shrinkage angle 19 is 30-45 degrees; the venturi divergence angle 20 is 20-60 degrees; the gaseous fuel outlet angle 22 is 0-30; the swirl angle 23 of the gas fuel swirl passage is 20-35 degrees; the inner diameter of the primary cyclone is 15 mm-30 mm; the outer diameter of the primary cyclone is 20 mm-40 mm; the inner diameter of the secondary cyclone is 27 mm-47 mm; the outer diameter of the secondary cyclone is 32 mm-57 mm; the lengths of the primary cyclone and the secondary cyclone are 5 mm-50 mm; the venturi throat is in the horizontal range of-1.5 cm of the liquid fuel outlet 17; the diameter of the venturi throat is 20 mm-38 mm; the ratio of the length of the venturi constriction 13 to the diameter of the venturi throat is 0.35-1.1.
While the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes may be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Many other changes and modifications may be made without departing from the spirit and scope of the invention. It is to be understood that the invention is not to be limited to the specific embodiments, but only by the scope of the appended claims.
Claims (10)
1. A dual fuel nozzle for a low pollution gas turbine combustor, comprising a nozzle housing (3), the nozzle housing (3) internally provided with a gaseous fuel sleeve (2) and an annular gaseous fuel passage (10) in the pipe wall, an inlet section in the gaseous fuel sleeve (2) provided with a liquid fuel pipe (1), and a liquid fuel passage (8) in the pipe; an atomization nozzle (7) is fixed at the outlet end of the liquid fuel pipe (1), and a venturi (6) is arranged in the downstream of the nozzle shell (3);
-a primary air channel (9) is formed between the gaseous fuel sleeve (2) and the liquid fuel tube (1); -a secondary air channel (11) is formed between the gaseous fuel sleeve (2) and the nozzle housing (3); the outlet ends of the primary air channel (9) and the secondary air channel (11) are provided with a primary cyclone (5) and a secondary cyclone (4), and the rotation directions of the primary cyclone (5) and the secondary cyclone (4) are opposite;
a downstream section of the gaseous fuel passage (10) is provided with a gaseous fuel swirl passage (12), and a gaseous fuel outlet (15) is arranged downstream of the gaseous fuel swirl passage (12); the gaseous fuel passage (10), the gaseous fuel swirling passage (12) and the gaseous fuel outlet (15) are communicated in sequence.
2. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1, wherein the venturi (6) comprises: the venturi tube comprises a contraction section (13) and an expansion section (14), wherein the inlet of the venturi tube contraction section (13) is flush with the outlets of the primary cyclone (5) and the secondary cyclone (4), the throat of the venturi tube (6) is flush with the outlet of the atomizing nozzle (7), the venturi tube (6) is coaxially arranged with the liquid fuel tube (1), and the outlet of the venturi tube (6) is flush with the bottom plate of the combustion chamber.
3. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1 wherein the outlet end of the gaseous fuel sleeve (2) is flush with the outlets of the primary swirler (5) and the secondary swirler (4), the outlet of the gaseous fuel sleeve (2) being inclined to the axial center.
4. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1, wherein the liquid fuel tube (1), gaseous fuel sleeve (2) and nozzle housing (3) are coaxially distributed.
5. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1, wherein the atomizing nozzle (7) is coaxially mounted at the rear end of the liquid fuel tube (1), in the shape of a circular truncated cone, with a liquid fuel swirl passage (16) inside; the liquid fuel outlet (17) is arranged at the center of the circular truncated cone of the atomizing nozzle 7, and the horizontal position of the liquid fuel outlet (17) is positioned at the throat part of the venturi tube (6).
6. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1 wherein the liquid fuel passage (8) communicates with a liquid fuel swirl passage (16) and a liquid fuel outlet (17) in sequence.
7. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1, wherein the primary swirler (5) and secondary swirler (4) employ swirl vanes or swirl holes.
8. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1 wherein the primary swirlers (5) are evenly distributed along the inner circumference of the liquid fuel sleeve (2).
9. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1 wherein the secondary swirlers (4) are evenly distributed along the outer circumference of the liquid fuel sleeve (2).
10. A dual fuel nozzle for a low pollution gas turbine combustor as claimed in claim 1 wherein the air supply lines of the primary (5) and secondary (4) swirlers are arranged separately, the ratio of primary and secondary air being adjustable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410216507.4A CN117989564A (en) | 2024-02-27 | 2024-02-27 | Dual-fuel nozzle for low-pollution gas turbine combustor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410216507.4A CN117989564A (en) | 2024-02-27 | 2024-02-27 | Dual-fuel nozzle for low-pollution gas turbine combustor |
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| CN117989564A true CN117989564A (en) | 2024-05-07 |
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| CN202410216507.4A Pending CN117989564A (en) | 2024-02-27 | 2024-02-27 | Dual-fuel nozzle for low-pollution gas turbine combustor |
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| US20050198965A1 (en) * | 2004-03-12 | 2005-09-15 | John Henriquez | Primary fuel nozzle having dual fuel capability |
| EP2213938A2 (en) * | 2009-02-03 | 2010-08-04 | General Electric Company | Combustion system burner tube |
| CN105716113A (en) * | 2016-02-06 | 2016-06-29 | 中国科学院工程热物理研究所 | Double-cyclone premixing burner |
| CN205481130U (en) * | 2016-02-06 | 2016-08-17 | 中国科学院工程热物理研究所 | Vortex premix burner |
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2024
- 2024-02-27 CN CN202410216507.4A patent/CN117989564A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0417380D0 (en) * | 2003-08-05 | 2004-09-08 | Japan Aerospace Exploration | Fuel/air premixer for gas turbine combustor |
| US20050198965A1 (en) * | 2004-03-12 | 2005-09-15 | John Henriquez | Primary fuel nozzle having dual fuel capability |
| EP2213938A2 (en) * | 2009-02-03 | 2010-08-04 | General Electric Company | Combustion system burner tube |
| CN105716113A (en) * | 2016-02-06 | 2016-06-29 | 中国科学院工程热物理研究所 | Double-cyclone premixing burner |
| CN205481130U (en) * | 2016-02-06 | 2016-08-17 | 中国科学院工程热物理研究所 | Vortex premix burner |
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