CN114992671B - Combined gas turbine combustion chamber - Google Patents
Combined gas turbine combustion chamber Download PDFInfo
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- CN114992671B CN114992671B CN202210656802.2A CN202210656802A CN114992671B CN 114992671 B CN114992671 B CN 114992671B CN 202210656802 A CN202210656802 A CN 202210656802A CN 114992671 B CN114992671 B CN 114992671B
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- tube bundle
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- fuel
- flame
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 94
- 239000000446 fuel Substances 0.000 claims abstract description 87
- 239000007789 gas Substances 0.000 claims abstract description 40
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 31
- 238000009826 distribution Methods 0.000 claims abstract description 13
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000003546 flue gas Substances 0.000 claims abstract description 7
- 230000002093 peripheral effect Effects 0.000 claims abstract 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 18
- 238000005516 engineering process Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 230000006641 stabilisation Effects 0.000 description 3
- 238000011105 stabilization Methods 0.000 description 3
- 125000004122 cyclic group Chemical group 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000005496 tempering Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 230000010355 oscillation Effects 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
A combined gas turbine combustion chamber belongs to the technical field of gas turbine combustion chambers. The combustion device is arranged in the outer shell, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet is formed in the outer shell; the combustion device comprises a burner and a flame tube, a nozzle tube bundle area communicated with the air inlet cavity is arranged on the burner, the flame tube is arranged at the periphery of the nozzle tube bundle area, and a flue gas outlet communicated with the flame tube is arranged on the outer shell; the periphery of the nozzle tube bundle area is provided with an air distribution cavity wrapping the nozzle tube bundle area, the air distribution cavity is communicated with the air inlet cavity, the front part of the nozzle tube bundle, which is close to the fuel supply area, is a premixing section, the rear part of the nozzle tube bundle, which is close to the flame tube, is a shunting section, the shunting section comprises a middle main flow area and an annular flame stabilizing area arranged at the periphery of the main flow area, and the main flow area and the flame stabilizing area are both communicated with the premixing section; the end of the premixing section is provided with a fuel inlet communicated with the fuel supply area, and the peripheral wall of the premixing section is provided with an air inlet communicated with the air distribution cavity.
Description
Technical Field
The invention relates to the technical field of combustion chambers of gas turbines, in particular to a combined combustion chamber of a gas turbine.
Background
Because of its high-efficiency clean nature, gas turbines have become an indispensable power source in industrial production, and as technology is updated iteratively, gas turbines are continually being developed towards higher efficiency and wider load regulation ranges, and how to achieve stable, low-emission combustion over a wide load condition range is an important performance goal of gas turbine combustors.
Most existing gas engines adopt a combustor adopting Dry Low nitrogen oxide (DLN) combustion technology, the combustor mainly adopts the mode of mixing excessive air and fuel into lean premixed gas so as to inhibit the generation of nitrogen oxides, but the gas engine is developed to a J level, the temperature level of the gas engine is close to the critical value of the DLN effective working range (1670-1900K), if the temperature is further increased, on one hand, the emission of nitrogen oxides is greatly increased even if the air and the fuel are completely premixed, and on the other hand, the conventional swirl premixed combustion mode is adopted, the risks of tempering, self-ignition, thermoacoustic oscillation and the like exist, so that the Dry Low nitrogen oxide (Dry NOx, DLN) combustion technology cannot meet the development of a gas turbine.
Compared with the traditional cyclone burner, the micro-premixing combustion technology mixes air and fuel in a tiny pipeline, improves the mixing uniformity of fuel gas, has a small flame structure and higher fuel gas flow speed, and has the quenching effect of pipe diameter, so that the micro-premixing combustion technology can reduce NOX emission and has good tempering resistance.
Disclosure of Invention
The invention aims to solve the technical problem of providing a combined gas turbine combustion chamber which can improve the mixing uniformity of gas, has a small flame structure and higher gas flow rate.
The invention aims to solve the technical problems by adopting the following technical scheme, and the invention relates to a combined gas turbine combustion chamber, which is characterized in that: the combustion device is arranged in the outer shell, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is arranged on the outer shell;
The combustion device comprises a combustor and a flame tube, wherein a nozzle tube bundle area is arranged on the combustor, a nozzle tube bundle is arranged in the nozzle tube bundle area, the nozzle tube bundle comprises a duty-level nozzle tube bundle arranged in the middle of the combustor and a main combustion-level nozzle tube bundle arranged at the periphery of the duty-level nozzle tube bundle, an upper port and a lower port are arranged on the flame tube, the upper port of the flame tube is arranged at the periphery of the nozzle tube bundle area, and a flue gas outlet communicated with the lower port of the flame tube is arranged on an outer shell;
The burner is provided with a fuel supply area in the direction opposite to the nozzle tube bundle area, and the fuel supply area comprises an duty-stage fuel cavity for supplying fuel to the duty-stage nozzle tube bundle and a main combustion-stage fuel cavity for supplying fuel to the main combustion-stage nozzle tube bundle;
The periphery in nozzle tube bank district is equipped with the gas distribution chamber in parcel nozzle tube bank district, the gas distribution chamber communicates with each other with the air inlet chamber, the front portion that the nozzle tube bank is close to the fuel supply district is the premix section, and the rear portion that is close to the flame tube is the reposition of redundant personnel section, the reposition of redundant personnel section includes middle mainstream region and sets up the cyclic annular steady flame district in mainstream region periphery, mainstream region and steady flame district all communicate with each other with the premix section, and swirl vane is installed with the junction of premix section in steady flame district, and swirl vane axial angle is 5~30, and the tip of premix section is equipped with the communicating fuel inlet with the fuel supply district, is equipped with on the periphery wall of premix section with the communicating inlet port of gas distribution chamber.
The technical problems to be solved by the invention can be further realized by the following technical scheme that the inner diameters of the main combustion stage nozzle tube bundle and the duty stage nozzle tube bundle are 5-12 mm, and the lengths are 15-120 mm.
The technical problem to be solved by the invention can be further solved by the following technical scheme that a class fuel pipe is arranged in the class fuel cavity, and a main fuel pipe is arranged in the main fuel cavity.
The technical problem to be solved by the invention can be further solved by the following technical scheme that the flame tube forms an on-duty combustion zone in a zone communicated with the on-duty nozzle tube bundle zone, and forms a main combustion zone in a zone communicated with the main combustion nozzle tube bundle zone.
The technical problem to be solved by the invention can be further solved by the following technical scheme that the air inlet is arranged on the outer shell and close to the flue gas outlet end.
The technical problem to be solved by the invention can be further solved by the following technical scheme that 1 on-duty fuel pipes are arranged, and at least 2 main fuel pipes are arranged.
Compared with the prior art, the invention has the beneficial effects that,
(1) The nozzle micro-premixing tube bundle is provided with a main flow area and a flame stabilizing area at a downstream outlet, the main flow area does not change the original airflow flowing state, the flame stabilizing area is in an expanding structure, the mixed airflow is expanded in a decelerating way, the flame stabilization is facilitated, the downstream swirl structure is also facilitated, in addition, the energy transfer between the airflows is facilitated due to the fact that the airflows in the main flow area and the flame stabilizing area have larger velocity gradients, and the flame stability is improved;
(2) The swirl vanes are arranged at the inlet of the flame stabilizing region, so that a circle of swirl region can be formed around jet flow in the main flow region, on one hand, the energy transfer of the air flow in the main flow region and the flame stabilizing region is enhanced, and on the other hand, the swirl vanes can be used as a main air flow stabilizing ignition source, the combustion stability is improved, and the operation boundary of the combustion chamber is widened;
(3) Compared with the traditional burner, each nozzle tube bundle of the main nozzle of the burner is relatively independent, and the modular array expansion is carried out according to the load demand, so that the burner has better expansibility; and the nozzle tube bundles are all millimeter-sized, and fuel and air are mixed in millimeter scale, so that more uniform fuel and air premixed gas can be obtained compared with the traditional cyclone premixed burner, the peak flame temperature in the combustion process can be reduced, and a better nitrogen oxide emission reduction effect is realized.
(4) Because the flame formed by the micro-mixing pipe is short and small and the temperature distribution is uniform, the length of the flame tube of the combustion chamber can be greatly shortened.
(5) Because a plurality of micro-premix pipes are distributed in an array form, the sprayed flame is relatively dispersed in the radial direction, the heat release is relatively uniform, and meanwhile, the micro-premix pipes of all main nozzles can adopt different structural schemes, so that the natural frequency difference is realized, the thermo-acoustic coupling probability is reduced, and the problem of unstable combustion can be effectively avoided.
Drawings
FIG. 1 is a schematic illustration of the structural principles of a combustion chamber;
FIG. 2 is a schematic view of a three-dimensional structure of a combustion chamber;
FIG. 3 is a schematic cross-sectional view of a combustor;
FIG. 4 is a top view of a burner body;
FIG. 5 is a schematic view of a nozzle tube bundle;
In the figure: 1. a combustion device; 2. an outer housing; 3. a flame tube; 4. a burner; 21. an air inlet; 22. air flow direction; 23. an air intake chamber; 31. a class combustion zone; 32. a main combustion stage combustion zone; 41. a primary fuel pipe; 41A, main combustion stage fuel inlet; 42. an on-duty fuel pipe; 42A, duty grade fuel inlet; 43. a main combustion grade fuel bin; 44. an on-duty fuel bin; 45. a primary combustion stage nozzle bundle; 45A, an air inlet hole; 45B, nozzle bundle fuel inlet; 45C, swirl vanes; 45D, shunt tubes; 45E, main flow region; 45F, a flame stabilizing area; 46. a class nozzle bundle; 47. a fuel bin and an air separator; 48. a burner body end cap; 49. the fuel flow direction; 410. the flow direction of the mixed gas is shown.
Detailed Description
Specific embodiments of the invention are described further below in order to facilitate a further understanding of the invention by those skilled in the art without limiting the scope of the claims thereto.
Referring to fig. 1-5, a combined gas turbine combustion chamber comprises an outer shell, wherein a combustion device is arranged in the outer shell, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is arranged on the outer shell;
The combustion device comprises a combustor and a flame tube, wherein a nozzle tube bundle area is arranged on the combustor, a nozzle tube bundle is arranged in the nozzle tube bundle area, the nozzle tube bundle comprises a duty-level nozzle tube bundle arranged in the middle of the combustor and a main combustion-level nozzle tube bundle arranged at the periphery of the duty-level nozzle tube bundle, an upper port and a lower port are arranged on the flame tube, the upper port of the flame tube is arranged at the periphery of the nozzle tube bundle area, and a flue gas outlet communicated with the lower port of the flame tube is arranged on an outer shell;
The burner is provided with a fuel supply area in the direction opposite to the nozzle tube bundle area, and the fuel supply area comprises an duty-stage fuel cavity for supplying fuel to the duty-stage nozzle tube bundle and a main combustion-stage fuel cavity for supplying fuel to the main combustion-stage nozzle tube bundle;
The periphery in nozzle tube bank district is equipped with the gas distribution chamber in parcel nozzle tube bank district, the gas distribution chamber communicates with each other with the air inlet chamber, the front portion that the nozzle tube bank is close to the fuel supply district is the premix section, and the rear portion that is close to the flame tube is the reposition of redundant personnel section, the reposition of redundant personnel section includes middle mainstream region and sets up the cyclic annular steady flame district in mainstream region periphery, mainstream region and steady flame district all communicate with each other with the premix section, and swirl vane is installed with the junction of premix section in steady flame district, and swirl vane axial angle is 5~30, and the tip of premix section is equipped with the communicating fuel inlet with the fuel supply district, is equipped with on the periphery wall of premix section with the communicating inlet port of gas distribution chamber.
The internal diameter of the main combustion stage nozzle tube bundle and the duty stage nozzle tube bundle is 5-12 mm, the length is 15-120 mm, the nozzle tube bundles are all millimeter-sized, and the fuel and the air are mixed in millimeter scale, so that more uniform fuel and air premixed gas can be obtained compared with the traditional cyclone premixed burner, the peak flame temperature in the combustion process can be reduced, and the better nitrogen oxide emission reduction effect is realized.
And a class fuel pipe is arranged in the class-on-duty fuel cavity, and a main fuel pipe is arranged in the main fuel cavity.
The cross section area of the rear end of the nozzle tube bundle is larger than that of the front end, the flame stabilizing area is of an expanding structure, the mixed air flow is expanded in a decelerating mode, flame stabilization is facilitated, the downstream rotational flow structure is formed, in addition, the energy transfer between the air flows is facilitated due to the fact that the air flows in the main flow area and the flame stabilizing area have larger speed gradients, and flame stability is improved.
The swirl vanes are also arranged at the inlet of the flame stabilizing region, so that a circle of swirl region can be formed around jet flow in the main flow region, on one hand, the energy transfer of the air flow in the main flow region and the flame stabilizing region is enhanced, and on the other hand, the flame stabilizing region can be used as a main air flow stable ignition source, the combustion stability is improved, and the operation boundary of a combustion chamber is widened;
The flame tube forms an on-duty combustion zone in a zone communicated with the on-duty nozzle tube bundle zone, forms a main combustion zone in a zone communicated with the main combustion nozzle tube bundle zone, and adopts a staged combustion technology: when in a small state, only the duty class works, and the large-state value class and the main combustion class work simultaneously.
The air inlet is arranged on the outer shell body and is close to the flue gas outlet end.
The on-duty grade fuel pipe is provided with 1, and the main combustion grade fuel pipe is provided with 2 at least.
The combustion chamber of the present embodiment includes a burner 4 disposed at the head of the outer housing 2 and connected to the flame tube 3 and disposed in the outer housing 2. The combustion device 1 and the flame tube 4 form an air inlet cavity 23, an air inlet 21 is formed in the bottom of the combustion chamber 2, air flows into the outer shell 2 along an air flow direction 22 through the air inlet 21, flows towards the burner 4 along the air inlet cavity 23, and finally enters the nozzle tube bundle through an air inlet hole 45A on the nozzle tube bundle. The inner cylindrical area formed by wrapping the flame tube is a combustion chamber combustion area, and the combustion chamber combustion area is divided into an on-duty combustion area 31 and a main combustion area 32.
As shown in fig. 3-4, the burner main body 4 adopts a main combustion stage and a duty stage combustion mode, and two main combustion stage fuel pipes 41 and one duty stage fuel pipe 42 are arranged at the front end of the burner main body 4, wherein the main combustion stage fuel pipes 41 are symmetrically distributed, and the duty stage fuel pipes 42 are positioned on the central line of the burner main body 4. The number of the main combustion stage nozzle tube bundles is preferably 3-8, in the embodiment, 3 layers are arranged in a staggered way, so that the influence of air inlet of the outer tube bundles on air inlet of the inner tube bundles is reduced, and the number of the micro-pre-tube bundles of the nozzle on duty is preferably 1-2; in this embodiment, the primary combustion stage nozzle bundle 45 is wrapped around the duty stage nozzle bundle 46 by 360 ° to facilitate flame transfer and flame stabilization. In addition, the fuel silo and air divider plate 47 isolate the air intake chamber and the fuel supply region from each other, and the burner body end cap 48 is positioned adjacent the outlet of the nozzle tube bundle, isolating the air intake chamber from the liner combustion region 24.
The fuel flows into the main fuel stage fuel bin 43 and the duty stage fuel bin 44 along the fuel flow direction 49 through the main fuel stage fuel inlet 41A and the duty stage fuel inlet 42A respectively, the fuel is uniformly dispersed in the fuel bins, then flows into the main fuel stage nozzle tube bundle 45 and the duty stage nozzle tube bundle 46 from the nozzle tube bundle end nozzle tube bundle fuel inlets 45B respectively, and flows downstream after being mixed with air in the tubes, and the mixed premixed air flows into the combustion zone of the flame tube to participate in combustion in the main fuel stage combustion zone 32 and the duty stage combustion zone 31 respectively.
As shown in fig. 5, the main combustion stage nozzle tube bundle 45 and the duty stage nozzle tube bundle 46 in this embodiment have the same structure, and thus the main combustion stage nozzle tube bundle 45 will be described in detail below as an example. The fuel inlet 45B is positioned at the upper end part of the main combustion stage nozzle tube bundle 45 and is communicated with the main combustion stage fuel bin 43; the air inlet holes 45A are arranged on the side wall of the main combustion stage nozzle tube bundle 45, and may adopt a circular hole or a bar hole, etc. in this embodiment, the circular hole is selected, and the number of rows of air holes along the axis is preferably 1-2, and in this embodiment, the number of rows is 1. The position close to the outlet of the nozzle tube bundle is provided with a shunt tube 45D, the shunt tube 45D divides the inner area of the nozzle tube bundle into a main flow area 45E and a flame stabilizing area 45F, the main flow area 45E is inside, the flame stabilizing area 45F is close to the wall surface, and in order to prevent backfire, the height of the straight wall section cavity channel of the inlet of the flame stabilizing area is small enough, so that the quenching effect of the wall surface is utilized to prevent backfire, and in the embodiment, the inlet area ratio of the main flow area and the flame stabilizing area is 100. In addition, still be provided with swirl vane 45C in steady flame district 45F entrance, swirl vane axial angle is 20, because straight wall section cavity height is very little, is difficult to form the swirl structure, in order to form the swirl structure smoothly in the export, steady flame district 45F outer wall adopts the expansion structure, expansion ratio in this embodiment is 1.5.
The fuel and air flow into the main combustion stage nozzle tube bundle 45 from the nozzle tube bundle fuel inlet 45B and the air inlet hole 45A respectively, then flow downstream along the mixed gas flow direction 410 along the mixing edge in the nozzle tube bundle, after flowing through the shunt tube 45D, the mixed gas is divided into two air flows, and the two air flows respectively flow into the main flow area 45E and the flame stabilizing area 45F, wherein the air flow in the main flow area 45F keeps the original flowing state to continue to flow downstream, and finally flows out of the nozzle tube bundle; the airflow in the flame stabilizing region 45F is disturbed by the inlet swirl vanes, flows in the flame stabilizing region, expands and decelerates gradually, finally flows out of the nozzle tube bundle, forms a swirl structure around the main flow, and participates in combustion together with the mixed gas in the main flow region in the combustion region of the combustion chamber.
In the embodiment, the upstream structures of the main combustion stage nozzle tube bundle 45 and the duty stage nozzle tube bundle 46 are not changed, the space occupation ratio of the main flow area is far larger than that of the flame stabilizing area, and the flow state of the upstream mixed gas is not changed in the main flow area, so that all technical advantages of the micro-premix burner are reserved in the present disclosure; the inlet of the flame stabilizing area adopts a swirl vane structure, and under the auxiliary effect of the expansion structure, the mixed gas in the flame stabilizing area finally surrounds the main flow to form a swirl structure, so that the effect of stabilizing an ignition source is achieved, and therefore, the excellent stability of the conventional swirl combustion chamber is also considered.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (6)
1. A combination gas turbine combustor, characterized by: the combustion device is arranged in the outer shell, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is arranged on the outer shell;
The combustion device comprises a combustor and a flame tube, wherein a nozzle tube bundle area is arranged on the combustor, a nozzle tube bundle is arranged in the nozzle tube bundle area, the nozzle tube bundle comprises a duty-level nozzle tube bundle arranged in the middle of the combustor and a main combustion-level nozzle tube bundle arranged at the periphery of the duty-level nozzle tube bundle, an upper port and a lower port are arranged on the flame tube, the upper port of the flame tube is arranged at the periphery of the nozzle tube bundle area, and a flue gas outlet communicated with the lower port of the flame tube is arranged on an outer shell;
The burner is provided with a fuel supply area in the direction opposite to the nozzle tube bundle area, and the fuel supply area comprises an duty-stage fuel cavity for supplying fuel to the duty-stage nozzle tube bundle and a main combustion-stage fuel cavity for supplying fuel to the main combustion-stage nozzle tube bundle;
The periphery of the nozzle tube bundle area is provided with a gas distribution cavity wrapping the nozzle tube bundle area, the gas distribution cavity is communicated with an air inlet cavity, the front part of the nozzle tube bundle, which is close to the fuel supply area, is a premixing section, the rear part of the nozzle tube bundle, which is close to the flame tube, is a diversion section,
The diversion section comprises a middle main flow area and an annular flame stabilizing area arranged at the periphery of the main flow area,
A shunt tube is arranged at a position close to the outlet of the nozzle tube bundle, and divides the inner area of the nozzle tube bundle into a main flow area and a flame stabilizing area; swirl vanes are arranged at the inlet of the flame stabilizing region, and the outer wall of the flame stabilizing region adopts an expansion structure;
the main flow area and the flame stabilizing area are both communicated with the premixing section, a swirl vane is arranged at the joint of the flame stabilizing area and the premixing section, the axial angle of the swirl vane is 5-30 degrees, the end part of the premixing section is provided with a fuel inlet communicated with the fuel supply area, and the peripheral wall of the premixing section is provided with an air inlet communicated with the air distribution cavity.
2. The combination gas turbine combustor as set forth in claim 1, wherein: the inner diameters of the main combustion stage nozzle tube bundle and the duty stage nozzle tube bundle are 5-12 mm, and the lengths are 15-120 mm.
3. The combination gas turbine combustor as set forth in claim 1, wherein: and a class fuel pipe is arranged in the class-on-duty fuel cavity, and a main fuel pipe is arranged in the main fuel cavity.
4. The combination gas turbine combustor as set forth in claim 1, wherein: the flame tube forms an on-duty combustion zone in a zone communicated with the on-duty nozzle tube bundle zone, and forms a main combustion zone in a zone communicated with the main combustion nozzle tube bundle zone.
5. The combination gas turbine combustor as set forth in claim 1, wherein: the air inlet is arranged on the outer shell body and is close to the flue gas outlet end.
6. The combination gas turbine combustor as set forth in claim 1, wherein: the on-duty grade fuel pipe is provided with 1, and the main combustion grade fuel pipe is provided with 2 at least.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210656802.2A CN114992671B (en) | 2022-06-11 | 2022-06-11 | Combined gas turbine combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210656802.2A CN114992671B (en) | 2022-06-11 | 2022-06-11 | Combined gas turbine combustion chamber |
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| CN115978587A (en) * | 2022-12-19 | 2023-04-18 | 江苏中科能源动力研究中心 | Combustion chamber with standing vortex micro-mixing combined nozzle |
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