CN116608491B - A combustion chamber with an axial air intake secondary burner - Google Patents

A combustion chamber with an axial air intake secondary burner Download PDF

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Publication number
CN116608491B
CN116608491B CN202310324964.0A CN202310324964A CN116608491B CN 116608491 B CN116608491 B CN 116608491B CN 202310324964 A CN202310324964 A CN 202310324964A CN 116608491 B CN116608491 B CN 116608491B
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China
Prior art keywords
burner
flame tube
fuel
combustor
duty
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CN202310324964.0A
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CN116608491A (en
Inventor
张宇明
彭志胜
臧鹏
董永杰
周豪
衡思江
傅燕妮
隋永枫
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Hangzhou Steam Turbine Power Group Co Ltd
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Hangzhou Steam Turbine Power Group Co Ltd
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Priority to CN202310324964.0A priority Critical patent/CN116608491B/en
Publication of CN116608491A publication Critical patent/CN116608491A/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/26—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid with provision for a retention flame
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/60—Devices for simultaneous control of gas and combustion air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/84—Flame spreading or otherwise shaping
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

The invention discloses a combustion chamber with an axial air inlet secondary combustor, and relates to the technical field of gas turbines. The combustion chamber comprises a secondary combustor, a main-stage combustor, an on-duty combustor and a flame tube, wherein the lower end portion of the secondary combustor extends into the flame tube and is communicated with the interior of the flame tube, the main-stage combustor is arranged at the front end portion of the flame tube, the tail end of the main-stage combustor is communicated with the flame tube, the on-duty combustor is arranged at the front end portion of the flame tube, the tail end of the on-duty combustor is communicated with the flame tube, and the main-stage combustor and the on-duty combustor are arranged at the same axial position at the top of the flame tube. The secondary combustor shell is provided with the rectifying hole, and forms a rectifying cavity together with the flame tube and the casing, so that air and fuel deflection caused by different static pressure differences between the front and rear of the secondary combustor is improved.

Description

Combustion chamber with axial air inlet secondary combustor
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustion chamber with an axial air inlet secondary combustor.
Background
The gas turbine takes low-carbon clean fuel such as natural gas as a main component, can eliminate the impact caused by unstable renewable energy sources such as wind energy, solar energy and the like, and achieves the purposes of energy peak regulation and carbon emission reduction. This places higher demands on the gas turbine combustor, which is required to meet the requirements of stable operation and low emissions over a wide range of operating conditions.
The staged combustion technology of the combustion chamber is used as an efficient and clean combustion technology, can meet the requirement of low-emission stable combustion of the combustion chamber of the gas turbine in a wide load range, and is widely focused and researched by various gas turbine manufacturers. Since the fuel of the conventional gas turbine combustor is injected into the liner entirely by the head swirler, this results in the combustor meeting emissions requirements only in a narrow range of rated loads, and only sacrificing emissions performance for maintaining stable combustion at low load conditions. Staged combustion technology, i.e., the introduction of air and fuel at different locations in the combustion chamber, includes fuel staging and air staging. Fuel staging is commonly used, including radial staging and axial staging. The fuel is injected into the flame tube for combustion at different radial positions of the head of the combustion chamber in radial classification. Axial staging is the introduction of fuel into the flame tube at different axial locations of the flame tube. The fuel supply amounts of the respective stages are controlled so as to change the equivalence ratios of the respective stages, and the temperatures of the respective regions are controlled so that the combustion temperatures are at NOx, CO, UHC to generate a region where the combustion temperatures are relatively low.
The GE combustion chamber mostly adopts a head radial staged combustion technology, the head is divided into a plurality of small combustors, and fuel is supplied to the head combustors in the low-load working condition of the gas turbine. As the load increases, the number of head-fed burners increases until full load is reached. This results in a complex overall control system that requires switching between different burners at different loads. The Japanese Kawasaki combustor afterburner adopts axial staged combustion, air and fuel are introduced into the rear part of the flame tube, but the afterburner adopts a radial air inlet mode, so that uneven distribution of air and fuel at the outlet of the afterburner is easily caused, and the bypass valve structure of the Japanese Sanpa combustor realizes axial air staging, but the bypass valve does not introduce fuel staging. At present, a gas turbine combustion chamber for realizing air and fuel staged combustion by adopting axial air inlet of a secondary combustor is not found at home and abroad.
Chinese patent publication No. CN107110506a discloses a burner, a burner with the burner, and a gas turbine. The burner can mix hydrocarbon first fuel, second fuel and combustion air in advance, inject premixed gas with thin concentration and uniform distribution into a combustion chamber of a combustor, and can restrain the emission amount of NOx. By injecting hydrogen gas from each of the second fuel injection nozzles protruding into the premixing flow passage into the flow of combustion air flowing from the outer periphery of the outer tube toward the center on the upstream side of the premixing flow passage, the primary mixed gas having a uniform concentration distribution is generated without the influence of the low-velocity flow field of the combustion air. Then, the natural gas is injected from the first fuel injection nozzle into the primary mixed gas, whereby the natural gas having a high specific gravity and the primary mixed gas are sufficiently stirred and mixed to generate a secondary mixed gas (premixed gas) having a thin concentration and a uniform distribution compared with the primary mixed gas. Although this patent provides a plurality of fuel introduction portions, the radial air intake method adopted by the fuel introduction portions tends to cause uneven distribution of the burner outlet air and fuel.
Chinese patent No. CN1705815 discloses a gas turbine combustor capable of reducing combustion vibration to stably reduce NOx, comprising a first case installed outside a subject body having an inner pipe, a transition piece or a bypass pipe to form a first inner space having a predetermined volume, a first throat having a predetermined length with one end opened to a sidewall of the subject body and the other end opened to the first inner space, wherein a first impedance element having a plurality of through holes is inserted and fitted to one end. The fluid particles are effectively captured by the first impedance element as a vibration element of combustion vibration generated in the combustion zone while resonating with air of the first internal space connected through the first throat to vibrate in the vicinity of the first impedance element, thereby suppressing the vibration amplitude thereof. However, this patent does not disclose a fuel staging arrangement and discloses a structure in which a plurality of housings or the like are provided, which makes the adjustment of the entire burner cumbersome.
Disclosure of Invention
In order to solve the problems of unstable operation and high emission of the combustion chamber in a wide working condition range, the invention provides the combustion chamber with the axial air inlet secondary combustor.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
A combustion chamber with an axial air inlet secondary combustor comprises a secondary combustor, a primary combustor, a duty combustor and a flame tube;
the lower end part of the secondary burner extends to the interior of the flame tube, and the lower end part of the secondary burner is communicated with the interior of the flame tube;
the main-stage burner is arranged at the front end part of the flame tube, and the tail end of the main-stage burner is communicated with the flame tube;
the on-duty burner is arranged at the front end part of the flame tube, and the tail end of the on-duty burner is communicated with the flame tube;
the main-stage burner and the duty burner are arranged at the same axial position at the top of the flame tube;
The secondary combustor at least comprises a short pipe, a central spray rod, secondary axial swirl vanes and a shell, wherein the central lines of the central spray rod, the shell and the short pipe are positioned on the same straight line.
Based on the technical scheme, the secondary axial swirl blades are arranged on the periphery of the central spray rod, the secondary axial swirl blades are positioned in the shell, the lower end of the short pipe extends into the flame tube, and the short pipe is communicated with the flame tube.
Based on the technical scheme, further, the inside of the secondary axial swirl vane is of a cavity structure, and a plurality of secondary fuel guide holes can be formed in the secondary axial swirl vane.
Based on the technical scheme, further, the included angle between the central axis of the secondary combustor and the horizontal axis of the flame tube is 60-90 degrees.
Based on the technical scheme, the number of the secondary combustors is 3-8, and the distance D between the secondary combustors and the tail end of the primary combustor is larger than or equal to the diameter D of the flame tube.
Based on the technical scheme, further, one end of the secondary combustor is provided with a secondary combustor fuel control valve.
Based on the technical scheme, the combustion chamber further comprises a casing, the casing is arranged on the periphery of the flame tube, the casing and the flame tube are coaxially arranged, and an air channel is formed between the outer surface of the flame tube and the inner surface of the casing.
Based on the technical scheme, further, the secondary combustor is fixed on the casing, a rectifying hole is formed in the casing of the secondary combustor, the rectifying hole comprises a plurality of through holes, the cross section area of each through hole is larger than that of the outlet of the short pipe, and the inner surface of the casing form a ring cavity.
Based on the technical scheme, further, the upper end part of the central spray rod is sleeved with an upper flat plate and a lower concave plate, the lower end face of the upper flat plate is connected with the upper end face of the lower concave plate to form an annular groove, and a plurality of secondary premixed fuel introduction holes are formed in the lower end face of the lower concave plate.
Based on the technical scheme, further, a secondary premixed fuel introduction hole is formed in the central spray rod, and the secondary premixed fuel introduction hole is positioned at the upper end of the secondary axial swirl vane.
Based on the technical scheme, further, at least one secondary diffusion fuel introduction hole is formed in the lower end portion of the central spray rod, and the total area of the secondary premixed fuel introduction holes is larger than or equal to the total area of the secondary diffusion fuel introduction holes.
Based on the technical scheme, further, one end of the primary combustor is provided with a primary fuel control valve, the primary combustor at least comprises one cyclone blade, the at least one cyclone blade forms a radial cyclone, and a primary fuel introduction hole for injecting fuel into the radial cyclone is further formed in the cyclone blade.
Based on the technical scheme, the premixed fuel and air form fuel/air mixed gas through the secondary premixed fuel introduction holes, the proportion of the premixed fuel is not lower than 40% of the fuel, and the diffusion fuel enters the short pipe through the secondary diffusion fuel introduction holes.
Based on the technical scheme, furthermore, the on-duty burner is a diffusion burner with axial air inlet, and the top end of the on-duty burner is provided with an on-duty fuel introduction hole for spraying on-duty fuel into the flame tube, and the on-duty fuel introduction holes are formed into a plurality of on-duty fuel introduction holes. The on-duty burner is positioned at the center of the head of the combustion chamber. When the fuel and air enter the flame tube, the fuel and air are mixed and combusted at the same time, so that stable diffusion flame is formed. One end of the on-duty burner is provided with an on-duty fuel control valve.
Based on the technical scheme, the number of the cyclone blades can be 12-20.
Based on the above technical scheme, further, the air inlet mode of the main stage burner is a radial air inlet mode.
Based on the technical scheme, air is mixed with fuel injected from the fuel introduction holes through the radial swirler vanes and enters the flame tube to form premixed combustion flame.
Compared with the prior art, the invention has the following beneficial effects:
(1) The invention comprises a main-stage burner, a duty burner and a secondary burner, wherein the main-stage burner and the duty burner are positioned at the head part of a combustion chamber, the secondary burner is positioned at the rear part of a flame tube, partial air and fuel are introduced into the flame tube from the secondary burner and have the same flow direction with main air flow in the flame tube, and when the installation angle of the secondary burner and the flame tube is 60-90 degrees, the disturbance on the main air flow in the flame tube is reduced, the arrangement is flexible, and the overall diameter of the combustion chamber is reduced.
(2) The secondary combustor shell is provided with the rectifying hole, and forms a rectifying cavity together with the flame tube and the casing, so that air and fuel deflection caused by different static pressure differences between the front and rear of the secondary combustor is improved.
(3) The secondary burner in the invention is positioned in a place which does not influence the combustion structure of the main combustion area, and because the secondary burner in the invention can shunt a part of air, the air quantity is not excessive when the main burner is in low load, the fuel/air proportion of the main burner can be kept in a re-stabilization zone, namely the stability of the main combustion area can be ensured under the condition of variable load working condition, wherein the main combustion area refers to the area of enveloping premixed flame and duty flame in the flame tube, and the combustion structure refers to the specific combustion flame temperature, form and position finally formed by the flow field form, fuel concentration distribution, fuel/air proportion and the like in a certain area.
(4) The secondary burner introduces partial air and fuel, wherein the secondary burner only introduces air during low load to ensure stable combustion of the air-fuel ratio of the main combustion area of the combustion chamber in a reasonable range, and excessive fuel is introduced into the flame tube from the secondary burner during high load to keep the air-fuel ratio of the main combustion area stable.
(5) After being sprayed into the flame tube, the air and fuel mixed gas of the secondary burner is mixed with the high-temperature combustion products after being combusted in the main combustion area for combustion, and after being mixed, the air and fuel mixed gas reacts at the rear part of the flame tube, so that an obvious flame front is not generated, and a flameless combustion area is formed. Since the temperature distribution is uniform in the flameless combustion region, NO additional NO X is generated, and thermoacoustic oscillations can be suppressed.
(6) The secondary combustor can meet the requirements of stable operation and low emission in a wide working condition range, wherein the wide working condition refers to the range from low load to rated load of the gas turbine.
Drawings
FIG. 1 is a schematic cross-sectional view of the present invention;
FIG. 2 is a schematic view of the secondary burner of the present invention when installed perpendicular to the casing;
fig. 3 is a schematic structural view of the secondary burner in embodiment 1;
FIG. 4 is a view in the direction A-A of FIG. 3;
FIG. 5 is a view in the direction B-B of FIG. 3;
fig. 6 is a schematic sectional structure of the secondary burner in embodiment 1;
fig. 7 is a schematic structural view of a secondary burner in embodiment 2;
fig. 8 is a schematic structural view of a secondary burner in embodiment 3;
fig. 9 is a schematic sectional structure of a secondary burner in embodiment 3;
the fuel injection system comprises a combustion chamber 1, a secondary combustor 3, a primary stage combustor 4, a duty combustor 5, a flame tube 6, a casing 7, a short tube 8, a swirler vane 9, a primary stage fuel introduction hole 10, a duty fuel introduction hole 11, a central spray rod 12, a secondary premixed fuel introduction hole 13, a rectifying hole 14, a secondary axial swirl vane 15, a shell 16, a secondary diffusion fuel introduction hole 17, an axial duty vane 18, a secondary fuel diversion hole 100, air 101, a primary stage fuel control valve 102, a duty fuel control valve 103, a secondary fuel control valve 104, a secondary fuel mixture 105, secondary fuel 106 and an annular groove.
Detailed Description
In order to make the objects and technical solutions of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below with reference to examples.
Example 1
The combustion chamber with the axial air inlet secondary burner is shown in fig. 1-6, and comprises a secondary burner 2, a primary burner 3, a duty burner 4, a flame tube 5 and a casing 6, wherein the casing 6 is arranged on the periphery of the flame tube 5, the casing 6 and the flame tube 5 are coaxially arranged, an air 100 channel is formed between the outer surface of the flame tube 5 and the inner surface of the casing 6, specifically, air 100 flowing through the air 100 channel formed by the flame tube 5 and the casing 6 by a compressor flows, part of air 100 enters the flame tube 5 through the secondary burner 2, and the rest of air 100 enters the flame tube 5 from the primary burner 3 and the duty burner 4 through the air 100 channel to provide required air 100 for a primary combustion area, wherein the primary combustion area refers to an area of the flame tube 5, which is enveloped with premixed flame and duty flame.
The secondary burner 2 is arranged at the rear part of the combustion chamber 1, the upper end part of the secondary burner 2 is arranged on the casing 6, the lower end part of the secondary burner 2 extends to the inside of the flame tube 5, the lower end part of the secondary burner 2 is communicated with the inside of the flame tube 5, the number of the secondary burners 2 ranges from 3 to 8, the distance D between the secondary burner 2 and the tail end of the primary burner 3 is not smaller than the diameter D of the flame tube 5, the primary burner 3 is arranged at the front end part of the flame tube 5, the tail end of the primary burner 3 is communicated with the flame tube 5, the duty burner 4 is arranged at the front end part of the flame tube 5, the tail end of the duty burner 4 is communicated with the flame tube 5, and the primary burner 3 and the duty burner 4 are arranged at the same axial position at the top of the flame tube 5.
The secondary burner 2 is arranged at the rear end part of the flame tube 5, and the secondary burner 2 at least comprises a short tube 7, a central spray rod 11, a secondary axial swirl vane 14 and a shell 15, as shown in fig. 3, the central lines of the central spray rod 11, the shell 15 and the short tube 7 are positioned on the same straight line, the secondary axial swirl vane 14 is arranged at the periphery of the central spray rod 11, the secondary axial swirl vane 14 is positioned in the shell 15, the lower end of the short tube 7 extends into the flame tube 5, and the short tube 7 is communicated with the flame tube 5.
The central spray rod 11, the secondary axial swirl blades 14 and the shell 15 form a secondary combustor 2 channel, air 100 and secondary fuel 105 firstly pass through the fuel channel of the central spray rod 11 and then enter the flame tube 5 through the short tube 7, and as the components are all gyrorotor bodies, the assembly is most convenient in a mode of overlapping central lines, and the uniformity of the concentration distribution of the secondary fuel 105 can be ensured. An upper flat plate and a lower concave plate are sleeved at the upper end part of the central spray rod 11, and an annular groove 106 is formed by connecting the lower end surface of the upper flat plate and the upper end surface of the lower concave plate.
One end of the secondary combustor 2 is provided with a secondary fuel control valve 103, and the secondary fuel control valve 103 is used for controlling secondary fuel 105 to enter and exit the secondary combustor 2. Fig. 4 is a view in the direction A-A in fig. 3, a plurality of rectifying holes 13 are uniformly arranged on the housing 15 of the secondary combustor 2, and when the air 100 passes through the secondary combustor 2, part of the air 100 enters the annular groove 106 formed by the casing 6 and the housing 15 from the rectifying holes 13 on the housing 15, and then the air 100 is mixed with the secondary fuel 105 sprayed from the secondary premixed fuel introducing hole 12. The sum of the cross-sectional areas of the plurality of rectifying holes 13 is larger than the cross-sectional area of the outlet of the short pipe 7, and the rectifying holes 13 can ensure that the air 100 entering the secondary combustor 2 is relatively uniform. The inner surface of the housing 15 and the inner surface of the casing 6 form an annular chamber through which the air 100 is mixed with the secondary fuel 105 injected from the secondary premixed fuel introduction hole 12. The installation included angle between the lower end part of the secondary combustor 2 and the flame tube 5 is 60-90 degrees. The installation angle is mainly used for being convenient to install, the installation flange with the angle smaller than 60 degrees does not have a position, the angle is larger than 90, and the air flow secondary burner enters the air flow forward and collides with the main air flow.
Fig. 5 is a view in the direction B-B in fig. 3, a plurality of secondary premixed fuel introduction holes 12 are formed in the lower end surface of the concave plate, at least one secondary diffusion fuel introduction hole 16 is formed in the lower end portion of the central spray rod 11, so that the injected secondary fuel 105 is uniformly mixed with the air 100 as much as possible, and the total area of the secondary premixed fuel introduction holes 12 is not smaller than the total area of the secondary diffusion fuel introduction holes 16. Specifically, the premixed fuel forms a fuel/air mixture with air 100 through the secondary premixed fuel introduction hole 12, the premixed fuel accounts for not less than 40% of the fuel, the diffusion fuel enters the inside of the short tube 7 through the secondary diffusion fuel introduction hole 16, and the secondary fuel 105 forms a secondary fuel mixture 104 in the flame tube through the short tube 7.
The main stage burner 3 adopts a radial air inlet mode, and one end of the main stage burner 3 is provided with a main stage fuel control valve 101. The main stage combustor 3 at least comprises one cyclone blade 8, the at least one cyclone blade 8 forms a radial cyclone, and a plurality of main stage fuel introduction holes 9 for injecting fuel into the radial cyclone are formed in the cyclone blade 8. Specifically, the number of the cyclone blades 8 can be selected to be 12-20. Air 100 is mixed with fuel injected through the swirler vanes 8 and the primary fuel introduction holes 9 into the liner 5 to form a premixed combustion flame. The fuel only enters the combustion chamber 1 in three ways, namely the duty burner 4, the main-stage burner 3 and the secondary burner 2 respectively, when the gas turbine reaches low load, for example, when the gas turbine does not reach 20% load, the secondary burner 2 is generally not filled with secondary fuel 105, the duty fuel control valve 102 is gradually closed, the main-stage fuel control valve 101 is gradually opened, most of the fuel is injected into the radial cyclone from the main-stage fuel introduction hole 9 to be mixed with main-stage air 100, and the duty burner 4 only keeps a small amount of fuel to maintain flame stability.
The on-duty burner 4 is located at the most central position of the head of the combustion chamber 1 and is a diffusion burner with axial air inlet, and one end of the on-duty burner 4 is provided with an on-duty fuel control valve 102 for controlling fuel to enter the on-duty burner 4. A small amount of air 100 enters the flame tube 5 through the axial duty vanes 17 and the duty fuel is injected into the flame tube 5 through the plurality of duty fuel introduction holes 10 at the top end of the duty burner 4. The air 100 is mixed with the pilot fuel and burned while entering the flame tube 5 to form a stable diffusion flame. During the working conditions of the gas turbine under the conditions of the rising speed and the load below 20%, all fuel in the combustion chamber 1 enters a fuel channel of the on-duty combustor 4 through the on-duty fuel control valve 102, and then the on-duty fuel introduction hole 10 is injected into the flame tube 5.
The specific working principle of the combustion chamber 1 is that the combustion chamber 1 has less fuel injection quantity and larger air 100/fuel ratio in the main combustion area in the starting working condition and the rotating speed increasing stage of the gas turbine. At this time, the control valve 103 for the secondary fuel 105 is closed, no secondary fuel 105 is injected into the secondary burner 2, and part of the air 100 in the combustion chamber 1 enters the flame tube 5 from the secondary burner 2, so that the flow rate of the air 100 entering the flame tube 5 from the primary burner 3 is reduced, the air 100/fuel ratio in the primary combustion area is reduced, and the flame is stabilized.
The gas turbine enters a load-up stage, and as the load of the gas turbine increases, the combustion mode of the combustor 1 is switched from a diffusion combustion mode of the duty combustor 4 to a premixed combustion mode mainly comprising the main stage combustor 3, and the duty combustor 4 only has a small amount of fuel to maintain stable combustion. During the low load phase, a portion of air 100 enters the combustor basket 5 from the secondary combustor 2, reducing the amount of air 100 entering the main combustion zone, being able to switch to a premixed combustion mode at a lower load (about 20% load), maintaining combustion stability, and widening the steady operation load range of the gas turbine. The specific principle of realizing the switching is that the valve opening of the main-stage fuel control valve 101 is opened and gradually increased, so that fuel enters the main-stage burner 3 at the head part of the combustion chamber 1, the proportion of the main fuel is gradually increased to a design value, and meanwhile, the valve opening of the duty fuel control valve 102 is gradually reduced, and the proportion of the duty fuel is reduced to the design value. As the gas turbine load increases, the primary combustion zone air 100 of the combustor 1 is maintained at a reasonable air-fuel ratio range and excess fuel is injected from the secondary combustor 2 into the liner 5. The air 100 and fuel mixture in the secondary burner 2 enter the flame tube 5 to burn with the main combustion area to complete the high-temperature smoke mixed combustion, and a uniform flameless combustion area is formed in the secondary combustion area at the rear part of the flame tube 5. The secondary combustion area does not form obvious flame fronts, the air-fuel ratio of the secondary combustor 2 can be adjusted in a larger range, and the adjustment flexibility of the whole combustion chamber 1 can be increased.
Example 2
Fig. 7 shows example 2, the difference between example 2 and example 1 is that the fuel injection mode of the secondary burner 2 is changed, the annular groove 106 of the secondary burner 2 is eliminated, and a secondary premixed fuel introduction hole 12 is opened on the center boom 11, the secondary premixed fuel introduction hole 12 is positioned at the upper end of the secondary axial swirl vane 14. Because the air 100 fuel of the secondary burner 2 is sprayed into the flame tube 5 to be quickly mixed with the high-temperature flue gas of the primary combustion area, and a uniform secondary combustion area is formed, whether the fuel is completely mixed or not can not affect pollutant emission.
Example 3
Fig. 8 and 9 are examples 3, and example 3 differs from examples 1 and 2 in the secondary axial swirl vanes 14 and the variation of the fuel introduction manner. The secondary axial swirl vane 14 has a certain thickness, the inside of the secondary axial swirl vane 14 is of a cavity structure, the secondary axial swirl vane 14 is provided with a secondary fuel guide hole 18, when the secondary fuel control valve 103 is opened, fuel enters the internal cavity of the secondary axial swirl vane 14 through a fuel channel in the central spray rod 11, the fuel entering the secondary axial swirl vane 14 is discharged through the secondary fuel guide hole 18 arranged on the secondary axial swirl vane 14, and the fuel sprayed out through the secondary fuel guide hole 18 enters the short pipe 7 and then flows through the flame tube 5 communicated with the short pipe 7 to burn. Specifically, the secondary axial swirl vane 14 is located in the housing 15 of the secondary burner 2, and the fuel passage of the central boom 11 of the secondary burner 2 is in communication with the secondary fuel deflector hole 18 of the secondary axial swirl vane 14. The sides of the secondary axial swirl vanes 14 may each be provided with 4-6 secondary fuel deflector holes 18, and a portion of the fuel enters the secondary burner 2 from the secondary fuel deflector holes 18 to be mixed with the air 100 entering the secondary burner 2.
The foregoing is a description of embodiments of the invention, which are specific and detailed, but are not to be construed as limiting the scope of the invention. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention.

Claims (5)

1.一种带有轴向进气二次燃烧器的燃烧室，其特征在于，包括二次燃烧器、主级燃烧器、值班燃烧器、火焰筒；1. A combustion chamber with an axial air inlet secondary burner, characterized in that it includes a secondary burner, a main burner, a duty burner, and a flame tube; 所述二次燃烧器的下端部延伸至火焰筒内部，且所述二次燃烧器的下端部与火焰筒内部连通；The lower end of the secondary burner extends to the interior of the flame tube, and the lower end of the secondary burner is communicated with the interior of the flame tube; 所述主级燃烧器设置在所述火焰筒的前端部，且所述主级燃烧器的末端与火焰筒连通；The main stage burner is arranged at the front end of the flame tube, and the end of the main stage burner is connected to the flame tube; 所述值班燃烧器设置在所述火焰筒的前端部，且值班燃烧器的末端与火焰筒连通；The duty burner is arranged at the front end of the flame tube, and the end of the duty burner is connected to the flame tube; 所述主级燃烧器和所述值班燃烧器设于火焰筒顶部的同一轴向位置；The main burner and the duty burner are arranged at the same axial position on the top of the flame tube; 二次燃烧器至少包括短管、中心喷杆、二次轴向旋流叶片和壳体，中心喷杆、壳体和短管的中心线位于同一直线上；The secondary burner comprises at least a short tube, a central spray bar, secondary axial swirl blades and a shell, wherein the center lines of the central spray bar, the shell and the short tube are located on the same straight line; 燃烧室还包括机匣，机匣设置在所述火焰筒的外围，且机匣与火焰筒同轴心设置，且所述火焰筒外表面和机匣内表面之间形成有空气通道；The combustion chamber further comprises a casing, which is arranged at the periphery of the flame tube, and the casing and the flame tube are arranged coaxially, and an air passage is formed between the outer surface of the flame tube and the inner surface of the casing; 所述二次燃烧器固定于机匣上，且二次燃烧器的壳体上设有整流孔，所述整流孔包括若干个通孔，所述通孔的横截面积大于短管出口处的横截面积，且壳体的内表面与机匣的内表面形成环腔；空气通过环腔与二次预混燃料引入孔喷出的二次燃料混合；The secondary burner is fixed on the casing, and a rectifying hole is provided on the shell of the secondary burner, the rectifying hole includes a plurality of through holes, the cross-sectional area of the through holes is larger than the cross-sectional area at the outlet of the short tube, and the inner surface of the shell and the inner surface of the casing form an annular cavity; the air is mixed with the secondary fuel sprayed from the secondary premixed fuel introduction hole through the annular cavity; 所述中心喷杆上端部套设有上平板和下凹板，所述上平板的下端面和下凹板的上端面连接形成有一环形凹槽，且所述下凹板的下端面上开设有多个二次预混燃料引入孔；The upper end of the central spray rod is sleeved with an upper flat plate and a lower concave plate, the lower end surface of the upper flat plate and the upper end surface of the lower concave plate are connected to form an annular groove, and the lower end surface of the lower concave plate is provided with a plurality of secondary premixed fuel introduction holes; 所述中心喷杆的下端部开设有至少一个二次扩散燃料引入孔，且所述二次预混燃料引入孔总面积≥二次扩散燃料引入孔的总面积。At least one secondary diffusion fuel introduction hole is formed at the lower end of the central spray bar, and the total area of the secondary premixed fuel introduction holes is greater than or equal to the total area of the secondary diffusion fuel introduction holes. 2.根据权利要求1所述的一种带有轴向进气二次燃烧器的燃烧室，其特征在于，所述二次轴向旋流叶片安装在中心喷杆的外围，且二次轴向旋流叶片位于壳体内部；短管的下端延伸入火焰筒内部，且短管与火焰筒内部连通。2. A combustion chamber with an axial air intake secondary burner according to claim 1, characterized in that the secondary axial swirl blades are installed on the periphery of the central spray rod, and the secondary axial swirl blades are located inside the shell; the lower end of the short tube extends into the interior of the flame tube, and the short tube is connected to the interior of the flame tube. 3.根据权利要求1所述的一种带有轴向进气二次燃烧器的燃烧室，其特征在于，所述二次燃烧器中心轴线与火焰筒的水平轴线的夹角为60°-90°。3. A combustion chamber with an axial air intake secondary burner according to claim 1, characterized in that the angle between the central axis of the secondary burner and the horizontal axis of the flame tube is 60°-90°. 4.根据权利要求1所述的一种带有轴向进气二次燃烧器的燃烧室，其特征在于，所述二次燃烧器的数量范围为3-8个，且所述二次燃烧器与主级燃烧器末端的距离D≥火焰筒的直径d。4. A combustion chamber with an axial air intake secondary burner according to claim 1, characterized in that the number of the secondary burners ranges from 3 to 8, and the distance D between the secondary burner and the end of the main burner is ≥ the diameter d of the flame tube. 5.根据权利要求1所述的一种带有轴向进气二次燃烧器的燃烧室，其特征在于，所述主级燃烧器至少包括一个旋流器叶片，且所述至少一个旋流器叶片构成一径向旋流器，所述旋流器叶片上还开设有将燃料喷入径向旋流器内的主级燃料引入孔。5. A combustion chamber with an axial air intake secondary burner according to claim 1, characterized in that the main-stage burner includes at least one swirler blade, and the at least one swirler blade constitutes a radial swirler, and the swirler blade is also provided with a main-stage fuel introduction hole for spraying fuel into the radial swirler.
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