Gas turbine multi-cyclone combustion chamber with adjustable circumferential rotational flow

Abstract

The gas turbine multi-cyclone combustion chamber comprises a shell, a two-stage cyclone and a plurality of single-stage cyclones, the two-stage cyclone and the single-stage cyclones are arranged in the shell, the two-stage cyclone is located at the center position of the shell, the single-stage cyclones are located on the periphery of the two-stage cyclone, and the single-stage cyclones are located on the periphery of the shell. A hydraulically-controlled connecting rod mechanism used for driving the single-stage swirler to deflect is arranged in the shell, and the combustion chamber can obtain the optimal flame distribution state.

Description

Technical Field

[0001] The invention belongs to the technical field of ground gas turbines and relates to a gas turbine multi-swirler combustion chamber with adjustable circumferential swirl. Background Art

[0002] Ground-based gas turbines are primarily used for power generation in power plants. Their high power output, complete combustion, and high energy conversion efficiency make them a reliable option for improving China's power supply. Currently, China's power supply is still primarily based on thermal power, supplemented by hydropower, wind power, solar power, nuclear power, and tidal power. In the short term, gas turbine power generation is primarily used for peak load regulation, which involves frequent changes in operating conditions depending on the power required.

[0003] Under varying load conditions, the air-fuel ratio within a gas turbine combustor varies. The flame distribution and center position change with the air-fuel ratio, impacting combustion efficiency and turbine pollutant emissions. Improving the structural design and combustion organization of the gas turbine combustor head, enabling the gas turbine to quickly achieve optimal flame distribution within the combustor under significant operating conditions, is of great engineering significance for the future application of gas turbines in ground-based power generation. Summary of the Invention

[0004] The object of the present invention is to overcome the above-mentioned shortcomings of the prior art and to provide a multi-swirler combustor for a gas turbine with adjustable circumferential swirl, which can achieve an optimal flame distribution state.

[0005] To achieve the above-mentioned objectives, the present invention discloses a gas turbine multi-swirler combustor with adjustable circumferential swirl, comprising a housing, a two-stage swirler, and several single-stage swirlers disposed within the housing. The two-stage swirler is located at the center of the housing, and the single-stage swirlers are located around the two-stage swirler. A hydraulically controlled connecting rod mechanism is provided within the housing for driving the deflection of the single-stage swirlers.

[0006] Furthermore, the double-stage cyclone includes a fuel delivery pipe and a central hollow channel of the double-stage cyclone, a plurality of first-stage weak swirl blades of the double-stage cyclone, and a plurality of second-stage strong swirl blades of the double-stage cyclone, which are arranged in sequence from the inside to the outside. A first-stage weak swirl blade channel of the double-stage cyclone is formed between adjacent first-stage weak swirl blades of the double-stage cyclone, and a second-stage strong swirl blade channel of the double-stage cyclone is formed between adjacent second-stage strong swirl blades of the double-stage cyclone. The fuel delivery pipe is connected to the central hollow channel of the double-stage cyclone.

[0007] Furthermore, the angle of the weak swirl blades of the first stage of the double-stage cyclone is 25°.

[0008] Furthermore, the angle of the second-stage strong swirl blade of the double-stage cyclone is 45°.

[0009] Furthermore, the single-stage cyclone includes a central hollow straight channel of the single-stage cyclone, a central hollow straight channel of the single-stage cyclone, and a venturi tube, wherein the central hollow straight channel of the single-stage cyclone is located around the central hollow straight channel of the single-stage cyclone, the central hollow straight channel of the single-stage cyclone is connected to the venturi tube via the central hollow straight channel of the single-stage cyclone, a plurality of gaseous fuel injection holes are provided on the central hollow straight channel of the single-stage cyclone, and a fuel delivery pipe is connected to the central hollow straight channel of the single-stage cyclone.

[0010] Furthermore, the angle of the flow limiting blade of the single-stage cyclone is 45°.

[0011] Furthermore, the hydraulically controlled connecting rod mechanism controls the single-stage cyclone to achieve an angular deflection of ±10° as a whole.

[0012] Furthermore, a central adjustable sealing ring is provided at the inlet of the single-stage cyclone and the outlet of the venturi tube.

[0013] Furthermore, the central adjustable sealing ring is composed of a plurality of annular steel sheets.

[0014] The present invention discloses a multi-swirler combustor for a gas turbine with adjustable circumferential swirl, comprising a housing, a two-stage swirler and a plurality of single-stage swirlers disposed within the housing. The two-stage swirler is located at the center of the housing, and the single-stage swirlers are located around the two-stage swirler. A hydraulically controlled connecting rod mechanism is provided within the housing for driving the deflection of the single-stage swirlers.

[0015] The double-stage cyclone includes a fuel delivery pipe and a central hollow channel of the double-stage cyclone, a plurality of first-stage weak swirl blades of the double-stage cyclone, and a plurality of second-stage strong swirl blades of the double-stage cyclone, which are arranged in sequence from the inside to the outside. The first-stage weak swirl blade channel of the double-stage cyclone is formed between adjacent first-stage weak swirl blades of the double-stage cyclone, and the second-stage strong swirl blade channel of the double-stage cyclone is formed between adjacent second-stage strong swirl blades of the double-stage cyclone. The fuel delivery pipe is connected to the central hollow channel of the double-stage cyclone.

[0016] The single-stage cyclone includes a central hollow straight channel of the single-stage cyclone, a central hollow straight channel of the single-stage cyclone, and a venturi. The central hollow straight channel of the single-stage cyclone is located around the central hollow straight channel of the single-stage cyclone. The central hollow straight channel of the single-stage cyclone is connected to the venturi via the central hollow straight channel of the single-stage cyclone. A plurality of gaseous fuel injection holes are provided on the central hollow straight channel of the single-stage cyclone. A fuel delivery pipe is connected to the central hollow straight channel of the single-stage cyclone.

[0017] The present invention has the following beneficial effects:

[0018] During specific operation, the multi-swirler combustor of a gas turbine with adjustable circumferential swirl described in the present invention utilizes a hydraulically controlled connecting rod mechanism to achieve angular deflection of the single-stage swirler toward the central double-stage swirler, thereby achieving an optimal flame distribution state under different gas turbine loads and combustor air-fuel ratios, thereby facilitating high economic efficiency and low pollution emissions in gas turbine power generation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings, which constitute part of the present invention, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0020] Figure 1 It is a structural diagram of the present invention;

[0021] Figure 2 is a radial cross-sectional view of the present invention;

[0022] Figure 3 It is a partially enlarged cross-sectional view of the present invention.

[0023] Among them, 1 is a two-stage swirler, 2 is a single-stage swirler, 3 is a central adjustable sealing ring, 4 is the central hollow channel of the two-stage swirler, 5 is the first-stage weak swirl blade channel of the two-stage swirler, 6 is the second-stage strong swirl blade channel of the two-stage swirler, 7 is the swirl blade channel of the single-stage swirler, 8 is the central hollow straight channel of the single-stage swirler, 9 is a venturi tube, 10 is a gaseous fuel injection hole, and 11 is a hydraulically controlled connecting rod mechanism. DETAILED DESCRIPTION

[0024] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0025] In the description of the present invention, it is to be understood that the terms “include” and “comprise” indicate the presence of the described features, wholes, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components and / or collections thereof.

[0026] It should also be understood that the terms used in the present specification are only for the purpose of describing particular embodiments and are not intended to limit the present invention. As used in the present specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms unless the context clearly indicates otherwise.

[0027] It should be further understood that the term "and / or" as used in the present specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items. For example, A and / or B may represent: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " in the present invention generally indicates that the associated objects are in an "or" relationship.

[0028] It should be understood that although the terms "first," "second," and "third" may be used to describe preset ranges in embodiments of the present invention, these preset ranges should not be limited to these terms. These terms are merely used to distinguish one preset range from another. For example, without departing from the scope of embodiments of the present invention, the first preset range may also be referred to as the second preset range, and similarly, the second preset range may also be referred to as the first preset range.

[0029] The word "if," as used herein, may be interpreted as "at the time of" or "when" or "in response to determining" or "in response to detecting," depending on the context. Similarly, the phrases "if it is determined" or "if (stated condition or event) is detected" may be interpreted as "when it is determined" or "in response to the determination" or "when detecting (stated condition or event)" or "in response to detecting (stated condition or event)," depending on the context.

[0030] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0031] The accompanying drawings illustrate various schematic diagrams of structures according to embodiments disclosed herein. These figures are not drawn to scale; for clarity, some details are exaggerated and some details may be omitted. The shapes of the various regions and layers shown in the figures, as well as their relative sizes and positional relationships, are merely exemplary and may deviate in practice due to manufacturing tolerances or technical limitations. Those skilled in the art may design regions / layers with different shapes, sizes, and relative positions as needed.

[0032] As is known to all, the combustion chamber is a device where fuel or propellant burns to generate high-temperature combustion gases. It is a key component of gas turbine engines, ramjet engines, rocket engines, etc., and has a direct impact on the operation and performance of the engine. The following is a detailed introduction to the combustion chamber:

[0033] 1. Structural composition

[0034] The combustion chamber is usually composed of an outer shell (sleeve), a flame tube, a nozzle (oil) nozzle, a swirl device, an ignition device, etc. The flame is transmitted and the pressure is balanced between the combustion chambers through a cross-flame tube.

[0035] Outer casing (sleeve): constitutes the air flow channel and is the main load-bearing part of the engine.

[0036] Flame tube: It is composed of vortex generator, flame tube body, gas duct, etc., and is the main place of combustion.

[0037] Nozzle: Atomizes the fuel, accelerates the formation of the mixture, ensures stable combustion and improves combustion efficiency.

[0038] Swirlizer: It makes the high-temperature gas form a low-speed recirculation zone at the head of the flame tube to ensure ignition, stable combustion and complete combustion.

[0039] Ignition device: Provides an initial ignition torch to the combustion chamber when the engine is started.

[0040] 2. Working Process

[0041] The combustion chamber's operating process includes airflow expansion and deceleration, fuel atomization, ignition, formation of a combustion recirculation zone, combustion, and mixture cooling. Air from the compressor enters the combustion chamber at high speed. Because high speeds are unsuitable for combustion, the air velocity must be reduced to allow for air expansion. Turbulent flames in a chemically appropriate kerosene-air mixture propagate slowly, so a low axial velocity zone must be created in the combustion chamber to ensure stable flame combustion throughout the engine's operating range.

[0042] 3. Classification

[0043] According to the different structural forms, the combustion chamber can be divided into a single-tube combustion chamber, a coupled-tube combustion chamber (annular tube combustion chamber) and annular combustion chamber.

[0044] Single-tube combustion chamber: A tubular flame tube is surrounded by a separate shell, forming a branch tube. Six to 16 such branch tubes are located around the gas turbine, interconnected by flame transfer tubes to propagate the flame and equalize pressure. Advantages include ease of assembly, disassembly, maintenance, and repair, as well as debugging, and experimental results that closely resemble actual conditions. Disadvantages include poor space utilization and significant flow losses.

[0045] A linked-tube combustor (annular-tube combustor): Several tubular flame tubes are evenly spaced around the circumference of a common annular housing, with cross-fire tubes installed between each tube. Its structure is somewhere between a tubular and annular combustor, combining the advantages of both. It's suitable for use with axial-flow compressors, fully utilizing the kinetic energy of the compressor's airflow. However, it's heavy, has a complex flame tube structure, and requires high manufacturing processes.

[0046] Annular combustion chamber: The flame tube is a single, annular cavity, concentrically mounted within an annular housing. This type of combustion chamber offers high space efficiency, minimizes frontal area, weight, pressure loss, flame tube surface area, and length, requires minimal cooling air, and features a uniform circumferential outlet flow field. It is widely used in various new engines. However, the combustion chambers communicate with each other, making it difficult to coordinate airflow and the fuel torch, and controlling combustion performance is challenging.

[0047] 4. Performance indicators

[0048] Combustion chamber performance indicators include combustion chamber efficiency, pressure loss, stability, ignition range, outlet temperature distribution, and heat capacity. Among these, the parameters most closely related to gas turbine variable operating conditions are combustion chamber efficiency and pressure loss. The former is directly related to the gas turbine's fuel consumption (affecting its efficiency) and also affects the gas flow rate through the turbine; the latter directly influences the turbine's expansion ratio.

[0049] 5. Design requirements

[0050] The design of the combustion chamber should meet the following main requirements:

[0051] Starting and ignition are quick and reliable under various weather conditions and flight conditions on the ground and in the air.

[0052] Within the flight envelope, under all normal engine operating conditions, the combustion chamber should ensure stable combustion of the mixture, with a high complete combustion coefficient and a low pressure loss coefficient.

[0053] Ensure that the mixture is completely burned within the shortest possible distance. The flame of the gas should be short, especially no residual flame should flow out of the combustion chamber. The generation of exhaust pollutants should also be reduced.

[0054] The outlet gas temperature field should be uniform along the circumference and distributed according to the turbine requirements along the blade height.

[0055] The components of the combustion chamber and their connections should have sufficient strength and rigidity, good cooling and reliable thermal compensation to reduce thermal stress.

[0056] The combustion chamber should have small outer dimensions, short axial dimensions, light weight, high heat capacity, simple structure, good performance, easy maintenance and inspection, and long service life.

[0057] Example 1

[0058] refer to Figure 1 、 Figure 2 and Figure 3 The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to the present invention comprises a housing, a two-stage swirler 1 and a plurality of single-stage swirlers 2 disposed within the housing. The two-stage swirler 1 is located at the center of the housing, and the single-stage swirlers 2 are located around the two-stage swirler 1. A hydraulically controlled connecting rod mechanism 11 is provided within the housing for driving the deflection of the single-stage swirlers 2.

[0059] The double-stage cyclone 1 includes a fuel delivery pipe and a double-stage cyclone central hollow channel, a plurality of double-stage cyclone first-stage weak swirl blades, and a plurality of double-stage cyclone second-stage strong swirl blades arranged in sequence from the inside to the outside. A double-stage cyclone first-stage weak swirl blade channel 5 is formed between adjacent double-stage cyclone first-stage weak swirl blades, and a double-stage cyclone second-stage strong swirl blade channel 6 is formed between adjacent double-stage cyclone second-stage strong swirl blades. The fuel delivery pipe is connected to the double-stage cyclone central hollow channel.

[0060] The single-stage cyclone 2 includes a single-stage cyclone central hollow straight channel 8, a single-stage cyclone central hollow straight channel 8, and a venturi 9. The single-stage cyclone central hollow straight channel 8 is located around the single-stage cyclone central hollow straight channel 8 and is connected to the venturi 9 via the single-stage cyclone central hollow straight channel 8. A plurality of gaseous fuel injection holes 10 are provided on the single-stage cyclone central hollow straight channel 8, and a fuel delivery pipe is connected to the single-stage cyclone central hollow straight channel 8.

[0061] Example 2

[0062] refer to Figure 1 、 Figure 2 and Figure 3 To further improve this application, the multi-swirler combustion chamber of a gas turbine with adjustable circumferential swirl according to the present invention includes a shell and a two-stage swirler 1 and several single-stage swirlers 2 arranged in the shell. The two-stage swirler 1 is located at the center of the shell, and the single-stage swirler 2 is located around the two-stage swirler 1.

[0063] The double-stage cyclone 1 includes a fuel delivery pipe and a double-stage cyclone central hollow channel, a plurality of double-stage cyclone first-stage weak swirl blades, and a plurality of double-stage cyclone second-stage strong swirl blades arranged in sequence from the inside to the outside. A double-stage cyclone first-stage weak swirl blade channel 5 is formed between adjacent double-stage cyclone first-stage weak swirl blades, and a double-stage cyclone second-stage strong swirl blade channel 6 is formed between adjacent double-stage cyclone second-stage strong swirl blades. The fuel delivery pipe is connected to the double-stage cyclone central hollow channel.

[0064] Preferably, the angle of the first-stage weak swirl blade of the double-stage cyclone is 25°; the angle of the second-stage strong swirl blade of the double-stage cyclone is 45°;

[0065] During operation, gaseous fuel flows into the central hollow channel 4 of the double-stage cyclone through the fuel delivery pipe, first mixed with the first-stage weak swirl output by the first-stage weak swirl blade channel 5 of the double-stage cyclone, and then mixed with the second-stage strong swirl output by the second-stage strong swirl blade channel 6 of the double-stage cyclone. This mixing method can control the position of the flame root in the combustion chamber to be located at a certain distance from the cyclone outlet, effectively avoiding the risk of backfire.

[0066] The single-stage cyclone 2 includes a single-stage cyclone central hollow straight channel 8, a single-stage cyclone central hollow straight channel 8, and a venturi 9. The single-stage cyclone central hollow straight channel 8 is located around the single-stage cyclone central hollow straight channel 8 and is connected to the venturi 9 via the single-stage cyclone central hollow straight channel 8. A plurality of gaseous fuel injection holes 10 are provided on the single-stage cyclone central hollow straight channel 8, and a fuel delivery pipe is connected to the single-stage cyclone central hollow straight channel 8.

[0067] Preferably, the angle of the flow limiting blade of the single-stage cyclone is 45°.

[0068] The hydraulically controlled connecting rod mechanism 11 controls the single-stage cyclone 2 to achieve an angular deflection of ±10° as a whole.

[0069] During operation, gaseous fuel enters the single-stage swirler through the central hollow straight channel 8 via the fuel delivery pipe, enters the single-stage swirler swirl blade channel 7 through the gaseous fuel injection holes 10 distributed thereon, and is mixed with the swirl. Subsequently, the gaseous fuel passes through the venturi 9 to obtain fully mixed premixed combustible gas. The premixed combustible gas ensures excellent ignition and starting performance of the multi-swirler combustion chamber.

[0070] When the gas turbine load and combustor air-fuel ratio change, the hydraulically controlled connecting rod mechanism 11 activates to achieve optimal flame distribution, causing the single-stage swirler 2 to rotate radially toward or away from the dual-stage swirler 1 in the combustor. This influences the fuel and gas distribution within the flame tube, thereby adjusting the combustion structure in the combustor and maintaining high gas turbine efficiency and low pollutant emissions. The angle of the single-stage swirler 2 can be adjusted, either as a whole or individually, depending on the actual operating conditions.

[0071] The hydraulically controlled connecting rod mechanism 11 enables the single-stage swirler 2 to deviate toward or away from the double-stage swirler 1 within an angular range of 10°. The deflection angle of the eight single-stage swirlers 2 can be adjusted as a whole or individually. The angular deflection of the single-stage swirler 2 can effectively adjust the gas and flame distribution in the combustion chamber, and can obtain the optimal flame distribution state under different gas turbine loads and combustion chamber air-fuel ratios.

[0072] A central adjustable sealing ring 3 consisting of 20 annular steel sheets is distributed at the inlet of the single-stage cyclone 2 and the outlet of the venturi tube 9.

[0073] Those skilled in the art will readily identify other embodiments of the present invention after considering the specification and disclosure of the invention. This application is intended to cover any variations, uses, or adaptations of the present invention that follow the general principles of the invention and include common knowledge or customary techniques in the art not disclosed herein. The description and examples are to be considered as exemplary only, with the true scope and spirit of the invention being indicated by the following claims.

[0074] It should be understood that the present invention is not limited to the exact construction described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present invention is limited only by the appended claims.

[0075] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any way. Any simple modification, change and equivalent structural change made to the above embodiment based on the technical essence of the present invention shall still fall within the scope of protection of the technical solution of the present invention.

Claims

1. A multi-swirler combustor for a gas turbine with adjustable circumferential swirl, characterized in that: The invention comprises a shell, a double-stage cyclone (1) and a plurality of single-stage cyclones (2) arranged in the shell, wherein the double-stage cyclone (1) is located at the center of the shell, and the single-stage cyclones (2) are located around the double-stage cyclone (1). A hydraulically controlled connecting rod mechanism (11) for driving the single-stage cyclones (2) to deflect is provided in the shell.

2. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 1, characterized in that: The double-stage cyclone (1) comprises a fuel delivery pipe and a double-stage cyclone central hollow channel, a plurality of double-stage cyclone first-stage weak swirl blades, and a plurality of double-stage cyclone second-stage strong swirl blades arranged in sequence from the inside to the outside, wherein a double-stage cyclone first-stage weak swirl blade channel (5) is formed between adjacent double-stage cyclone first-stage weak swirl blades, and a double-stage cyclone second-stage strong swirl blade channel (6) is formed between adjacent double-stage cyclone second-stage strong swirl blades, and the fuel delivery pipe is connected to the double-stage cyclone central hollow channel.

3. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 2, characterized in that: The angle of the weak swirl blades in the first stage of the double-stage cyclone is 25°.

4. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 2, characterized in that: The angle of the second-stage strong swirl blade of the double-stage cyclone is 45°.

5. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 2, characterized in that: The single-stage cyclone (2) comprises a central hollow straight channel (8) of the single-stage cyclone, a central hollow straight channel (8) of the single-stage cyclone and a venturi (9), wherein the central hollow straight channel (8) of the single-stage cyclone is located around the central hollow straight channel (8) of the single-stage cyclone, the central hollow straight channel (8) of the single-stage cyclone is connected to the venturi (9) via the central hollow straight channel (8) of the single-stage cyclone, a plurality of gaseous fuel injection holes (10) are provided on the central hollow straight channel (8) of the single-stage cyclone, and a fuel delivery pipe is connected to the central hollow straight channel (8) of the single-stage cyclone.

6. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 5, characterized in that: The angle of the flow limiting blade of the single-stage cyclone is 45°.

7. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 5, characterized in that: The hydraulically controlled connecting rod mechanism (11) controls the single-stage cyclone (2) to achieve an overall angular deflection of ±10°.

8. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 5, characterized in that: A central adjustable sealing ring (3) is provided at the inlet of the single-stage cyclone (2) and the outlet of the venturi tube (9).

9. The multi-swirler combustor of a gas turbine with adjustable circumferential swirl according to claim 5, characterized in that: The central adjustable sealing ring (3) is composed of a plurality of annular steel sheets.

10. A multi-swirler combustor for a gas turbine with adjustable circumferential swirl, characterized in that: The invention comprises a housing, a double-stage cyclone (1) and a plurality of single-stage cyclones (2) arranged in the housing, wherein the double-stage cyclone (1) is located at the center of the housing, and the single-stage cyclones (2) are located around the double-stage cyclone (1). A hydraulically controlled connecting rod mechanism (11) for driving the single-stage cyclones (2) to deflect is provided in the housing; The double-stage cyclone (1) comprises a fuel delivery pipe and a double-stage cyclone central hollow channel, a plurality of double-stage cyclone first-stage weak swirl blades, and a plurality of double-stage cyclone second-stage strong swirl blades arranged in sequence from the inside to the outside, wherein a double-stage cyclone first-stage weak swirl blade channel (5) is formed between adjacent double-stage cyclone first-stage weak swirl blades, and a double-stage cyclone second-stage strong swirl blade channel (6) is formed between adjacent double-stage cyclone second-stage strong swirl blades, and the fuel delivery pipe is connected to the double-stage cyclone central hollow channel; The single-stage cyclone (2) comprises a central hollow straight channel (8) of the single-stage cyclone, a central hollow straight channel (8) of the single-stage cyclone and a venturi (9), wherein the central hollow straight channel (8) of the single-stage cyclone is located around the central hollow straight channel (8) of the single-stage cyclone, the central hollow straight channel (8) of the single-stage cyclone is connected to the venturi (9) via the central hollow straight channel (8) of the single-stage cyclone, a plurality of gaseous fuel injection holes (10) are provided on the central hollow straight channel (8) of the single-stage cyclone, and a fuel delivery pipe is connected to the central hollow straight channel (8) of the single-stage cyclone.

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