Combustor capable of axially adjusting rotational flow degree of oxidizing agent

Abstract

The combustor is of a coaxial sealing cavity structure and sequentially comprises a fuel cavity, an oxidizing agent cavity and a mixing cavity from bottom to top, and efficient mixing of fuel and an oxidizing agent is achieved through nozzle assemblies distributed in a square multi-layer array mode in the oxidizing agent cavity; each nozzle assembly is integrated with a rotatable oxidizing agent direct flow component, a plurality of axial rotational flow generation components with single rotational flow channels and a fuel conveying shaft sleeve, and continuous adjustment of the rotational flow degree of an oxidizing agent under different working conditions is achieved by switching the single rotational flow channels with different rotational flow angles. And in cooperation with a fuel and oxidant double-channel pre-rotation design and a variable cross-section mixed gas injection channel, the mixing uniformity is remarkably improved, the local high temperature is restrained, and NOx emission is reduced.

Description

Technical Field

[0001] The present invention relates to a burner, specifically a burner with axially adjustable oxidant swirl degree, belonging to the technical field of gas turbines. Background Art

[0002] As an efficient power device, the performance of a gas turbine depends on the combustion efficiency and stability of the combustion chamber. The combustion chamber undertakes the key tasks of fuel and oxidant mixing, ignition, and energy release, and its design directly affects the overall thermal efficiency, emission level, and operation reliability of the gas turbine. However, traditional combustion chambers often face problems such as uneven fuel mixing and poor flame stability, resulting in the generation of excessive pollutants such as nitrogen oxides (NO x ), carbon monoxide (CO), etc. Especially when dealing with multiple fuel switches or variable operating conditions, the performance fluctuations are particularly obvious. Currently, Patent CN119196719A discloses a burner that realizes tangential adjustment of the air swirl degree in the range of 0 - 65° through the combined adjustment of an air guide component and a tangential swirl component. However, tangential swirl has certain limitations in practical applications: on the one hand, its mixing uniformity is limited by the swirl angle adjustment range; on the other hand, in a burner with limited space, tangential swirl is prone to difficultly achieving the ideal swirl intensity due to the swirl channel length and flow dissipation, resulting in a decline in the mixing effect and combustion stability.

[0003] In contrast, axial swirl shows certain advantages. Within a certain scale range, axial swirl can achieve a wider range of swirl angle adjustment, thereby achieving more uniform mixing and more stable flame residence. Based on these advantages, developing a burner with a wider oxidant swirl range and axially adjustable is of great significance for improving the performance of the combustion chamber and achieving the best combustion effect under different combustion requirements. Summary of the Invention

[0004] Aiming at the problems existing in the above-mentioned prior art, the present invention provides a burner with axially adjustable oxidant swirl degree. Through an innovative structure, this design realizes flexible adjustment of a wider range of axial swirl degrees, enabling the combustion chamber to adapt to different fuel characteristics and different operating conditions, improving the combustion efficiency, reducing pollutant emissions, and enhancing the stability and adaptability of the system.

[0005] To achieve the above object, the burner with axially adjustable oxidizer swirl intensity is provided with a fuel chamber, an oxidizer chamber and a mixing chamber coaxially and sealed at intervals from bottom to top. The fuel chamber and the oxidizer chamber are separated by a lower baffle of the fuel chamber and an upper baffle of the oxidizer chamber, and the oxidizer chamber and the mixing chamber are separated by an upper baffle of the oxidizer chamber and a lower baffle of the mixing chamber. A plurality of nozzle assemblies are fixedly arranged in the oxidizer chamber, and the plurality of nozzle assemblies are symmetrically arranged with respect to the center of the oxidizer chamber in a square multi-layer array structure; the fuel chamber is provided with a lower baffle of the fuel chamber, a fuel input channel and an upper baffle of the fuel chamber; the oxidizer chamber is provided with a lower baffle of the oxidizer chamber, an oxidizer input channel and an upper baffle of the oxidizer chamber; the mixing chamber is provided with a lower baffle of the mixing chamber and a mixture gas injection channel; it is characterized in that, The combustion nozzle assembly includes a fuel delivery shaft sleeve, an oxidizer direct current component and an axial swirl generating component. The oxidizer direct current component and the axial swirl generating component are coaxially arranged outside the fuel delivery shaft sleeve, and from bottom to top are the oxidizer direct current component and the axial swirl generating component.

[0006] The oxidizer direct current component is a through-hole shaft sleeve structure with a through-hole inside, and an oxidizer direct current channel penetrating the oxidizer direct current component is opened thereon, and a plurality of small through-holes are opened on the outer periphery of the oxidizer direct current channel.

[0007] The axial swirl generating component is a through-hole shaft sleeve structure with a through-hole coaxially arranged inside, and the upper end of the axial swirl generating component is connected to the oxidizer chamber by a threaded seal. The lower end of the axial swirl generating component is provided with a multi-stage axial swirl channel penetrating the axial swirl generating component and having a spiral structure. The multi-stage axial swirl channel has a single swirl channel with different axial swirl angles, and a plurality of threaded holes are opened on its outer periphery. The lower end of the single swirl channel is communicated with the upper end of the oxidizer direct current channel of the oxidizer direct current component, and the upper end opening faces the mixture gas injection channel.

[0008] The fuel delivery shaft sleeve is a blind-hole shaft sleeve structure with a blind hole coaxially arranged inside, and the opening position is at the bottom end of the fuel delivery shaft sleeve. The bottom end of the fuel delivery shaft sleeve is connected to the upper baffle of the fuel chamber by a threaded seal. The blind hole of the fuel delivery shaft sleeve forms a fuel channel, and a radial fuel injection hole is opened on one side of the fuel delivery shaft sleeve close to the mixture gas injection channel.

[0009] As a further improvement of the present invention, a plurality of fuel input channels of the fuel chamber are arranged around the central axis of the burner, and the fuel input channels have a certain swirl intensity. A plurality of oxidizer input channels of the oxidizer chamber are arranged around the central axis of the burner, and the oxidizer input channels have a certain swirl intensity.

[0010] As a further improvement of the present invention, the mixture gas injection channel of the mixing chamber is composed of a converging pipe section with a variable cross-section structure and a straight pipe section with an equal cross-section.

[0011] As a further improvement of the present invention, a plurality of multi-stage axial swirl channels of the axial swirl generating component are arranged around the central axis of the axial swirl generating component, and the swirl intensity of the single swirl channel built in the multi-stage axial swirl channel increases or decreases successively in the clockwise direction.

[0012] As a further improvement of the present invention, the swirl angle range of the single swirl channel is 0 - 70°, and the number of the multi-stage axial swirl channels is affected by the swirl intensity of the single swirl channel.

[0013] As a further improvement of the present invention, the small through hole of the oxidant direct current component and the threaded hole of the axial swirl generating component are hermetically connected by fixing bolts to realize the sealing connection between the oxidant direct current component and the axial swirl generating component.

[0014] As a further improvement of the present invention, by rotating the oxidant direct current component, the small through hole is coaxially aligned with different threaded holes in the same group respectively, so as to realize the connection between the oxidant direct current channel and different single swirl channels in the multi-stage axial swirl channel, and further realize the adjustment of the swirl degree of the nozzle assembly.

[0015] As a further improvement of the present invention, a plurality of radial fuel injection holes of the fuel delivery bushing are arranged on the same horizontal line.

[0016] As a further improvement of the present invention, the top end of the fuel delivery bushing is flush with the top end of the straight pipe section of the mixed gas injection channel.

[0017] As a further improvement of the present invention, a perforated plate is arranged between the oxidant direct current component in the oxidant cavity and the upper partition plate of the fuel cavity.

[0018] Compared with the prior art, the burner with axially adjustable oxidant swirl degree of the present invention has the following beneficial effects: 1. In terms of improving fuel adaptability, for a single nozzle with adjustable oxidant swirl degree, according to the fuel characteristics of different fuels, through the combined adjustment of the oxidant direct current component and the axial swirl generating component, the swirl intensity requirements under different working conditions can be realized, so as to improve the fuel adaptability of the burner under different working conditions.

[0019] 2. In terms of enhancing the uniformity of the mixed gas flow, the present invention adopts a perforated plate, so that the oxidant enters the nozzle assembly in a more uniform manner, and then an axially rotating gas flow with a specific swirl degree is generated through the axial swirl generating component. This rotating gas flow is more fully mixed with the jet fuel in the mixed gas injection channel.

[0020] 3. In terms of reducing NO xIn terms of emissions, the variable cross-section structure design of the mixing gas injection channel's contraction pipe section helps increase the jet velocity of the mixing gas in the straight pipe section, further shortening the residence time of the high-temperature recirculation zone in the combustion chamber and reducing NO x emissions.

[0021] 4. In terms of improving combustion efficiency, both the fuel input channel and the oxidant input channel have a certain degree of swirl. This pre-selection design causes the fuel and the oxidant to form a pre-swirl before entering the combustion zone, further enhancing the mixing effect between the two, so that the combustion reaction can proceed more evenly, avoiding high temperatures and incomplete combustion caused by local over-oxidation or oxygen deficiency combustion, thereby improving combustion efficiency. Description of the Drawings

[0022] Figure 1 is the overall two-dimensional sectional structure schematic diagram of the present invention; Figure 2 is the overall three-dimensional structure schematic diagram of the present invention; Figure 3 is the overall top view of the present invention; Figure 4 is one of the three-dimensional structure schematic diagrams of the nozzle assembly of the present invention (the single swirl channel angles are 15°, 30°, and 45° in sequence); Figure 5 is the second three-dimensional structure schematic diagram of the nozzle assembly of the present invention (the single swirl channel angles are 60° and 70° in sequence); Figure 6 is the top view of the axial swirl generating component of the present invention (the single swirl channel angles are 15°, 30°, and 45° in sequence); Figure 7 is the top view of the axial swirl generating component of the present invention (the single swirl channel angles are 60° and 70° in sequence); Figure 8 is the top view of the oxidant direct current component of the present invention; In the figure: 1 - fuel chamber, 11 - lower partition of the fuel chamber, 12 - fuel input channel, 13 - upper partition of the fuel chamber, 2 - oxidant chamber, 21 - lower partition of the oxidant chamber, 22 - oxidant input channel, 23 - upper partition of the oxidant chamber, 3 - mixing chamber, 31 - lower partition of the mixing chamber, 32 - mixing gas injection channel, 321 - contraction pipe section, 322 - straight pipe section, 4 - nozzle assembly, 41 - fuel delivery shaft sleeve, 411 - fuel channel, 412 - radial fuel injection hole, 42 - oxidant direct current component, 421 - oxidant direct current channel, 422 - small through hole, 43 - axial swirl generating component, 431 - multi-stage axial swirl channel, 432 - threaded hole, 5 - fixing bolt, 6 - perforated plate. Detailed Embodiments

[0023] The present invention will be further described below with reference to the accompanying drawings. As Figure 1 shown, in this burner with axially adjustable oxidizer swirl intensity, a fuel chamber 1, an oxidizer chamber 2, and a mixing chamber 3 are coaxially and hermetically spaced in sequence from bottom to top. The fuel chamber 1 and the oxidizer chamber 2 are separated by an upper fuel chamber partition 13 and a lower oxidizer chamber partition 21, and the oxidizer chamber 2 and the mixing chamber 3 are separated by an upper oxidizer chamber partition 23 and a lower mixing chamber partition 31. A plurality of nozzle assemblies 4 are fixedly arranged in the oxidizer chamber 2. As Figure 3 shown, the plurality of nozzle assemblies 4 are symmetrically arranged with respect to the center of the oxidizer chamber 2 in a square multi-layer array structure.

[0024] The fuel chamber 1 is provided with a lower fuel chamber partition 11, a plurality of fuel input channels 12 with a certain swirl intensity evenly arranged around the central axis of the fuel burner, and an upper fuel chamber partition 13. Fuel enters the fuel chamber 1 in the form of a swirling air flow through the fuel input channels 12.

[0025] The oxidizer chamber 2 is provided with a lower oxidizer chamber partition 21, a plurality of oxidizer input channels 22 with a certain swirl intensity evenly arranged around the central axis of the fuel burner, and an upper oxidizer chamber partition 23. Oxidizer enters the oxidizer chamber 2 in the form of a swirling air flow through the oxidizer input channels 22.

[0026] The mixing chamber 3 is provided with a lower mixing chamber partition 31 and a mixed gas injection channel 32. The mixed gas injection channel 32 is composed of a lower converging pipe section 321 and an upper straight pipe section 322.

[0027] As Figure 4 shown, the combustion nozzle assembly 4 includes a fuel delivery shaft sleeve 41, an oxidizer direct current component 42, and an axial swirl generating component 43. The oxidizer direct current component 42 and the axial swirl generating component 43 are coaxially arranged outside the fuel delivery shaft sleeve 41, and the oxidizer direct current component 42 and the axial swirl generating component 43 are arranged in sequence from bottom to top.

[0028] The oxidizer direct current component 42 is a through-hole shaft sleeve structure with a through-hole inside, and a plurality of groups of oxidizer direct current channels 421 penetrating the oxidizer direct current component 42 are opened thereon. The plurality of groups of oxidizer direct current channels 421 are evenly arranged around the central axis of the oxidizer direct current component 42. As Figure 6 shown, a plurality of small through-holes 422 are opened on the outer periphery of the oxidizer direct current channel 421.

[0029] Inside the axial swirl generating component 43, there is a through-hole shaft sleeve structure with a through-hole coaxially arranged. The upper end of the axial swirl generating component 43 is connected to the upper partition plate 23 of the oxidant chamber by threaded sealing. At the lower end of the axial swirl generating component 43, there is a multi-stage axial swirl channel 431 that penetrates the axial swirl generating component 43 and has a spiral structure. Inside the multi-stage axial swirl channel 431, there are single swirl channels with different axial swirl angles. The number of single swirl channels in the same group of multi-stage axial swirl channels 431 is affected by its swirl angle. The axial swirl angle of the single swirl channel refers to the angle between the central axis of its outlet flow channel and the plane perpendicular to the plane where the outlet surface is located. The swirl angle range of the single swirl channel of the axial swirl generating component 43 is 0 - 70°. Multiple groups of threaded holes 432 are opened on the outer periphery of the multi-stage axial swirl channel 431. The number of groups is the same as the number of small through-holes 422 on the oxidant direct-flow component 42. The number of threaded holes 432 in the same group is the same as the number of single swirl channels in the multi-stage axial swirl channel 431. The lower end of the single swirl channel communicates with the upper end of the oxidant direct-flow channel 421 of the oxidant direct-flow component 42, and the cross-sectional area of the oxidant direct-flow channel 42 on the communication surface is slightly smaller than the cross-sectional area of the single swirl channel on the communication surface; the upper end opening faces the mixed gas injection channel 32. In this embodiment, as Figure 4 , 6 shown, the number of single swirl channels in the multi-stage axial swirl channel 431 is three, and the swirl angles are 30°, 45°, and 60° respectively in the clockwise direction; as Figure 5 , 7 shown, the number of single swirl channels in the multi-stage axial swirl channel 431 is two, and the swirl angles are 60° and 70° respectively in the clockwise direction.

[0030] The fuel delivery shaft sleeve 41 is a blind-hole shaft sleeve structure with a blind hole coaxially arranged inside, and the opening position is at the bottom end of the fuel delivery shaft sleeve 41. The bottom end of the fuel delivery shaft sleeve 41 is connected to the upper partition plate 13 of the fuel chamber by threaded sealing. The blind hole of the fuel delivery shaft sleeve 41 forms a fuel channel 411, and a radial fuel injection hole 412 is opened on one side of the fuel delivery shaft sleeve 41 close to the mixed gas injection channel 32.

[0031] The working principle of the burner with axially adjustable oxidant swirl is as follows: Rotating gaseous fuel is supplied into the fuel chamber 1 through the fuel input channel 11. The fuel flows through the fuel channel 411 of the fuel delivery shaft sleeve 41 extending into the fuel chamber 1 and then flows to the radial fuel injection holes 412, and is injected through the radial fuel injection holes 412 into the front end of the converging section 321 of the mixed gas injection channel 32. Rotating gaseous oxidant is supplied into the oxidant chamber 2 through the oxidant input channel. The oxidant successively passes through the porous plate 6, the oxidant direct flow channel 421 of the oxidant direct flow component 42, and the single swirl channel of the axial swirl generating component 43 and enters the front end of the converging section 321 of the mixed gas injection channel 32. Under the action of the single swirl channel, the oxidant with a certain swirl degree entering the front end of the converging section 321 is preliminarily mixed with the fuel simultaneously entering the front end of the converging section 321. The mixed gas after preliminary mixing is further mixed through the rear end of the converging section 321 and the straight pipe section 322 to achieve better mixing uniformity, and the mixed gas after secondary mixing enters the combustion chamber for combustion. Multiple nozzle assemblies 3 are centrosymmetric with respect to the center of the oxidant chamber 2 and are arranged in a square multi-layer array structure. The nozzle assembly 4 arranged at the center of the oxidant chamber 2 is the central nozzle. The multi-layer multiple nozzles evenly arranged around the central nozzle at a set spacing are the inner layer nozzles. Based on the central axis of the oxidant chamber 2, the nozzles in the outermost layer are the outermost layer nozzles. The oxidant direct flow component 42 and the axial swirl generating component 43 are jointly adjusted according to different working conditions to obtain the required oxidant swirl degree.

[0032] To facilitate the full mixing of fuel and oxidant, as a further improvement of the present invention, the mixed gas injection channel 32 of the mixing chamber 3 is composed of a converging section 321 with a variable cross-section structure and a straight pipe section 322 with a constant cross-section, and the converging section 321 is located at the lower end of the straight pipe section 322. The inner surface of the variable cross-section converging section 321 can generate disturbances to the air flow, thereby facilitating the full mixing of fuel and oxidant.

[0033] To increase the inlet velocity of the mixed gas entering the combustion chamber, as a further improvement of the present invention, the diameter of the converging section 321 decreases successively from the front end to the rear end, so that a greater mixed gas velocity can be obtained in the straight pipe section 322, and finally the inlet velocity entering the combustion chamber is increased.

[0034] To achieve a wider range of oxidant swirl adjustment effects, as a further improvement of the present invention, multiple multi-stage axial swirl channels 431 of the axial swirl generating component 43 are arranged around the central axis of the axial swirl generating component 43. The swirl intensity of the single swirl channels built in the multi-stage axial swirl channels 431 increases or decreases successively in the clockwise direction, and the swirl angle range of the single swirl channels is 0 - 70°.

[0035] In order to achieve precise control of the swirl degree of the nozzle, as a further improvement scheme of the present invention, a rotating structure is also provided between the oxidant direct-current component 42 and the axial swirl generating component 43. The rotating structure is composed of the small through-hole 422 of the oxidant direct-current component 42, the threaded hole 432 of the axial swirl generating component 43 and the fixing bolt 5. A plurality of the same group of threaded holes 432 are provided. After determining the target swirl angle, the small through-hole 422 and the threaded hole 432 corresponding to the single swirl channel are coaxially matched, and then the fixing bolt 5 of the same specification is hermetically connected thereto, so as to realize the connection between the oxidant direct-current channel 421 and the target single swirl channel. In the actual application process, a rubber gasket for sealing can be placed at the interface between the oxidant direct-current component 42 and the axial swirl generating component 43 for further sealing.

[0036] In order to achieve a better mixing effect, as a further improvement scheme of the present invention, the gas outlet area of the radial fuel injection hole 412 is much smaller than the gas outlet area of the single swirl channel outlet of the multi-stage axial swirl channel 431. The oxidant enters the front end of the converging pipe section 321 of the mixed gas injection channel 32 in different directions along the single swirl channel, and at the same time, the gaseous fuel jetting out through the radial fuel injection hole 412 can impact the swirling oxidant at a relatively large jet velocity, thereby improving the mixing effect of the fuel and the oxidant.

[0037] In order to make the airflow entering the nozzle assembly more uniform, as a further improvement scheme of the present invention, a perforated plate 6 is provided between the oxidant direct-current component 42 in the oxidant chamber 2 and the upper partition plate 13 of the fuel chamber, and the perforated plate 6 with different pore diameters and pore spacings can be set according to different situations.

[0038] This burner with axially adjustable oxidant swirl degree can improve the adaptability of the combustion system to multiple fuels, achieve efficient combustion of fuels and reduce pollutant emissions through the combined adjustment mechanism of the oxidant direct-current component and the axial swirl generating component.

Claims

1. A burner with an axially adjustable swirl degree of an oxidant, wherein a fuel chamber (1), an oxidant chamber (2) and a mixing chamber (3) are coaxially and sealedly arranged in sequence from bottom to top. The fuel chamber (1) and the oxidant chamber (2) are separated by an upper fuel chamber partition (13) and a lower oxidant chamber partition (21), and the oxidant chamber (2) and the mixing chamber (3) are separated by an upper oxidant chamber partition (23) and a lower mixing chamber partition (31). A plurality of nozzle assemblies (4) are fixedly arranged in an oxidant chamber (2), and the plurality of nozzle assemblies (4) are symmetrically arranged relative to the center of the oxidant chamber (2) to form a square multi-layer array structure; a fuel chamber lower baffle (11), a fuel input channel (12), and a fuel chamber upper baffle (13) are provided on the fuel chamber (1); an oxidant chamber lower baffle (21), an oxidant input channel (22), and an oxidant chamber upper baffle (23) are provided on the oxidant chamber (2); and a mixing chamber lower baffle (31) and a mixed gas injection channel (32) are provided on the mixing chamber (3); the characteristics are as follows: The combustion nozzle assembly (4) comprises a fuel delivery sleeve (41), an oxidant direct flow component (42), and an axial swirl flow generating component (43). The oxidant direct flow component (42) and the axial swirl flow generating component (43) are coaxially arranged outside the fuel delivery sleeve (41), and the oxidant direct flow component (42) and the axial swirl flow generating component (43) are arranged in order from bottom to top.

2. The oxidant direct flow component (42) is a through-hole sleeve structure with a through hole inside, and an oxidant direct flow channel (421) penetrating the oxidant direct flow component (42) is formed thereon, and a plurality of small through holes (422) are formed on the periphery of the oxidant direct flow channel (421).

3. A through-hole sleeve structure with a through hole coaxially arranged inside the axial swirl generating component (43), and a threaded sealing connection is adopted between the upper end of the axial swirl generating component (43) and the oxidant chamber (2). A multi-stage axial swirl channel (431) penetrating the axial swirl generating component (43) and having a spiral structure is arranged at the lower end of the axial swirl generating component (43), and a single swirl channel with different axial swirl angles is arranged in the multi-stage axial swirl channel (431), and a plurality of groups of threaded holes (432) are opened on the outer periphery of the single swirl channel, and the lower end of the single swirl channel is connected to the upper end of the oxidant direct flow channel (421) of the oxidant direct flow component (42), and the upper end opens toward the mixed gas injection channel (32).

4. The fuel delivery sleeve (41) is a blind hole sleeve structure with a blind hole coaxially disposed therein, and the opening position is located at the bottom end of the fuel delivery sleeve (41), and the bottom end of the fuel delivery sleeve (41) is connected to the fuel chamber upper partition (13) by a threaded seal. The blind hole of the fuel delivery sleeve (41) forms a fuel channel (411), and a radial fuel injection hole (412) is opened on the side of the fuel delivery sleeve (41) close to the mixed gas injection channel (32).

5. The burner with axially adjustable swirl degree of oxidant according to claim 1, characterized in that: A plurality of fuel input channels (12) of the fuel chamber (1) are arranged around the central axis of the burner, and the fuel input channels (12) have a certain degree of swirl. A plurality of oxidant input channels (22) of the oxidant chamber (2) are arranged around the central axis of the burner, and the oxidant input channels (22) have a certain degree of swirl.

6. The burner with axially adjustable swirl degree of the oxidant according to claim 1, characterized in that: The mixed gas injection channel (32) of the mixing chamber (3) is composed of a contraction pipe section (321) with a variable cross-section structure and a straight pipe section (322) with a constant cross-section, and the contraction pipe section (321) is located at the lower end of the straight pipe section (322).

7. The burner with axially adjustable swirl degree of oxidant according to claim 1, characterized in that: A plurality of multi-stage axial swirl channels (431) of the axial swirl generating component (43) are arranged around the central axis of the axial swirl generating component (43), and the swirl intensity of a single swirl channel built into the multi-stage axial swirl channels (431) increases or decreases in sequence in the clockwise direction.

8. The burner with axially adjustable swirl degree of the oxidant according to claims 1 and 4, characterized in that: The swirl angle range of a single swirl channel is 0-70°, and the number of multi-stage axial swirl channels (431) is affected by the swirl intensity of the single swirl channel.

9. The burner with axially adjustable swirl degree of oxidant according to claim 1, characterized in that: The small through hole (422) of the oxidant direct flow component (42) and the threaded hole (432) of the axial swirl flow generating component (43) are connected in a sealed manner via fixing bolts (5).

10. The burner with axially adjustable swirl degree of oxidant according to claim 1, characterized in that: By rotating the oxidant direct flow component (42), the small through holes (422) are respectively coaxial with the threaded holes (432) of the same group but different from each other, thereby enabling the oxidant direct flow channel (421) to be connected to different single swirl channels in the multi-stage axial swirl channel (431), thereby achieving the adjustment of the swirl degree of the nozzle assembly (4).

11. The burner with axially adjustable swirl degree of oxidant according to claim 1, characterized in that: A plurality of radial fuel injection holes (412) of the fuel delivery sleeve (41) are arranged on the same horizontal line.

12. The burner with axially adjustable swirl degree of the oxidant according to claims 1, 3 and 8, characterized in that: The top end of the fuel delivery shaft sleeve (41) is flush with the top end of the straight pipe section (322) of the mixed gas injection channel (32).

13. The burner with axially adjustable swirl degree of oxidant according to claim 1, characterized in that: A porous plate (6) is provided between the oxidant direct flow component (42) in the oxidant chamber (2) and the upper partition plate (13) of the fuel chamber.

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