Lean premixed annular multi-nozzle burner and gas turbine with strong and weak swirl matching

Abstract

The present invention provides a lean premixed annular multi-nozzle burner and gas turbine with strong and weak swirl matching, comprising: an axial swirl nozzle, a fuel premixer and a premixing sleeve; the fuel premixer is installed on the inner side of the premixing sleeve, the premixing sleeve and one end of the fuel premixer are installed on the end plate of the combustion chamber head, and the axial swirl nozzle is installed between the fuel premixer and the premixing sleeve; a plurality of the axial swirl nozzles are installed on the end plate of the combustion chamber head, the swirl numbers of adjacent axial swirl nozzles are different, and the swirl numbers of the alternate axial swirl nozzles are the same. The present invention adopts the arrangement of strong swirl nozzles and weak swirl nozzles alternately, so that the interference between the nozzles is more balanced, the flow and combustion state are stable, so that the influence on the entire multi-nozzle burner when some nozzles are disturbed can be effectively solved, and the stability of the multi-nozzle burner is enhanced.

Description

Technical Field

[0001] The invention relates to the field of multi-nozzle burner structures on gas turbine combustion chambers, and in particular to a lean premixed annular multi-nozzle burner with strong and weak swirl matching and a gas turbine. Background Art

[0002] Due to the high thermal load and large load adjustment ratio of multi-nozzle burners, gas turbines currently often use multiple nozzles with the same swirl number. However, due to the complex interference between the flow between the nozzles and the flames, one of the difficulties faced in the design and operation of multi-nozzle lean premixed burners is poor combustion stability, which is manifested in high-amplitude pressure pulsations that can damage the combustion chamber structure. Therefore, the problem of poor combustion stability can be solved from the perspective of flow interference between multiple nozzles with the same swirl number.

[0003] At present, in the prior art (Chinese patent application number CN201510117660.2, which discloses a gas turbine low-swirl multi-nozzle burner structure), this multi-nozzle arrangement method in which the central nozzle and the surrounding nozzles have different swirl directions can suppress combustion instability and reduce emissions. However, in actual application, due to the large differences in flow and combustion states under different load conditions, the prior art is not sufficient to meet the technical requirements of the entire operating range by adjusting the swirl direction of a single nozzle.

[0004] Patent document CN104728866B discloses a five-nozzle burner structure suitable for a low-pollution combustion chamber of a gas turbine. The burner is composed of five low-swirl nozzles, and the surrounding nozzles are equidistant and evenly arranged circumferentially along the central nozzle, and the swirl directions of the surrounding nozzles are the same. The swirl direction of the central nozzle is the same as or opposite to the swirl direction of the surrounding nozzles. The application aims to use lean premixed combustion of gas fuel and air to reduce the residence time of the flame, reduce the flame temperature, and achieve the purpose of low emissions, but fails to solve the problem of flow interference between multiple nozzles with the same swirl number. Summary of the invention

[0005] In view of the defects in the prior art, the object of the present invention is to provide a lean premixed annular multi-nozzle burner and a gas turbine with matching strong and weak swirls.

[0006] According to the present invention, a lean premixed annular multi-nozzle burner with strong and weak swirl matching is provided, comprising: an axial swirl nozzle, a fuel premixer and a premixing sleeve;

[0007] The fuel premixer is installed inside the premixing sleeve, the premixing sleeve and one end of the fuel premixer are installed on the combustion chamber head end plate of the combustion chamber, and the axial swirl nozzle is installed between the fuel premixer and the premixing sleeve;

[0008] A plurality of the axial swirl nozzles are installed on the end plate of the combustion chamber head, the swirl numbers of adjacent axial swirl nozzles are different, and the swirl numbers of alternate axial swirl nozzles are the same.

[0009] Preferably, the axial swirl nozzle comprises: an axial swirl nozzle outer wall, an axial swirl nozzle inner wall and axial swirl blades;

[0010] The inner side of the axial swirl nozzle outer wall is provided with the inner wall of the axial swirl nozzle, and a plurality of the axial swirl blades are installed between the inner wall of the axial swirl nozzle and the outer wall of the axial swirl nozzle;

[0011] The annular space between the inner wall of the axial swirl nozzle and the outer wall of the axial swirl nozzle is divided into a plurality of axial annular swirl flow channels by the axial swirl blades.

[0012] Preferably, the three adjacent axial swirl nozzles include: a first nozzle, a second nozzle and a third nozzle;

[0013] The first nozzle and the third nozzle are located on both sides of the second nozzle, the swirl number of the second nozzle is not equal to the swirl numbers of the first nozzle and the third nozzle, and the swirl numbers of the first nozzle and the third nozzle are the same.

[0014] Preferably, a fuel premixer inlet is arranged at one end of the fuel premixer facing away from the combustion chamber head end plate, the fuel premixer inlet is connected to a fuel source, a plurality of rows of fuel jet holes are arranged on the side wall of the fuel premixer, the fuel jet holes connect the internal space of the fuel premixer and the space between the outside of the fuel premixer and the premixing sleeve.

[0015] Preferably, a premixing sleeve inlet is arranged between one end of the premixing sleeve facing away from the combustion chamber head end plate and the fuel premixer, and air enters the space between the premixing sleeve and the fuel premixer from the premixing sleeve inlet.

[0016] Preferably, one side of the fuel premixer and the premixing sleeve is connected to the combustion chamber head end plate, and the fuel premixer and the premixing sleeve are installed on the combustion chamber head end plate.

[0017] Preferably, the plurality of axial swirl nozzles have the same swirl direction.

[0018] Preferably, the distance L1 between the second nozzle and the first nozzle or the third nozzle is 1.75d-2.25d;

[0019] The side surface of the combustion chamber is formed by the short side wall of the combustion chamber and the long side wall of the combustion chamber, and the circle surrounded by the axes of the first nozzle, the second nozzle and the third nozzle is concentric with the inner wall of the combustion chamber and the outer wall of the combustion chamber;

[0020] The distance L5 between the axis centers of the first nozzle, the second nozzle and the third nozzle and the long side wall of the combustion chamber is equal to the distance L2 between the axis centers of the first nozzle and the third nozzle and the short side wall of the combustion chamber, which is 1d-1.5d;

[0021] d is the outer diameter of the annular space between the inner wall of the axial swirl nozzle and the outer wall of the axial swirl nozzle.

[0022] Preferably, the distance L3 between two adjacent rows of the fuel injection holes is 0.2d-0.3d;

[0023] The distance L4 between the end of the premixing sleeve facing away from the combustion chamber head end plate and the nearest row of fuel injection holes is 0.15d-0.3d;

[0024] The distance L6 between the end of the axial swirl nozzle facing away from the combustion chamber head end plate and the nearest row of fuel injection holes is 1d-1.5d;

[0025] d is the outer diameter of the annular space between the inner wall of the axial swirl nozzle and the outer wall of the axial swirl nozzle.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] 1. The present invention adopts an alternating arrangement of strong swirl nozzles and weak swirl nozzles to solve the problem that when the swirl numbers of each nozzle of a traditional multi-nozzle burner are the same, due to the interference between the nozzles being in a weak equilibrium state, the jets at the nozzle outlets will swing unsteadily left and right after the interference, inducing flow and heat release pulsation in the combustion chamber, and after disturbances occur at the upstream inlets of some nozzles, the flow and combustion of the multi-nozzle burner will become unstable. The alternating arrangement of strong swirl nozzles and weak swirl nozzles can break the weak equilibrium state between the nozzles, and the strong swirl nozzle jet can continuously and stably squeeze the weak swirl nozzle jet, causing the jet to always deflect to one side, making the interference between the nozzles more balanced and stable, and the flow and combustion states stable, thereby effectively solving the impact of disturbances in some nozzles on the entire multi-nozzle burner and enhancing the stability of the multi-nozzle burner.

[0028] 2. By adopting the alternating arrangement of strong swirl nozzles and weak swirl nozzles, the turbulence intensity of the nozzle outlet jet and the vortex intensity of the recirculation zone can be significantly improved. The increase in the jet turbulence intensity can effectively promote the heat and mass transfer between the jet and the burned high-temperature gas. The increase in the vortex intensity in the recirculation zone can enhance the entrainment of the burned high-temperature flue gas, thereby achieving the purpose of enhancing the flow mixing effect and reducing the carbon monoxide emissions in the combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0030] Figure 1 It is a front half-section view of an annular multi-nozzle burner;

[0031] Figure 2 It is a side half-section view of an annular multi-nozzle burner;

[0032] Figure 3 It is a cross-sectional view of the premixing sleeve and the fuel premixer;

[0033] Figure 4 It is a three-dimensional structural diagram of the premixing sleeve and the fuel premixer;

[0034] Figure 5 It is a three-dimensional structural diagram of the axial swirl nozzle;

[0035] Figure 6 This is the principle diagram of interference between swirl nozzles;

[0036] Figure 7 It is a schematic diagram of the structure of 12 strong and weak alternating annular swirl nozzles;

[0037] Figure 8 Comparison of CO emissions when the swirl number of the three nozzles is 0.72 and the swirl number of the second nozzle is increased to 1.02;

[0038] Fig. 9 Comparison of the pressure pulsation amplitude in the combustion chamber under the test condition of equivalence ratio of 0.83 when the swirl number of the three nozzles is 0.72;

[0039] Fig.10 Comparison of the pressure pulsation amplitude in the combustion chamber under the test condition of an equivalence ratio of 0.83 when the swirl number of the second nozzle is increased to 1.02.

[0040] As shown in the figure:

[0041] DETAILED DESCRIPTION

[0042] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0043] Example 1

[0044] like Figure 1 and Figure 2As shown, this embodiment can be used in the combustion chamber of a gas turbine, and includes: an axial swirl nozzle 1, a fuel premixer 2 and a premixing sleeve 3; the fuel premixer 2 is installed inside the premixing sleeve 3, and one end of the premixing sleeve 3 and the fuel premixer 2 is installed on the combustion chamber head end plate 41. An axial swirl nozzle 1 is installed between the fuel premixer 2 and the premixing sleeve 3; a plurality of axial swirl nozzles 1 are installed on the combustion chamber head end plate 41, and the plurality of axial swirl nozzles 1 have the same rotation direction, the swirl numbers of adjacent axial swirl nozzles 1 are different, and the swirl numbers of the interlaced axial swirl nozzles 1 are the same. The three adjacent axial swirl nozzles 1 include: a first nozzle 11, a second nozzle 12 and a third nozzle 13; the first nozzle 11 and the third nozzle 13 are located on both sides of the second nozzle 12, the swirl number of the second nozzle 12 is not equal to the swirl number of the first nozzle 11 and the third nozzle 13, and the swirl number of the first nozzle 11 and the third nozzle 13 is the same. The side surface of the combustion chamber 4 is formed by the combustion chamber inner wall 42 and the combustion chamber outer wall 43 . The combustion chamber inner wall 42 and the combustion chamber outer wall 43 are concentric with the circle formed by the axes of the first nozzle 11 , the second nozzle 12 and the third nozzle 13 .

[0045] like Figure 3 and Figure 4 As shown, a premixing sleeve inlet 31 is arranged between the end of the premixing sleeve 3 facing away from the end plate 41 of the combustion chamber head and the fuel premixer 2, and air enters the space between the premixing sleeve 3 and the fuel premixer 2 from the premixing sleeve inlet 31. A fuel premixer inlet 21 is arranged at the end of the fuel premixer 2 facing away from the end plate 41 of the combustion chamber head, and the fuel premixer inlet 21 is connected to a fuel source. A plurality of rows of fuel jet holes 22 are arranged on the side wall of the fuel premixer 2, and the fuel jet holes 22 communicate with the internal space of the fuel premixer 2 and the space between the outside of the fuel premixer 2 and the premixing sleeve 3.

[0046] like Figure 5 As shown, the axial swirl nozzle 1 includes: an axial swirl nozzle outer wall 103, an axial swirl nozzle inner wall 104 and an axial swirl blade 105; the axial swirl nozzle inner wall 104 is arranged inside the axial swirl nozzle outer wall 103, a plurality of axial swirl blades 105 are installed between the axial swirl nozzle inner wall 104 and the axial swirl nozzle outer wall 103, and the annular space between the axial swirl nozzle inner wall 104 and the axial swirl nozzle outer wall 103 is divided into a plurality of axial annular swirl flow channels 106 by the axial swirl blades 105.

[0047] The distance L1 between the second nozzle 12 and the first nozzle 11 or the third nozzle 13 is 1.75d-2.25d; the distance L5 between the axis of the first nozzle, the second nozzle and the third nozzle and the inner wall 42 of the combustion chamber is equal to the distance L2 between the axis of the first nozzle, the second nozzle and the third nozzle and the outer wall 43 of the combustion chamber, which is 1d-1.5d; the distance L3 between two adjacent rows of fuel jet holes 22 is 0.2d-0.3d; the distance L4 between the end of the premixing sleeve 3 facing away from the end plate 41 of the combustion chamber head and the nearest row of fuel jet holes 22 is 0.15d-0.3d; the distance L6 between the end of the axial swirl nozzle 1 facing away from the end plate 41 of the combustion chamber head and the nearest row of fuel jet holes 22 is 1d-1.5d; d is the outer diameter of the annular space between the inner wall 104 of the axial swirl nozzle and the outer wall 103 of the axial swirl nozzle.

[0048] Working principle:

[0049] like Figure 6 As stated, Figure 6 The left side is a strong swirl nozzle. Figure 6 The right side is a weak swirl nozzle. The jet 53 of the strong swirl nozzle can continuously and stably squeeze the jet 53 of the weak swirl nozzle, causing the jet to always deflect to one side without swinging left and right, making the interference between the nozzles more balanced and stable, and the flow and combustion state stable.

[0050] By adopting the alternating arrangement of strong swirl nozzles and weak swirl nozzles, the turbulence intensity of the nozzle outlet jet 53 and the vortex intensity of the recirculation zones 51 and 52 can be significantly improved. The increase in the turbulence intensity of the jet 53 can effectively promote the heat and mass transfer between the jet 53 and the burned high-temperature gas near the jet boundary. The increase in the vortex intensity of the recirculation zones 51 and 52 can enhance the suction of the burned high-temperature flue gas, and suck the high-temperature gas that has been fully burned downstream back to the nozzle outlet, thereby achieving the purpose of enhancing the flow mixing effect and reducing the carbon monoxide emissions in the combustion chamber.

[0051] Example 2

[0052] Example 2 is a preferred example of Example 1.

[0053] like Figures 1 to 7 As shown, the axial swirl nozzle 1 comprises: an axial swirl nozzle outer wall 103, an axial swirl nozzle inner wall 104, an axial swirl nozzle inlet 102, an axial swirl nozzle outlet 101, an axial annular swirl flow channel 106 and an axial swirl blade 105;

[0054] The axial swirl nozzle 1 is located between the fuel premixer 2 and the premixing sleeve 3. The inner wall 104 of the axial swirl nozzle is installed on one end of the fuel premixer 2 through a thread. The outer wall 103 of the axial swirl nozzle is installed on the premixing sleeve 3 through a thread. Three rows of fuel injection holes 22 are opened on the side of the fuel premixer 2.

[0055] A premixing sleeve inlet 31 is provided at one end of the premixing sleeve 3 facing away from the end plate 41 of the combustion chamber head. Air enters the space between the premixing sleeve 3 and the fuel premixer 2 through the premixing sleeve inlet 31. A fuel premixer inlet 21 is provided at one end of the fuel premixer 2 facing away from the end plate 41 of the combustion chamber head. Gas fuel enters the fuel premixer 2 through the fuel premixer inlet 21. To achieve the purpose of premixed combustion, the gas fuel is mixed with the air in the premixing sleeve 3 through the fuel jet hole 22. The mixed gas fuel enters the axial swirl nozzle 1 through the axial swirl nozzle inlet 102 and enters the combustion chamber 4 from the axial swirl nozzle outlet 101.

[0056] This embodiment includes a total of 12 axial swirl nozzles 1 with the same rotation direction, and the 12 axial swirl nozzles 1 are arranged in a ring, and the swirl numbers of adjacent axial swirl nozzles 1 are different, and the swirl numbers of alternate axial swirl nozzles 1 are the same. In this embodiment, three adjacent axial swirl nozzles 1 with the same rotation direction are intercepted, including: a first nozzle 11, a second nozzle 12 and a third nozzle 13, and the first nozzle 11 and the third nozzle 13 are symmetrically arranged about the second nozzle 12.

[0057] An annular space is formed between the outer wall 103 of the axial swirl nozzle and the inner wall 104 of the axial swirl nozzle, and the annular space is divided into multiple axial annular swirl channels 106 by multiple axial swirl blades 105. The swirl number is adjusted by adjusting the installation angle of the axial swirl blades 105. The swirl numbers of the first nozzle 11 and the third nozzle 13 are the same, and the swirl number of the second nozzle 12 is greater than or less than the first nozzle 11 and the third nozzle 13.

[0058] The axial swirl nozzle 1 is composed of 6-8 axial swirl blades 105. The blade installation angle of the axial swirl blades 105 is 40° to 50°, and the swirl number ranges from 0.72 to 1.02. , dimensionless parameters are generally used to quantify the swirl intensity, that is, the swirl number, and its definition is shown in the following formula:

[0059]

[0060] Among them, θ is the installation angle of the nozzle swirl blade, and its sine value is a dimensionless parameter; Z is the ratio of the inner diameter d to the outer diameter D of the nozzle swirl flow channel, which is a dimensionless parameter.

[0061] In some embodiments, the distance L1 between the second nozzle 12 and the first nozzle 11 or the third nozzle 13 is 1.75d-2.25d;

[0062] To prevent overheating of the inner wall 42 and the outer wall 43 of the combustion chamber 4, the distance L5 between the axis of the first nozzle 11, the second nozzle 12 and the third nozzle 13 and the inner wall 42 of the combustion chamber is equal to the distance L2 between the axis of the first nozzle 11, the second nozzle 12 and the third nozzle 13 and the outer wall 43 of the combustion chamber, which is 1d-1.5d;

[0063] The distance L3 between two adjacent rows of fuel injection holes 22 is 0.2d-0.3d;

[0064] To ensure that the fuel and air are fully premixed, the distance L4 between the end of the premixing sleeve 3 facing away from the combustion chamber head end plate 41 and the nearest row of fuel injection holes 22 is 0.15d-0.3d;

[0065] The distance L6 between the end of the axial swirl nozzle 1 facing away from the combustion chamber head end plate 41 and the nearest row of fuel injection holes 22 is 1d-1.5d;

[0066] d is the outer diameter of the annular space between the axial swirl nozzle inner wall 104 and the axial swirl nozzle outer wall 103 .

[0067] Example 3

[0068] like Figure 8 As shown, in some embodiments, three axial swirl nozzles 1 are taken as an example. When three axial swirl nozzles 1 are used, the CO emissions of the burner with three axial swirl nozzles 1 all having a swirl number of 0.72 and the burner with the swirl number of the middle axial swirl nozzle 1 increased to 1.02 are compared under different test conditions. Under different equivalence ratio conditions, such as Figure 8 As shown in the middle A line, after increasing the swirl number of the intermediate axial swirl nozzle 1, the CO emission is between 1 and 2 ppm; Figure 8 As shown in the middle line B, when the swirl numbers of the three axial swirl nozzles 1 are all 0.72, the CO emission is as high as 40 ppm. The results show that increasing the swirl number of the middle axial swirl nozzle 1 helps to enhance combustion and reduce CO emissions at the outlet of the combustion chamber 4.

[0069] At the same time, the test found that under low equivalence ratio conditions, the burner with three axial swirl nozzles 1 and a swirl number of 0.72 would be more prone to flameout. The test results show that by increasing the swirl number of the central axial swirl nozzle 1 to 1.02, its flameout equivalence ratio can be reduced from 0.59 to 0.53, effectively improving the flameout boundary.

[0070] Combination Fig. 9 and Fig.10As shown, the pressure pulsation amplitude in the combustion chamber 4 is compared under the test condition of an equivalence ratio of 0.83 for a burner with three axial swirl nozzles 1 having a swirl number of 0.72 and a burner with a central axial swirl nozzle 1 having a swirl number increased to 1.02. It can be found that the main frequency of the combustion oscillation has changed from 322Hz to 269Hz; secondly, the pressure pulsation amplitude in the combustion chamber 4 has decreased by about 70%. This shows that by increasing the swirl number of the intermediate axial swirl nozzle 1, combustion instability can be effectively suppressed.

[0071] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0072] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A lean premixed annular multi-nozzle burner with strong and weak swirl matching, characterized in that: include: An axial swirl nozzle (1), a fuel premixer (2) and a premixing sleeve (3); The fuel premixer (2) is installed inside the premixing sleeve (3), the premixing sleeve (3) and one end of the fuel premixer (2) are installed on a combustion chamber head end plate (41) of the combustion chamber (4), and the axial swirl nozzle (1) is installed between the fuel premixer (2) and the premixing sleeve (3); A plurality of the axial swirl nozzles (1) are installed on the combustion chamber head end plate (41), the swirl numbers of adjacent axial swirl nozzles (1) are different, and the swirl numbers of alternate axial swirl nozzles (1) are the same; The axes of the plurality of swirl nozzles are concentrically arranged in a circle.

2. The lean premixed annular multi-nozzle burner with strong and weak swirl matching according to claim 1 is characterized in that: The axial swirl nozzle (1) comprises: an axial swirl nozzle outer wall (103), an axial swirl nozzle inner wall (104) and axial swirl blades (105); The axial swirl nozzle inner wall (104) is arranged inside the axial swirl nozzle outer wall (103), and a plurality of axial swirl blades (105) are installed between the axial swirl nozzle inner wall (104) and the axial swirl nozzle outer wall (103); The annular space between the inner wall (104) of the axial swirl nozzle and the outer wall (103) of the axial swirl nozzle is divided into a plurality of axial annular swirl flow channels (106) by the axial swirl blades (105).

3. The lean premixed annular multi-nozzle burner with strong and weak swirl matching according to claim 2 is characterized in that: The three adjacent axial swirl nozzles (1) include: a first nozzle (11), a second nozzle (12) and a third nozzle (13); The first nozzle (11) and the third nozzle (13) are located on both sides of the second nozzle (12); the swirl number of the second nozzle (12) is not equal to the swirl number of the first nozzle (11) and the third nozzle (13); the swirl numbers of the first nozzle (11) and the third nozzle (13) are the same.

4. The lean premixed annular multi-nozzle burner with strong and weak swirl matching according to claim 2 is characterized in that: A fuel premixer inlet (21) is arranged at one end of the fuel premixer (2) facing away from the combustion chamber head end plate (41), and the fuel premixer inlet (21) is connected to a fuel source. A plurality of rows of fuel jet holes (22) are arranged on the side wall of the fuel premixer (2), and the fuel jet holes (22) communicate with the internal space of the fuel premixer (2) and the space between the outside of the fuel premixer (2) and the premixing sleeve (3).

5. The lean premixed annular multi-nozzle burner with strong and weak swirl matching according to claim 1 is characterized in that: A premixing sleeve inlet (31) is arranged between one end of the premixing sleeve (3) facing away from the combustion chamber head end plate (41) and the fuel premixer (2), and air enters the space between the premixing sleeve (3) and the fuel premixer (2) from the premixing sleeve inlet (31).

6. The lean premixed annular multi-nozzle burner with strong and weak swirl matching according to claim 1 is characterized in that: The plurality of axial swirl nozzles (1) have the same swirl direction.

7. The lean premixed annular multi-nozzle burner with strong and weak swirl matching according to claim 3 is characterized by: A distance L1 between the second nozzle (12) and the first nozzle (11) or the third nozzle (13) is 1.75d-2.25d; The side of the combustion chamber (4) is formed by a short side wall (42) and a long side wall (43) of the combustion chamber, and the circle formed by the axes of the first nozzle (11), the second nozzle (12) and the third nozzle (13) is concentric with the inner side wall (42) and the outer side wall (43) of the combustion chamber; The distance L5 between the axis centers of the first nozzle (11), the second nozzle (12) and the third nozzle (13) and the long side wall (42) of the combustion chamber is equal to the distance L2 between the axis centers of the first nozzle (11) and the third nozzle (13) and the short side wall (43) of the combustion chamber, which is 1d-1.5d; d is the outer diameter of the annular space between the inner wall (104) of the axial swirl nozzle and the outer wall (103) of the axial swirl nozzle.

8. The lean premixed annular multi-nozzle burner with strong and weak swirl matching according to claim 4 is characterized in that: The distance L3 between two adjacent rows of the fuel injection holes (22) is 0.2d-0.3d; The distance L4 between the end of the premixing sleeve (3) facing away from the combustion chamber head end plate (41) and the nearest row of fuel injection holes (22) is 0.15d-0.3d; The distance L6 between the end of the axial swirl nozzle (1) facing away from the combustion chamber head end plate (41) and the nearest row of fuel injection holes (22) is 1d-1.5d; d is the outer diameter of the annular space between the inner wall (104) of the axial swirl nozzle and the outer wall (103) of the axial swirl nozzle.

9. A gas turbine, characterized in that: A lean premixed annular multi-nozzle burner with matching strong and weak swirls as described in any one of claims 1 to 8 is used.

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