Burner nozzle and axial staged burner

Abstract

The invention provides a burner nozzle and an axial staged burner. The combustor nozzle comprises a fairing and a swirler which are connected, the fairing is provided with a rectifying hole, the swirler comprises a center shaft, blades and a shell, the multiple blades distributed at intervals are arranged on the periphery of the center shaft, the center shaft is provided with a first fuel channel, second fuel channels are formed in the blades, and fuel outlets are formed in the wall faces of the blades. The first fuel channel communicates with the fuel outlet through the second fuel channel, the shell is connected to the peripheries of the multiple blades and provided with a fuel inlet, third fuel channels are further arranged in at least part of the blades, and the fuel inlet communicates with the second fuel channel through the third fuel channels. The burner nozzle has a stable burning effect, and is simple in structure and convenient to produce, disassemble and assemble.

Description

Technical Field

[0001] The invention relates to the field of burners, and in particular to a burner nozzle and an axially graded burner. Background Art

[0002] The axially staged burner is one of the core components of the gas turbine, which includes the first-stage fuel nozzle and the second-stage fuel nozzle along the medium flow direction. The fuel is injected in stages through the first-stage fuel nozzle and the second-stage fuel nozzle, which can reduce the residence time of the fuel in the high-temperature area of ​​the combustion chamber, reduce the emission of NOx during the combustion process, and ensure the combustion temperature at low load and reduce the generation of CO. However, in the related art, the structure of the second-stage fuel nozzle is relatively complex, and there is a situation of unstable combustion. Summary of the invention

[0003] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.

[0004] To this end, an embodiment of the present invention provides a burner nozzle and an axially staged burner using the burner nozzle.

[0005] The burner nozzle of the embodiment of the present invention comprises:

[0006] A connected fairing and swirler, the fairing is provided with a fairing hole, the swirler includes a central axis, blades and an outer shell, the outer periphery of the central axis is provided with a plurality of blades arranged at intervals, the central axis is provided with a first fuel channel, the interior of the blades is provided with a second fuel channel, the wall of the blades is provided with a fuel outlet, the second fuel channel connects the first fuel channel with the fuel outlet, the outer shell is connected to the outer periphery of the plurality of blades and is provided with a fuel inlet, at least some of the blades are also provided with a third fuel channel, the third fuel channel connects the fuel inlet with the second fuel channel.

[0007] In the burner nozzle of the embodiment of the present invention, the rectifying hole of the fairing rectify the incoming gas to ensure that the incoming gas stably flows to the swirler, the fuel is supplied through the fuel inlet, and is supplied to the fuel outlet through the third fuel channel, the first fuel channel and the second fuel channel in sequence, so that the fuel is discharged into the swirler through the fuel outlet on the blade wall surface, so that the fuel and the incoming gas are fully and evenly mixed, thereby ensuring stable fuel combustion. Therefore, the burner nozzle of the embodiment of the present invention has a stable combustion effect, and the structure is simple, which is easy to produce and disassemble.

[0008] In some embodiments, the blade has a first wall surface and a second wall surface that are relatively arranged along the circumferential direction of the central axis, and the first wall surface and the second wall surface of each of the blades are provided with the fuel outlet, or the first wall surface of each of the blades is provided with the fuel outlet, or the second wall surface of each of the blades is provided with the fuel outlet.

[0009] In some embodiments, the second fuel channel extends radially along the central axis, a wall surface of the blade is provided with a plurality of the fuel outlets, and the plurality of the fuel outlets are arranged at intervals along the second fuel channel.

[0010] In some embodiments, the blade is provided with at least two second fuel passages, and the at least two second fuel passages are arranged at intervals along the axial direction of the central axis.

[0011] In some embodiments, a conical first protrusion is provided at one end of the central axis facing the fairing, and the first protrusion extends into the fairing.

[0012] In some embodiments, a circular second protrusion is provided at the other end of the central axis away from the fairing.

[0013] In some embodiments, the second protrusion is provided with a fuel nozzle, and the fuel nozzle is communicated with the first fuel channel.

[0014] In some embodiments, both the axial wall and the circumferential wall of the fairing are provided with fairing holes.

[0015] In some embodiments, the burner nozzle also includes a cylindrical base, which is connected to one end of the swirler away from the swirler, and the inner cavity of the base is connected to the swirler, and the base is provided with a plurality of cooling holes arranged at intervals along the circumferential direction, and the cooling holes are connected to the inner cavity of the base.

[0016] In some embodiments, the burner nozzle also includes a first sealing ring and a second sealing ring, the fairing is provided with a first flange portion, the swirler is provided with a second flange portion and a third flange portion, the base is provided with a fourth flange portion, the first flange portion is connected to the second flange portion, and the first sealing ring is provided between the first flange portion and the second flange portion, the third flange portion is connected to the fourth flange portion, and the second sealing ring is provided between the third flange portion and the fourth flange portion.

[0017] The axially staged burner of the embodiment of the present invention comprises:

[0018] The first-stage fuel nozzle and the second-stage fuel nozzle, wherein the second-stage fuel nozzle is the burner nozzle described in any one of the above embodiments.

[0019] The axially staged burner of the embodiment of the present invention, the second-stage fuel nozzle adopts the burner nozzle of the embodiment of the present invention, so as to have a stable combustion effect and be easy to assemble and maintain. In addition, it avoids direct contact with the mainstream fuel gas to prevent high temperature and thermal acoustic problems.

[0020] In some embodiments, the axially staged combustor further includes a flame tube, and the burner nozzle includes a cylindrical base connected to the flame tube. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 1 is a schematic diagram of a first example of a burner nozzle according to an embodiment of the present invention, in which the burner nozzle is arranged on a flame tube;

[0022] Figure 2 1 is a schematic diagram of a second example of a burner nozzle according to an embodiment of the present invention, in which the burner nozzle is arranged on a flame tube;

[0023] Figure 3 is a cross-sectional view of a first example of a burner nozzle according to an embodiment of the present invention;

[0024] Figure 4 yes Figure 3 A magnified schematic diagram of part A;

[0025] Figure 5 yes Figure 3 A magnified schematic diagram of part B;

[0026] Figure 6 yes Figure 1 A schematic diagram of a first example of a mesocyclone;

[0027] Figure 7 is a cross-sectional view of a second example of a swirler of a burner nozzle according to an embodiment of the present invention;

[0028] Figure 8 is a schematic diagram of a second example of a swirler of a burner nozzle according to an embodiment of the present invention;

[0029] Fig. 9 is a cross-sectional view of a third example of a swirler of a burner nozzle according to an embodiment of the present invention;

[0030] Fig.10 is a schematic diagram of a fourth example of a swirler of a burner nozzle according to an embodiment of the present invention;

[0031] Fig.11 Schematic diagram of a fifth example of a swirler of a burner nozzle according to an embodiment of the present invention.

[0032] Reference numerals:

[0033] 1. fairing; 11. fairing hole; 12. first flange;

[0034] 2. swirler; 21. central axis; 211. first fuel channel; 212. first protrusion; 213. second protrusion; 214. fuel nozzle; 22. blade; 221. second fuel channel; 222. fuel outlet; 223. third fuel channel; 224. first wall; 225. second wall; 23. housing; 231. fuel inlet; 24. second flange; 25. third flange;

[0035] 3. Base; 31. Cooling hole; 32. Fourth flange;

[0036] 4. The first sealing ring;

[0037] 5. Second sealing ring;

[0038] 6. Flame tube. DETAILED DESCRIPTION

[0039] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0040] Reference below Figure 1-Figure 11 A combustor nozzle and an axially staged combustor according to embodiments of the present invention are described.

[0041] like Figure 1-Figure 11 As shown, the burner nozzle according to the embodiment of the present invention includes a fairing 1 and a swirler 2 .

[0042] The fairing 1 is connected to the cyclone 2. Specifically, Figure 1-Figure 3 As shown, the fairing 1 is preferably but not limited to being arranged at the top of the cyclone 2 and connected to the inlet end of the cyclone 2 (such as Figure 1 The top of the cyclone 2 is connected to

[0043] The fairing 1 is provided with a fairing hole 11. Specifically, the fairing hole 11 penetrates through the wall of the fairing 1 and communicates with the inner cavity of the fairing 1.

[0044] The cyclone 2 includes a central shaft 21, blades 22 and a housing 23. A plurality of blades 22 are arranged at intervals on the outer circumference of the central shaft 21. In other words, the plurality of blades 22 are connected to the central shaft 21 and are arranged at intervals along the circumference of the central shaft 21.

[0045] The central shaft 21 is provided with a first fuel channel 211, the interior of the blade 22 is provided with a second fuel channel 221, the wall of the blade 22 is provided with a fuel outlet 222, and the second fuel channel 221 connects the first fuel channel 211 with the fuel outlet 222. The fuel outlet 222 can be a round hole, a square hole, a waist-shaped hole, etc.

[0046] The outer shell 23 is connected to the outer periphery of the plurality of blades 22 and is provided with a fuel inlet 231. Specifically, the outer shell 23 is preferably, but not limited to, cylindrical, and the axis of the outer shell 23 is parallel to the axis of the central axis 21, so that the outer shell 23 surrounds the outer periphery of the central axis 21 and is spaced from the central axis 21, and the plurality of blades 22 are connected between the outer peripheral surface of the central axis 21 and the inner peripheral surface of the outer shell 23. The fuel inlet 231 is preferably, but not limited to, provided on the outer peripheral surface of the outer shell 23 and penetrates the shell wall of the outer shell 23.

[0047] At least some of the blades 22 are further provided with a third fuel channel 223, preferably but not limited to, one of the blades 22 is provided with a third fuel channel 223, and the third fuel channel 223 is spaced apart from the second fuel channel 221 located in the same blade 22. The third fuel channel 223 connects the fuel inlet 231 with the second fuel channel 221.

[0048] When the burner nozzle is in use, incoming gas such as air enters the inner cavity of the fairing 1 through the fairing hole 11, and then enters the swirler 2 from the inlet end of the swirler 2. Fuel is supplied from the fuel inlet 231, and then sequentially passes through the third fuel channel 223, the first fuel channel 211 and the second fuel channel 221 to the fuel outlet 222, so that the fuel is evenly supplied to the swirler 2 through the fuel outlet 222 on the wall surface of each blade 22, so that the fuel and the incoming gas are fully and evenly mixed in the swirler 2, and then discharged from the outlet end (such as Figure 1 The water is discharged from the bottom end of the cyclone 2 shown.

[0049] In the burner nozzle of the embodiment of the present invention, the rectifying hole of the fairing rectify the incoming gas to ensure that the incoming gas stably flows to the swirler, the fuel is supplied through the fuel inlet, and is supplied to the fuel outlet through the third fuel channel, the first fuel channel and the second fuel channel in sequence, so that the fuel is discharged into the swirler through the fuel outlet on the blade wall surface, so that the fuel and the incoming gas are fully and evenly mixed, thereby ensuring stable fuel combustion. Therefore, the burner nozzle of the embodiment of the present invention has a stable combustion effect, and the structure is simple, which is easy to produce and disassemble.

[0050] In some embodiments, the blade 22 has a first wall surface 224 and a second wall surface 225 which are arranged opposite to each other along the circumferential direction of the central axis 21. Figure 6 and Figure 8 shown.

[0051] A fuel outlet 222 may be provided on the first wall surface 224 and the second wall surface 225 of each blade 22. Figure 7 and Figure 8 When the incoming gas passes between adjacent blades 22, the incoming gas between the adjacent blades 22 is mixed with the fuel discharged from the first wall surface 224 of the blade 22 on one side and the fuel discharged from the second wall surface 225 of the blade 22 on the other side, so that the fuel and the incoming gas are fully and evenly mixed in the swirler 2 in the circumferential direction of the swirler 2.

[0052] Alternatively, only the first wall surface 224 of each blade 22 may be provided with a fuel outlet 222, and the second wall surface 225 may not be provided with a fuel outlet 222; or only the second wall surface 225 of each blade 22 may be provided with a fuel outlet 222, and the first wall surface 224 may not be provided with a fuel outlet 222. Figure 3 , Figure 6 and Fig. 9 When the incoming gas passes between adjacent blades 22, the incoming gas between the adjacent blades 22 is mixed with the fuel discharged from the first wall surface 224 of the blade 22 on one side, or is mixed with the fuel discharged from the second wall surface 225 of the blade 22 on the other side, so that the fuel and the incoming gas are fully and evenly mixed in the swirler 2 in the circumferential direction of the swirler 2.

[0053] Preferably, the first wall surface 224 and the second wall surface 225 of each blade 22 are both provided with a fuel outlet 222 to achieve a better mixing effect between the fuel and the incoming gas.

[0054] In some embodiments, the second fuel channel 221 extends radially along the central axis 21 , and a wall surface of the blade 22 is provided with a plurality of fuel outlets 222 , and the plurality of fuel outlets 222 are arranged at intervals along the second fuel channel 221 .

[0055] like Figure 3 , Figure 7 and Fig. 9 As shown, the second fuel channel 221 extends in the radial direction of the central axis 21 . In other words, the second fuel channel 221 extends in the radial direction of the swirler 2 .

[0056] It is understandable that the second fuel channel 221 may extend in a straight line or in a curved manner along the radial direction of the central axis 21. The third fuel channel 223 may extend in a straight line or in a curved manner along the radial direction of the central axis 21.

[0057] The second fuel channel 221 is connected to a plurality of fuel outlets 222. The plurality of fuel outlets 222 connected to the second fuel channel 221 may all be located on the first wall surface 224 or all be located on the second wall surface 225. Figure 3 , Figure 6 and Fig. 9The plurality of fuel outlets 222 communicating with the second fuel channel 221 may also be partially located on the first wall surface 224 and partially located on the second wall surface 225, as shown in FIG. Figure 7 and Figure 8 shown.

[0058] A plurality of fuel outlets 222 connected to the second fuel channel 221 and located on the same wall surface (the first wall surface 224 or the second wall surface 225) of the blade 22 are arranged at intervals along the second fuel channel 221, such as Figure 3 , Figure 6-Figure 9 shown.

[0059] When the incoming gas passes between adjacent blades 22 , the incoming gas mixes with the fuel discharged from a plurality of fuel outlets 222 arranged at intervals along the second fuel channel 221 , so that the fuel and the incoming gas are fully and evenly mixed in the radial direction of the swirler 2 in the swirler 2 .

[0060] In some embodiments, the blade 22 is provided with at least two second fuel channels 221 , and the at least two second fuel channels 221 are arranged at intervals along the axial direction of the central axis 21 .

[0061] like Figure 7 and Figure 8 As shown, the first fuel channel 211 extends axially along the center axis 21, and the blade 22 is provided with at least two second fuel channels 221, preferably but not limited to two second fuel channels 221, the two second fuel channels 221 are arranged axially at intervals along the center axis 21, and are connected to the first fuel channel 211.

[0062] When the incoming gas passes between adjacent blades 22 , the incoming gas is sequentially mixed with the fuel discharged from the two rows of fuel outlets 222 , thereby improving the mixing efficiency of the fuel and the incoming gas.

[0063] It is understood that the blade 22 is not limited to having at least two second fuel passages 221. Figure 3 , Figure 6 , Fig. 9 In the example shown, a second fuel passage 221 is provided in the blade 22 .

[0064] It should be noted that the relative positions of the second fuel channel 221 and the third fuel channel 223 are not limited. When the blade 22 is provided with two second fuel channels 221, the third fuel channel 223 is preferably located between the two second fuel channels 221, such as Figure 7 When the blade 22 is provided with a second fuel channel 221, the third fuel channel 223 may be located below the second fuel channel 221, as shown in FIG. Figure 3 It can also be located above the second fuel channel 221, such as Fig. 9 shown.

[0065] Furthermore, the second fuel channels 221 in all the blades 22 are correspondingly arranged along the axial direction of the central axis 21 to achieve a better mixing effect.

[0066] In some embodiments, the blade 22 may be a swirl blade to generate a swirl flow, or may be a non-swirl blade to generate no swirl flow.

[0067] The blade 22 may be a straight blade, such as Figure 6 , Figure 8 and Fig.11 The blades 22 may also be bent, such as Fig.10 The blade 22 may also be a spiral blade.

[0068] In some embodiments, a conical first protrusion 212 is disposed at one end of the central shaft 21 facing the fairing 1 , and the first protrusion 212 extends into the fairing 1 .

[0069] like Figure 3 , Figure 7 and Fig. 9 As shown, a first protrusion 212 extending upward is provided at the top of the central shaft 21 . The first protrusion 212 is conical, and may be a cone or a pyramid. The first protrusion 212 extends into the fairing 1 .

[0070] The first protrusion 212 can reduce air flow resistance, thereby ensuring a stable flame generated by the burner nozzle.

[0071] In some embodiments, a circular second protrusion 213 is disposed at the other end of the central shaft 21 away from the fairing 1 .

[0072] like Figure 3 , Figure 6-Figure 11 As shown, a circular second protrusion 213 is disposed at the bottom end of the central shaft 21 , and the second protrusion 213 is preferably, but not limited to, hemispherical.

[0073] The second protrusion 213 can form a reflow zone, thereby ensuring the flame stability generated by the burner nozzle.

[0074] In some embodiments, the second protrusion 213 is provided with a fuel nozzle 214 , and the fuel nozzle 214 is communicated with the first fuel channel 211 .

[0075] like Fig.11As shown, the second protrusion 213 is provided with a fuel nozzle 214, and the fuel nozzle 214 can be one, and the fuel nozzle 214 is located at the center of the second protrusion 213. In other words, the fuel nozzle 214 is located on the axis of the central axis 21. In other words, the fuel nozzle 214 is located on the center line of the central axis 21. The fuel nozzle 214 can also be provided in plurality, and the plurality of fuel nozzles 214 are preferably, but not limited to, uniformly distributed on the outer wall surface of the second protrusion 213.

[0076] The fuel nozzle 214 is in communication with the first fuel channel 211 , and the fuel sprayed from the fuel nozzle 214 is used as a duty fuel, which can improve the stability of the flame generated by the burner nozzle.

[0077] It is understandable that the second protrusion 213 may also be provided in a closed manner, such as Figure 3 , Figure 6-Figure 10 shown.

[0078] In some embodiments, both the axial wall and the circumferential wall of the fairing 1 are provided with fairing holes 11 .

[0079] like Figure 1-Figure 3 As shown, a plurality of fairing holes 11 are provided through the top wall of the fairing 1 , and the plurality of fairing holes 11 are evenly distributed on the top surface of the fairing 1 .

[0080] The circumferential wall of the fairing 1 is also provided with a plurality of fairing holes 11 passing through it. The plurality of fairing holes 11 on the circumferential wall are arranged in a plurality of rows spaced apart along the axial direction of the fairing 1 , and each row is provided with a plurality of fairing holes 11 spaced apart along the circumference of the fairing 1 .

[0081] This ensures that the fairing 1 has a rectifying effect on the incoming gas flow, thereby ensuring the flow stability of the incoming gas flow, thereby ensuring the flame stability generated by the burner nozzle.

[0082] The rectifying hole 11 can be a round hole, a square hole, a waist-shaped hole, etc.

[0083] In some embodiments, the burner nozzle of the embodiment of the present invention also includes a cylindrical base 3, which is connected to the end of the swirler 2 away from the swirler 2, and the inner cavity of the base 3 is connected to the swirler 2. The base 3 is provided with a plurality of cooling holes 31 arranged at intervals along the circumferential direction, and the cooling holes 31 are connected to the inner cavity of the base 3.

[0084] like Figure 1-Figure 3 As shown, the circumferential wall surface of the fairing 1, the outer shell 23 and the base 3 are all cylindrical around the vertical direction and are sequentially connected in the vertical direction. The inner cavity of the base 3 is connected to the outlet end of the cyclone 2 to receive the mixed gas discharged by the cyclone 2. The base 3 is provided with a plurality of cooling holes 31 arranged at intervals along its circumference. The cooling holes 31 penetrate the wall surface of the base 3 and are connected to the inner cavity of the base 3.

[0085] The base 3 is used to be connected to a device on which a burner nozzle is to be installed so as to fix the burner nozzle, and the cooling hole 31 is used to reduce the temperature of the base 3 .

[0086] In some embodiments, the burner nozzle of the embodiment of the present invention also includes a first sealing ring 4 and a second sealing ring 5, the fairing 1 is provided with a first flange portion 12, the swirler 2 is provided with a second flange portion 24 and a third flange portion 25, the base 3 is provided with a fourth flange portion 32, the first flange portion 12 is connected to the second flange portion 24, and a first sealing ring 4 is provided between the first flange portion 12 and the second flange portion 24, the third flange portion 25 is connected to the fourth flange portion 32, and a second sealing ring 5 is provided between the third flange portion 25 and the fourth flange portion 32.

[0087] like Figure 1 , Figure 3-Figure 5 As shown, the bottom end of the fairing 1 is provided with a first flange portion 12 , the top end of the cyclone 2 is provided with a second flange portion 24 , the bottom end of the cyclone 2 is provided with a third flange portion 25 , and the top end of the base 3 is provided with a fourth flange portion 32 .

[0088] The first flange 12 and the second flange 24 are connected by a connecting member such as a bolt, so as to connect the bottom end of the fairing 1 with the top end of the cyclone 2. A first sealing ring 4 is provided between the first flange 12 and the second flange 24. The fairing 1 and the cyclone 2 are sealed and connected by the first sealing ring 4 to prevent gas leakage. Preferably, the bottom surface of the first flange 12 is provided with a first sealing groove for embedding the first sealing ring 4, such as Figure 4 shown.

[0089] The third flange 25 and the fourth flange 32 are connected by a connecting member such as a bolt, so as to connect the bottom end of the cyclone 2 with the top end of the base 3. A second sealing ring 5 is provided between the third flange 25 and the fourth flange 32. The cyclone 2 and the base 3 are sealed by the second sealing ring 5 to prevent gas leakage. Preferably, the top surface of the fourth flange 32 is provided with a second sealing groove for embedding the second sealing ring 5, such as Figure 5 shown.

[0090] It is understood that the fairing 1, the cyclone 2 and the base 3 are not limited to the Figure 1 connected in the manner shown, as shown in Figure 2 In the example shown, the fairing 1, the cyclone 2 and the base 3 are integrally connected.

[0091] In some embodiments, Figure 1 and Figure 3As shown, the outer circumference of the shell 23 is provided with a boss, and the fuel inlet 231 is provided on the boss, so that the shell 23 has a thin wall thickness and weight, and ensures that the fuel inlet 231 can be connected to the fuel supply component. Preferably, the end surface of the boss facing away from the shell 23 is flush with the outer circumference of the third flange portion 25.

[0092] It is understood that the fuel inlet 231 is not limited to being disposed on the boss. Figure 2 In the example shown, the outer circumferences of the fairing 1 , the outer circumferences of the housing 23 , and the outer circumferences of the base 3 are flush, and the fuel inlet 231 is provided on the outer circumference of the housing 23 .

[0093] like Figure 1-Figure 11 As shown, the axially staged combustor according to the embodiment of the present invention includes a first-stage fuel nozzle and a second-stage fuel nozzle.

[0094] The second-stage fuel nozzle is a burner nozzle according to an embodiment of the present invention.

[0095] The axially staged burner of the embodiment of the present invention, the second-stage fuel nozzle adopts the burner nozzle of the embodiment of the present invention, so as to have a stable combustion effect and be easy to assemble and maintain. In addition, it avoids direct contact with the mainstream fuel gas to prevent high temperature and thermal acoustic problems.

[0096] In some embodiments, the axially staged burner of the embodiment of the present invention further includes a flame tube 6 , and the burner nozzle includes a cylindrical base 3 , which is connected to the flame tube 6 .

[0097] like Figure 1-Figure 3 As shown, the bottom of the base 3 is connected to the flame tube 6, preferably but not limited to an integral connection, so as to integrate the burner nozzle inside the combustion cylinder. The flame tube 6 shown in the figure is a part of the flame tube 6.

[0098] The side of the flame tube 6 with the burner nozzle is a compressed air area, and the side of the flame tube 6 away from the burner nozzle is a high-temperature gas area. The cooling holes 31 on the base 3 are used to reduce the temperature of the base 3 to prevent the base 3 from being overheated by the heat emitted by the high-temperature gas area.

[0099] In the description of the present invention, it is necessary to understand that the terms "center", "up", "down", "vertical", "horizontal", "top", "bottom", "inside", "outside", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to 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 invention.

[0100] In addition, the terms "first" and "second" are only used for distinction, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0101] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0102] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0103] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0104] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A burner nozzle, characterized in that: include: A fairing (1) and a swirler (2) are connected, wherein the fairing (1) is provided with a fairing hole (11), and the swirler (2) comprises a central shaft (21), blades (22) and a shell (23), wherein the outer periphery of the central shaft (21) is provided with a plurality of blades (22) arranged at intervals, wherein the central shaft (21) is provided with a first fuel channel (211), wherein the interior of the blades (22) is provided with a second fuel channel (221), wherein the wall surface of the blades (22) is provided with a fuel outlet (222), wherein the second fuel channel (221) connects the first fuel channel (211) with the fuel outlet (222), wherein the shell (23) is connected to the outer periphery of the plurality of blades (22) and is provided with a fuel inlet (231), wherein at least some of the blades (22) are further provided with a third fuel channel (223), wherein the third fuel channel (223) connects the fuel inlet (231) with the second fuel channel (221).

2. The burner nozzle according to claim 1, characterized in that The blade (22) has a first wall surface (224) and a second wall surface (225) which are arranged opposite to each other in the circumferential direction of the central axis (21); the first wall surface (224) and the second wall surface (225) of each blade (22) are provided with the fuel outlet (222); or, the first wall surface (224) of each blade (22) is provided with the fuel outlet (222); or, the second wall surface (225) of each blade (22) is provided with the fuel outlet (222).

3. The burner nozzle according to claim 1, characterized in that The second fuel channel (221) extends radially along the central axis (21); a wall surface of the blade (22) is provided with a plurality of fuel outlets (222); and the plurality of fuel outlets (222) are arranged at intervals along the second fuel channel (221).

4. The burner nozzle according to claim 1, characterized in that The blade (22) is provided with at least two second fuel channels (221), and the at least two second fuel channels (221) are arranged at intervals along the axial direction of the central axis (21).

5. The burner nozzle according to claim 1, characterized in that A conical first protrusion (212) is provided at one end of the central axis (21) facing the fairing (1), and the first protrusion (212) extends into the fairing (1).

6. The burner nozzle according to claim 1, characterized in that A circular second protrusion (213) is provided at the other end of the central axis (21) away from the fairing (1).

7. The burner nozzle according to claim 6, characterized in that The second protrusion (213) is provided with a fuel nozzle (214), and the fuel nozzle (214) is communicated with the first fuel channel (211).

8. The burner nozzle according to claim 1, characterized in that The axial wall surface and the circumferential wall surface of the fairing (1) are both provided with fairing holes (11).

9. The burner nozzle according to claim 1, characterized in that The invention also comprises a cylindrical base (3), wherein the base (3) is connected to one end of the cyclone (2) facing away from the cyclone (2), and the inner cavity of the base (3) is communicated with the cyclone (2), and the base (3) is provided with a plurality of cooling holes (31) arranged at intervals along the circumferential direction, and the cooling holes (31) are communicated with the inner cavity of the base (3).

10. The burner nozzle according to claim 9, characterized in that The invention also comprises a first sealing ring (4) and a second sealing ring (5), wherein the fairing (1) is provided with a first flange portion (12), the cyclone (2) is provided with a second flange portion (24) and a third flange portion (25), the base (3) is provided with a fourth flange portion (32), the first flange portion (12) is connected to the second flange portion (24), and the first sealing ring (4) is provided between the first flange portion (12) and the second flange portion (24), the third flange portion (25) is connected to the fourth flange portion (32), and the second sealing ring (5) is provided between the third flange portion (25) and the fourth flange portion (32).

11. An axially staged burner, characterized in that: include: The first-stage fuel nozzle and the second-stage fuel nozzle, wherein the second-stage fuel nozzle is a burner nozzle according to any one of claims 1-10.

12. The axially staged combustor according to claim 11, characterized in that: It also comprises a flame tube (6), wherein the burner nozzle comprises a cylindrical base (3), and the base (3) is connected to the flame tube (6).

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