Fuel staged burner

Abstract

The invention discloses a fuel staged combustor, and relates to the technical field of structural design of combustion chambers of gas turbines. Comprising a cartridge receiver, a nozzle and a connecting pipe, the cartridge receiver and the nozzle are concentrically arranged, the connecting pipe is arranged between the cartridge receiver and the nozzle, the cartridge receiver is provided with a plurality of classifier cartridge fuel cavities, the outer side of the cartridge receiver is connected with fuel inlet pipes corresponding to the classifier cartridge fuel cavities, the nozzle is composed of a nozzle outer wall and a plurality of nozzle micropipes, and gaps between the nozzle outer wall and the nozzle micropipe walls form nozzle fuel cavities. The nozzle fuel cavity is divided into a plurality of areas, and a plurality of air inlet channels are arranged in the connecting pipe. Fuel enters the classifier box fuel cavity from the fuel inlet pipe, enters different areas of the nozzle fuel cavity through different air inlet channels, is sprayed in from the fuel spraying holes of the nozzle micro-pipe, is mixed with air to form uniform premixed gas, and finally is sprayed out from the micro-pipe outlet. A combustion field with uniform temperature distribution can be formed, meanwhile, the fuel cavities of the grader box can be opened in sequence to form various combined paths, and the combustion mode can be effectively adjusted by adjusting the fuel equivalence ratio of each stage.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine combustion chamber structure design, and in particular to a fuel staged burner. Background Art

[0002] The energy industry has a growing demand for low-carbon emission technology improvements for power station gas turbines. Gas turbines with hydrogen combustion capabilities are the main technical approach, and hydrogen-rich fuels are different from conventional fuels, so the diffusion combustion and premixed combustion technologies commonly used in gas turbine combustors are no longer applicable. Therefore, it is necessary to promote the further development of gas turbine technology by developing new combustion technologies and improving the combustor structure based on the characteristics of hydrogen-rich fuel components.

[0003] At present, micro-premixing is usually used to make the fuel and air burn under more uniform and leaner mixing conditions. Although micro-premixed combustion technology has significant advantages in reducing nitrogen oxide (NOx) emissions and improving combustion efficiency, it also has some disadvantages and challenges. Flashback risk: Hydrogen burns quickly and is prone to flashback. Especially under high-speed flow conditions, flashback problems may lead to combustion instability and safety issues. Combustion instability: Hydrogen flames propagate quickly and are prone to combustion instability, including oscillation and resonance. Uneven mixing: Hydrogen has a low density and weak jet penetration, and is easily swept away by high-speed airflow, resulting in the inability of the injected hydrogen to be fully mixed in the large-flow, high-speed inlet airflow. There is a phenomenon of local fuel concentration and over-richness, which brings about the problem of high local equivalence ratio and high-temperature hot spots, and then generates a large amount of NOx. Therefore, it is necessary to develop a combustion technology with flexible fuel grading so that the burner can achieve low-pollution and stable combustion under all operating conditions of the whole machine.

[0004] The existing patent CN113091094B discloses a method for premixing fuel and air in a nozzle of a gas turbine combustion chamber, wherein the nozzle includes a fuel delivery manifold, a fuel flow channel, and a fuel-air premixing tube. The fuel delivery manifold is provided with a plurality of fuel outlets, and each fuel outlet corresponds to at least one fuel flow channel. There are a plurality of fuel-air premixing tubes, and the fuel-air premixing tube is provided with a fuel spray hole. The fuel enters from the fuel delivery manifold, enters the fuel flow channel through the fuel outlet, enters the fuel-air premixing tube through the fuel spray hole, and mixes with the air pre-entered therein to form a mixture, and the mixture is sprayed out from the fuel-air premixing tube. The nozzle and method can ensure that the entire nozzle has good uniformity of premixing of fuel and air. The disadvantage is that there is only one-level fuel distribution, and it is easy to extinguish or the flame stability is poor under low-load conditions, especially when burning hydrogen fuel. The escape of hydrogen fuel after extinguishing the flame is easy to cause safety accidents.

[0005] The existing patent CN118423714A discloses a gas turbine multi-nozzle array fuel-staged burner head, which is composed of a duty class nozzle, a first-level main combustion nozzle, a second-level main combustion nozzle, a combustion chamber end cooling plate, a duty class fuel distribution cavity, a first-level main combustion fuel distribution cavity and a second-level main combustion fuel distribution cavity. It adopts a fuel-staged and zoned nozzle arrangement to increase the load step by step from the inside to the outside; by controlling the area of ​​the air film holes on the cooling plate at the end of the combustion chamber and the area of ​​the lateral air inlet holes, it is ensured that the speed of the cooling air film holes is lower than the nozzle speed, and the inclined opening of the cooling air film holes does not affect the combustion flame; each level of the fuel pipe has an independent fuel distribution cavity for distribution, which ensures the uniformity of distribution and the flexibility of fuel regulation.

[0006] In summary, the above two existing patents have not fully achieved low-pollution and stable combustion of fuel in the gas turbine combustion chamber. Summary of the invention

[0007] Based on the above technical problems, the present invention proposes a fuel staged burner to solve the problem that the fuel cannot be stably burned with low pollution in the combustion chamber of a gas turbine in the prior art. The specific technical solution is as follows:

[0008] A fuel staged burner comprises an inner nozzle and an outer casing arranged concentrically, and also comprises a plurality of connecting pipes between the nozzle and the casing, the casing has a plurality of staged casing fuel cavities, the outer side of the casing is connected to a plurality of fuel inlet pipes corresponding to the staged casing fuel cavities, the connecting pipe comprises a plurality of air inlet channels, the nozzle comprises a nozzle outer wall and a plurality of nozzle micro-tubes on the inner side of the nozzle outer wall, the gap between the nozzle outer wall and the tube wall of the nozzle micro-tube forms a nozzle fuel cavity, the nozzle fuel cavity is divided into a plurality of zones, and the nozzle micro-tubes are all provided with fuel spray holes.

[0009] Furthermore, the casing includes a plurality of fuel cavity partitions, and the fuel cavity partitions are used to divide the casing fuel cavity into a plurality of graded casing fuel cavities.

[0010] Furthermore, the casing is an annular component, an annular fuel chamber is provided on the casing, and the fuel chamber partition includes a first fuel chamber partition, and the first fuel chamber partition is used to axially divide the annular fuel chamber into a plurality of annular casing fuel chambers.

[0011] Furthermore, the fuel chamber partition also includes a second fuel chamber partition, which is located in the annular casing fuel chamber, and the second fuel chamber partition is used to divide the annular casing fuel chamber into a plurality of graded casing fuel chambers.

[0012] Furthermore, the cavity volume of the graded casing fuel cavity increases step by step.

[0013] Furthermore, one end of the connecting pipe is connected to the inner wall of the annular fuel cavity, and the other end of the connecting pipe is connected to the outer wall of the nozzle.

[0014] Furthermore, a connecting pipe partition is provided in the connecting pipe, and the connecting pipe partition is used to separate the connecting pipe into a plurality of air intake channels, and the plurality of annular casing fuel cavities correspond one-to-one to the plurality of air intake channels.

[0015] Furthermore, the connecting pipe partition is connected to the first fuel chamber partition.

[0016] Furthermore, the nozzle is an annular columnar component, the plurality of nozzle micro-tubes are arranged at equal intervals on the inner side of the nozzle outer wall, and the nozzle micro-tubes are arranged along the axial direction.

[0017] Furthermore, the nozzle micro-tube runs through two end surfaces of the nozzle, the nozzle micro-tube includes a micro-tube inlet and a micro-tube outlet, and the fuel spray hole is opened at one end close to the micro-tube inlet.

[0018] Furthermore, a gap between the outer wall of the nozzle and the wall of the nozzle microtube forms a nozzle fuel chamber, and the nozzle further comprises a plurality of partition plates, and the partition plates are used to partition the nozzle fuel chamber.

[0019] Furthermore, the partition partition includes a first partition partition, and the first partition partition is used to divide the nozzle fuel chamber into a plurality of fan-shaped nozzle fuel chambers along the circumferential direction.

[0020] Furthermore, the partition partition also includes a second partition partition and a third partition partition, the second partition partition and the third partition partition are located in the fan-shaped nozzle fuel chamber, one end of the second partition partition is connected to the side wall of the nozzle, one end of the third partition partition is connected to the end face of the nozzle close to the microtube inlet, and the other end of the second partition partition is vertically connected to the other end of the third partition partition.

[0021] Furthermore, the second partition partition is connected to the connecting pipe partition.

[0022] Furthermore, a convex curved portion is provided on the nozzle micro-tube, and the fuel spray hole is opened on a convex side of the convex curved portion.

[0023] Based on the above technical solution, compared with the prior art, the present invention has at least the following beneficial effects:

[0024] 1. The fuel-graded burner proposed in the present invention is provided with a graded fuel cavity, has multiple load-raising paths, and adjusts the equivalence ratio of different fuel grades, thereby satisfying safe and stable combustion within the full range of operating conditions.

[0025] 2. The present invention proposes a fuel-staged burner, in which the nozzle body is composed of hundreds of micro-tubes to achieve micro-premixed low-pollution combustion. At the same time, the nozzle micro-tubes are divided into multiple zones, which facilitates the implementation of various fuel staged schemes.

[0026] 3. The fuel-staged burner proposed by the present invention divides a single connecting pipe into multiple air inlet channels, which can reduce the number of connecting pipes and interfaces and reduce the impact on the air field.

[0027] 4. The fuel staged burner proposed in the present invention realizes micro-mixing of hydrogen fuel and air, improves the uniformity of fuel and air mixing, avoids excessive local combustion temperature, thereby reducing the emission of nitrogen oxides in the combustion chamber and protecting the environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0029] Figure 1 It is a three-dimensional schematic diagram of a fuel staged burner proposed by the present invention;

[0030] Figure 2 It is a cross-sectional schematic diagram of a fuel staged burner proposed by the present invention;

[0031] Figure 3 It is a cross-sectional schematic diagram of a fuel staged burner proposed by the present invention;

[0032] Figure 4 It is a cross-sectional schematic diagram of a fuel staged burner proposed by the present invention;

[0033] Figure 5 It is a partial structural schematic diagram of a fuel staged burner proposed by the present invention;

[0034] Figure 6 It is a structural schematic diagram of a nozzle micro-tube in a fuel staged burner proposed by the present invention.

[0035] Figure markings: 100-casing; 200-nozzle; 300-connecting pipe; 101-104-fuel inlet pipe; 105-107-fuel chamber partition, 108-1st stage casing fuel chamber; 109-2nd stage casing fuel chamber; 110-3rd stage casing fuel chamber; 111-4th stage casing fuel chamber; 201-nozzle microtube; 202-204-partition partition; 205-nozzle fuel chamber; 206-nozzle fuel chamber; 207-microtube inlet; 208-microtube outlet; 209-fuel spray hole; 301-connecting pipe partition; 302-303-intake channel. DETAILED DESCRIPTION

[0036] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0037] The present invention is further described in detail below in conjunction with specific embodiments. These embodiments should not be construed as limiting the scope of protection claimed by the present invention.

[0038] In order to solve the problem in the prior art that fuel cannot be stably burned with low pollution in the combustion chamber of a gas turbine, the present invention proposes a fuel staged burner.

[0039] To achieve the above object, the present invention provides a fuel staged burner. Figure 1-Figure 6 As shown, a fuel staged burner is specifically exemplified. The fuel staged burner includes a casing 100, a nozzle 200 and a connecting pipe 300, wherein the casing 100 and the nozzle 200 are connected via the connecting pipe 300. A plurality of fuel inlet pipes are connected to the outer side of the casing 100, and the casing 100 is provided with a plurality of staged casing fuel cavities. The nozzle 200 includes a nozzle outer wall and a plurality of nozzle micro-tubes arranged on the inner side of the nozzle outer wall, and a nozzle fuel cavity is formed by a gap between the nozzle outer wall and the nozzle micro-tube wall, and the nozzle fuel cavity is divided into a plurality of zones. The connecting pipe 300 is divided into a plurality of air intake channels. The fuel enters the staged casing fuel cavity from the fuel inlet pipe, and enters different zones of the nozzle fuel cavity through different air intake channels of the connecting pipe.

[0040] The structure of the above-mentioned fuel staged burner is described in detail below.

[0041] In some embodiments, the specific implementation of the casing 100 is shown in Figure 1-Figure 4 shown.

[0042] See also Figure 1 As shown, the casing 100 and the nozzle 200 are arranged concentrically, and the casing 100 is located outside the nozzle 200, and the casing 100 and the nozzle 200 are connected by a plurality of connecting pipes 300. The casing 100 is a thin-walled annular component, on which a raised annular cavity is provided, and the outer side of the annular cavity is connected to the fuel inlet pipes 101-104. The fuel enters the annular cavity through the fuel inlet pipes 101-104, and the annular cavity is the casing fuel cavity.

[0043] See also Figure 2 As shown, a first fuel chamber partition 105 is provided in the casing fuel chamber, and the first fuel chamber partition 105 is an annular partition, which divides the casing fuel chamber into two axially adjacent annular casing fuel chambers. Among them, the right annular casing fuel chamber is connected to the fuel inlet pipe 101 and the fuel inlet pipe 102, and the left annular casing fuel chamber is connected to the fuel inlet pipe 103 and the fuel inlet pipe 104.

[0044] Optionally, the fuel inlet pipe 101 and the fuel inlet pipe 102 are arranged opposite to each other, and the fuel inlet pipe 103 and the fuel inlet pipe 104 are arranged opposite to each other.

[0045] See also Figure 3 As shown, it is a cross-sectional view of the right annular casing fuel chamber. Two second fuel chamber partitions 106 are provided in the right annular casing fuel chamber. The second fuel chamber partitions 106 divide the right annular casing fuel chamber into two arc-shaped graded casing fuel chambers along the circumferential direction, namely, the first-stage casing fuel chamber 108 and the second-stage casing fuel chamber 109.

[0046] Optionally, the cavity volume of the first-stage casing fuel cavity 108 is smaller than the cavity volume of the second-stage casing fuel cavity 109 .

[0047] See also Figure 4 As shown, it is a cross-sectional view of the left annular casing fuel chamber. Two second fuel chamber partitions 107 are provided in the left annular casing fuel chamber. The second fuel chamber partitions 107 divide the left annular casing fuel chamber into two arc-shaped graded casing fuel chambers along the circumferential direction, namely, the third-level casing fuel chamber 110 and the fourth-level casing fuel chamber 111.

[0048] Optionally, the cavity volume of the 3rd-stage casing fuel cavity 110 is smaller than the cavity volume of the 4th-stage casing fuel cavity 111 .

[0049] The classification of the casing fuel cavity of the present invention is not limited to the above-mentioned separation scheme, and can also be divided into more levels of fuel cavities. For example, two first fuel cavity partitions 105 can be provided to separate the casing fuel cavity into three axially adjacent annular casing fuel cavities, and each annular casing fuel cavity is not limited to being divided into two arc-shaped machine brake fuel cavities in the above-mentioned scheme, but can also be divided into multiple arc-shaped casing fuel cavities, and the cavity volumes of the multiple arc-shaped casing fuel cavities increase successively.

[0050] In some embodiments, the specific implementation of the connecting tube 300 is shown in Figure 1 , Figure 2 and Figure 5 shown.

[0051] See also Figure 1 As shown, one end of the connecting pipe 300 is connected to the inner side of the casing fuel cavity of the casing 100, and the other end is connected to the nozzle outer wall of the nozzle 200. The connecting pipe 300 is used to transfer the fuel in the casing fuel cavity to the nozzle 200. At the same time, multiple connecting pipes 300 are evenly distributed in the annular space between the casing 100 and the nozzle 200 to ensure the fixed support installation of the casing 100 and the nozzle 200.

[0052] See also Figure 2 and Figure 5As shown, a connecting tube partition 301 is provided in the connecting tube 300, and the connecting tube partition 301 divides the connecting tube 300 into two air intake channels 302 and 303. At the same time, the connecting tube partition 301 is integrally connected with the first fuel chamber partition 105, so that the air intake channel 302 is connected with the right side annular casing fuel chamber, that is, the fuel in the first-stage casing fuel chamber 108 and the second-stage casing fuel chamber 109 can be transported through the corresponding air intake channel 302 in the connecting tube 300, and the air intake channel 303 is connected with the left side annular casing fuel chamber, that is, the fuel in the third-stage casing fuel chamber 110 and the fourth-stage casing fuel chamber 111 can be transported through the corresponding air intake channel 303 in the connecting tube 300.

[0053] The division of the air intake channel of the connecting pipe 300 of the present invention is not limited to the above scheme, and can be divided into multiple air intake channels by a connecting pipe partition. The number of air intake channels depends on the division of the above-mentioned casing fuel cavity, that is, the casing fuel cavity is divided into several annular casing fuel cavities along the axial direction, and the air intake channels are divided into several.

[0054] In some embodiments, the specific implementation of the nozzle 200 is shown in Figure 1 , Figure 4 , Figure 5 and Figure 6 The nozzle 200 comprises a nozzle outer wall, a plurality of nozzle micro-tubes 201, and a plurality of partition plates 202-204.

[0055] See also Figure 1 As shown, the nozzle 200 is an annular columnar component, and the circular hole in the middle is a through hole, which is convenient for fixing the burner on the main shaft. Multiple nozzle microtubes 201 are arranged at equal intervals and fixed on the inner side of the nozzle outer wall, and the gap between the tube wall of the nozzle microtube 201 and the nozzle outer wall forms a nozzle fuel chamber.

[0056] See also Figure 5 As shown, a plurality of first partition baffles 202 are provided in the nozzle 200. The first partition baffles 202 are radial baffles. The first partition baffles 202 divide the annular cylinder of the nozzle 200 into a plurality of fan-shaped areas along the circumferential direction, that is, the nozzle fuel chamber is also divided into a plurality of areas, and one area is respectively connected to a connecting pipe 300.

[0057] See also Figure 5As shown, a second partition partition 203 and a third partition partition 204 are provided in each sector ring area of ​​the nozzle fuel chamber. The second partition partition 203 is parallel to the end faces of the two ends of the nozzle outer wall, is located at the position where the nozzle 200 is connected to the connecting pipe 300, and one end is connected to the connecting pipe partition 301, and the other end extends radially inward, so as to axially separate the area of ​​each sector ring area of ​​the nozzle fuel chamber close to the nozzle side wall; the plate surface of the third partition partition 204 is perpendicular to the plate surface of the second partition partition 203, one end of the third partition partition 204 is connected to one of the end faces of the nozzle 200, and the other end is connected to the end of the second partition partition 203 extending inward, and the second partition partition 203 and the third partition partition 204 jointly separate each sector ring area of ​​the nozzle fuel chamber into two areas, namely the nozzle fuel chamber 205 and the nozzle fuel chamber 206. In this embodiment, there are a total of 6 sector ring areas, each sector ring area is divided into 2 areas, so the nozzle fuel chamber is divided into 12 areas in total, the air intake channel 302 in the connecting pipe is connected with the corresponding nozzle fuel chamber 205, and the air intake channel 303 is connected with the corresponding nozzle fuel chamber 206.

[0058] The second partition baffle 203 and the third partition baffle 204 only partition the nozzle fuel cavity, and do not partition the interior of the nozzle microtube 201. At the same time, the regional division of the nozzle fuel cavity is not limited to the above scheme, and the first partition baffle 202, the second partition baffle 203 and the third partition baffle 204 are not limited to 6, that is, the circumferential division of the nozzle fuel cavity is not limited to 6 sector annular areas, and the axial division of each sector annular area is not limited to 2, and specific division is required according to actual conditions.

[0059] See also Figure 5 As shown, each nozzle micro-tube 201 penetrates the two end faces of the nozzle outer wall, the micro-tube inlet 207 is located at one end of the nozzle 200 connected to the third partition baffle 204, and the micro-tube outlet 208 is located at the other end face of the nozzle 200. A fuel spray hole 209 is opened on the tube wall of the nozzle micro-tube 201 at one end close to the micro-tube inlet 207. Air enters the nozzle micro-tube 201 from the micro-tube inlet 207, and fuel is sprayed into the nozzle micro-tube 201 from the spray hole 209. The fuel and air are mixed to form a premixed gas, and the premixed gas is discharged from the micro-tube outlet 208. The flow cross-section of the nozzle micro-tube 201 is not limited to a circle, and can be a triangle or an ellipse, etc.

[0060] See also Figure 6 As shown, a bending portion is provided on the nozzle microtube 201, and a fuel spray hole 209 is opened on one side of the bending portion close to the microtube inlet 207. The fuel enters the nozzle microtube 201 through the fuel through hole 209 of the bending portion, and the fuel and air cross jets are mixed to form a premixed gas. The bending portion changes the flow direction of the airflow to form a secondary flow, and the disturbance is enhanced, thereby improving the mixing uniformity of the premixed gas at the microtube outlet 208 and reducing NOx emissions.

[0061] Optionally, the nozzle micro-tube 201 is provided with a plurality of bends, and each bend has a fuel injection hole 209 .

[0062] When the fuel-graded burner proposed in the present invention is working, the fuel enters the corresponding casing fuel chambers 108-111 through the fuel inlet pipes 101-104 on the casing 100, respectively, and the fuel can be divided into 4 levels. Then, the fuel enters the corresponding nozzle fuel chambers through the air inlet channels 302 or 303 in the connecting pipe 300, and the fuel is sprayed into the nozzle microtube 201 from the fuel spray hole 209, and mixed with the air entering from the microtube inlet 207 to form a uniform premixed gas. The premixed gas is sprayed out from the microtube outlet 208, thereby forming a combustion field with uniform temperature distribution to ensure low NOx emissions. At the same time, the graded casing fuel chambers of the present invention can be opened in sequence and enter different areas of the nozzle fuel chamber to form a variety of permutation and combination paths. The fuel-graded burner proposed in the present invention can not only meet the fuel demand of the whole machine under wide load conditions, but also can effectively adjust the combustion mode by flexibly adjusting the fuel equivalence ratio of each level to avoid thermoacoustic oscillation, thereby achieving low-pollution stable combustion under all load conditions of the whole machine.

[0063] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0064] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0065] It should be noted that, in the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means 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 specific features, structures, materials or characteristics described 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, unless they are contradictory.

Claims

1. A fuel staged burner, characterized in that: It includes an inner nozzle and an outer casing which are arranged concentrically, and also includes a plurality of connecting pipes between the nozzle and the casing, the casing has a plurality of graded casing fuel cavities, the outer side of the casing is connected to a plurality of fuel inlet pipes corresponding to the graded casing fuel cavities, the connecting pipes include a plurality of air intake channels, the nozzle includes a nozzle outer wall and a plurality of nozzle micro-tubes on the inner side of the nozzle outer wall, the gap between the nozzle outer wall and the tube wall of the nozzle micro-tube forms a nozzle fuel cavity, the nozzle fuel cavity is divided into a plurality of zones, and the nozzle micro-tubes are all provided with fuel spray holes.

2. The fuel staged burner according to claim 1, characterized in that: The casing includes a plurality of fuel cavity partitions, and the fuel cavity partitions are used to divide the casing fuel cavity into a plurality of graded casing fuel cavities.

3. The fuel staged burner according to claim 2, characterized in that: The casing is an annular component, an annular fuel cavity is arranged on the casing, and the fuel cavity partition includes a first fuel cavity partition, and the first fuel cavity partition is used to divide the annular fuel cavity into a plurality of annular casing fuel cavities along the axial direction.

4. The fuel staged burner according to claim 3, characterized in that: The fuel cavity partition also includes a second fuel cavity partition, which is located in the annular casing fuel cavity and is used to divide the annular casing fuel cavity into a plurality of graded casing fuel cavities.

5. The fuel staged burner according to claim 4, characterized in that: The cavity volume of the graded casing fuel cavity increases step by step.

6. The fuel staged burner according to claim 3, characterized in that: One end of the connecting pipe is connected to the inner wall of the annular fuel cavity, and the other end of the connecting pipe is connected to the outer wall of the nozzle.

7. The fuel staged burner according to claim 6, characterized in that: A connecting pipe partition is provided in the connecting pipe, and the connecting pipe partition is used to divide the connecting pipe into a plurality of air intake channels, and the plurality of annular casing fuel cavities correspond one to one with the plurality of air intake channels.

8. The fuel staged burner according to claim 7, characterized in that: The connecting pipe partition is connected to the first fuel chamber partition.

9. The fuel staged burner according to claim 7, characterized in that: The nozzle is an annular columnar component, and the plurality of nozzle micro-tubes are arranged at equal intervals on the inner side of the outer wall of the nozzle, and the nozzle micro-tubes are arranged along the axial direction.

10. The fuel staged burner according to claim 9, characterized in that: The nozzle micro-tube passes through two end surfaces of the nozzle, the nozzle micro-tube comprises a micro-tube inlet and a micro-tube outlet, and the fuel injection hole is opened at one end close to the micro-tube inlet.

11. The fuel staged burner according to claim 10, characterized in that: A gap between the outer wall of the nozzle and the tube wall of the nozzle microtube forms a nozzle fuel cavity. The nozzle further comprises a plurality of partition plates, and the partition plates are used to partition the nozzle fuel cavity.

12. The fuel staged burner according to claim 11, characterized in that: The partition partition includes a first partition partition, and the first partition partition is used to divide the nozzle fuel cavity into a plurality of fan-shaped nozzle fuel cavities along the circumferential direction.

13. The fuel staged burner according to claim 12, characterized in that: The partition partition also includes a second partition partition and a third partition partition, the second partition partition and the third partition partition are located in the fan-shaped nozzle fuel chamber, one end of the second partition partition is connected to the side wall of the nozzle, one end of the third partition partition is connected to the end face of the nozzle close to the microtube inlet, and the other end of the second partition partition is vertically connected to the other end of the third partition partition.

14. The fuel staged burner according to claim 13, characterized in that: The second partition partition is connected to the connecting pipe partition.

15. The fuel staged burner according to claim 10, characterized in that: The nozzle micro-tube is provided with a convex curved portion, and the fuel spray hole is opened on a convex side of the convex curved portion.

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