Cooling micromixing nozzle, combustor and gas turbine

Abstract

The application discloses a cooling micro-mixing nozzle, a combustor and a gas turbine. The cooling micro-mixing nozzle comprises a nozzle body, a gas outlet and a plurality of cooling holes are arranged at a gas injection end of the nozzle body, the gas outlet is arranged to spray combustible gas, and the cooling holes are arranged to spray cooling air to cool the gas injection end; a micro-mixing channel, a cooling channel and a cooling cavity are arranged in the nozzle body, the micro-mixing channel is arranged to convey the combustible gas, and an outlet end of the micro-mixing channel is the gas outlet, the cooling channel, the cooling cavity and the cooling holes are sequentially communicated, so that the cooling channel provides the cooling air to the cooling cavity, and the cooling air in the cooling cavity is sprayed from the cooling holes. The scheme provided by the application can effectively protect the gas injection end of the micro-mixing nozzle by the cooling air, and prolong the service life of the micro-mixing nozzle.

Description

Technical Field

[0001] This article relates to the field of gas turbine technology, and in particular to a cooling micro-mixing nozzle, burner and gas turbine. Background Technology

[0002] Gas turbines are one of the important devices for the clean utilization of fossil energy and are widely used in power generation, aviation and industrial power.

[0003] In gas turbines, the combustion gases ejected from micro-mixing nozzles circulate after combustion, with the flame flowing back into the recirculation zone at the jet end, creating a continuous ignition effect. However, while this recirculation improves combustion efficiency, it can also cause thermal damage to the nozzle material. This is especially true when using hydrogen fuel, whose combustion characteristics lead to a significant increase in flame temperature and velocity. The high-temperature combustion gases severely damage the nozzle, resulting in a shorter nozzle lifespan.

[0004] Therefore, how to design an effective cooling air structure to prevent high-temperature gas from damaging the nozzle is a technical problem that needs to be solved. Summary of the Invention

[0005] Embodiments of this application provide a cooling micro-mixing nozzle, burner, and gas turbine to solve the problem of short service life caused by thermal damage to the micro-mixing nozzles currently used in gas turbines.

[0006] This application provides a cooling micro-mixing nozzle for a gas turbine. The cooling micro-mixing nozzle includes a nozzle body, and the jet end of the nozzle body is provided with a gas outlet and a plurality of cooling holes. The gas outlet is configured to inject combustible gas, and the cooling holes are configured to eject cooling air to cool the jet end.

[0007] The nozzle body is provided with a micro-mixing channel, a cooling channel and a cooling chamber. The micro-mixing channel is configured to transport combustible gas and the outlet end of the micro-mixing channel is the gas outlet. The cooling channel, the cooling chamber and the cooling hole are connected in sequence so that the cooling channel provides cooling air to the cooling chamber and the cooling air in the cooling chamber is ejected from the cooling hole.

[0008] In one embodiment, the gas outlet is provided with a plurality of cooling holes, the plurality of cooling holes including a plurality of first cooling holes and a plurality of second cooling holes, the plurality of first cooling holes being arranged on the outer periphery of the plurality of gas outlets, and the plurality of second cooling holes being arranged at the center of the plurality of gas outlets.

[0009] In one embodiment, the nozzle body is further provided with a fuel chamber and a fuel channel for inputting fuel into the fuel chamber. A micro-mixing pipe section having the micro-mixing channel passes through the fuel chamber. The pipe wall of the micro-mixing pipe section is provided with a connecting hole that connects the micro-mixing channel and the fuel chamber. The inlet end of the micro-mixing channel is set as an air inlet so that the fuel entering from the connecting hole and the air entering from the air inlet are mixed in the micro-mixing channel and then sprayed out from the gas outlet.

[0010] In one embodiment, the fuel chamber and the cooling chamber are separated by a partition, the cooling chamber being closer to the jet end than the fuel chamber, and the micro-mixing pipe section passing through the fuel chamber, the partition, and the cooling chamber in sequence.

[0011] In one embodiment, each of the micro-mixing pipe segments is provided with at least one set of connecting holes, and each set of connecting holes includes a plurality of connecting holes arranged at the same height position of the micro-mixing pipe segment and spaced apart in the circumferential direction.

[0012] The injection angle of at least one set of connecting holes is set such that when fuel is injected from the set of connecting holes into the micro-mixing channel, a swirling flow is formed.

[0013] In one embodiment, the cooling channels are provided in multiple ways, and the cooling micro-mixing nozzle further includes at least one baffle. Each baffle is configured to open and close a cooling air inlet of one of the cooling channels, and the flow rate of the cooling air is adjusted by adjusting the number of cooling air inlets opened by the baffle.

[0014] In one embodiment, a plurality of the cooling air inlets are arranged at intervals around the periphery of the micro-mixing channel;

[0015] The cooling micro-mixing nozzle also includes a fixing ring detachably installed on the nozzle body. The fixing ring and the nozzle body form a plurality of receiving grooves corresponding to the cooling air inlets. When the fixing ring is installed on the nozzle body, the baffle is fixed in the receiving groove. The number of openings of the cooling air inlets can be changed by installing different numbers of baffles.

[0016] In one embodiment, the nozzle body is provided with a fuel pipe having the fuel passage, the fuel pipe including an extension section extending into the fuel chamber, so that the gas delivered to the fuel chamber by the fuel passage flows back from bottom to top and enters the connecting hole.

[0017] Embodiments of this application also provide a burner including at least one cooling micro-mixing nozzle as described above.

[0018] Embodiments of this application also provide a gas turbine, including the burner described above.

[0019] The technical solution provided by the embodiments of this application protects the jet end of the nozzle body from corrosion by high-temperature combustion gases by the cooling air ejected from the cooling holes. Furthermore, by setting up cooling channels to first supply cooling air to the cooling chamber, and then redistributing the cooling air within the cooling chamber to each cooling hole, not only is the distribution of cooling air to each cooling hole uniform, but the arrangement of the cooling holes is also more flexible, allowing them to be arbitrarily arranged on the end face of the jet end corresponding to the cooling chamber as needed. Therefore, the solution provided by this application can effectively protect the jet end of the micro-mixing nozzle through cooling air, extending the service life of the micro-mixing nozzle.

[0020] Other features and advantages of this application will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the application. Other advantages of this application can be realized and obtained by means of the embodiments described in the description and the accompanying drawings. Attached Figure Description

[0021] The accompanying drawings are used to provide an understanding of the technical solutions of this application and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of this application and do not constitute a limitation on the technical solutions of this application.

[0022] Figure 1 This is a schematic diagram of the structure of a cooling micro-mixing nozzle according to one embodiment of this application;

[0023] Figure 2 for Figure 1 A schematic diagram of the cooling micro-mixing nozzle viewed from the jet end;

[0024] Figure 3 for Figure 1 A cross-sectional schematic diagram of the cooling micro-mixing nozzle in the image;

[0025] Figure 4 This is a schematic diagram of the micro-mixing pipe segment cut at the connecting hole according to one embodiment of this application;

[0026] Figure 5 This is a schematic diagram of the nozzle body according to one embodiment of the present application;

[0027] Figure 6 This is a schematic diagram of the structure of the fixing ring according to one embodiment of this application.

[0028] Explanation of reference numerals in the attached figures:

[0029] 1- Nozzle body; 11- Cooling channel; 111- Cooling air inlet; 12- Cooling chamber; 13- Cooling hole; 13a- First cooling hole; 13b- Second cooling hole; 14- Micro-mixing channel; 141- Air inlet; 142- Gas outlet; 15- Micro-mixing pipe section; 151- Connecting hole; 16- Fuel channel; 161- Extension pipe section; 162- Connecting pipe section; 17- Fuel chamber; 18- Baffle; 19- Limiting recess; 2- Fixing ring; 21- Groove; 3- Baffle. Detailed Implementation

[0030] This application describes several embodiments, but these descriptions are exemplary and not limiting, and it will be apparent to those skilled in the art that many more embodiments and implementations are possible within the scope of the embodiments described herein. Although many possible combinations of features are shown in the drawings and discussed in the detailed description, many other combinations of the disclosed features are also possible. Unless specifically limited, any feature or element of any embodiment may be used in combination with, or may replace, any feature or element of any other embodiment.

[0031] This application includes and contemplates combinations of features and elements known to those skilled in the art. The embodiments, features, and elements disclosed in this application can also be combined with any conventional features or elements to form unique inventive solutions. Any feature or element of any embodiment can also be combined with features or elements from other inventive solutions to form another unique inventive solution. Therefore, it should be understood that any feature shown and / or discussed in this application can be implemented individually or in any suitable combination. Therefore, the embodiments are not limited except by the limitations imposed by the appended claims and their equivalents. Furthermore, various modifications and changes can be made within the scope of the appended claims.

[0032] Furthermore, in describing representative embodiments, the specification may have presented methods and / or processes as a specific sequence of steps. However, the method or process should not be limited to the specific order of steps described herein, to the extent that it does not depend on such a specific order. As will be understood by those skilled in the art, other sequences of steps are also possible. Therefore, the specific order of steps set forth in the specification should not be construed as a limitation of the claims. Moreover, the claims concerning the method and / or process should not be limited to the steps performed in the written order, and those skilled in the art will readily understand that these orders can be varied and still remain within the spirit and scope of the embodiments of this application.

[0033] Embodiments of this application provide a cooling micro-mixing nozzle for a gas turbine, such as... Figures 1-3 As shown, it includes a nozzle body 1, the jet end of which is provided with a gas outlet 142 and a plurality of cooling holes 13. Figure 2 The nozzle body 1 (showing the jet end) has a gas outlet 142 configured to inject combustible gas, and a cooling hole 13 configured to eject cooling air to cool the jet end.

[0034] The nozzle body 1 is provided with a micro-mixing channel 14, a cooling channel 11 and a cooling chamber 12. The micro-mixing channel 14 is configured to transport combustible gas and the outlet end of the micro-mixing channel 14 is the gas outlet 142. The cooling channel 11, the cooling chamber 12 and the cooling hole 13 are connected in sequence so that the cooling channel 11 provides cooling air to the cooling chamber 12 and the cooling air in the cooling chamber 12 is ejected from the cooling hole 13.

[0035] The technical solution provided by the embodiments of this application is that the cooling air ejected from the cooling hole 13 can protect the jet end of the nozzle body 1 from the corrosion of high-temperature gas. Moreover, by setting the cooling channel 11, the cooling air is first provided to the cooling chamber 12, and then the cooling air in the cooling chamber 12 is redistributed to each cooling hole 13. This not only makes the distribution of cooling air to each cooling hole 13 uniform, but also makes the setting of the cooling hole 13 more flexible. The cooling hole 13 can be arbitrarily arranged on the end face of the jet end corresponding to the cooling chamber 12 as needed.

[0036] Therefore, the solution provided in this application can effectively protect the jet end of the micro-mixing nozzle by cooling air, thereby extending the service life of the micro-mixing nozzle.

[0037] In one embodiment, the gas outlet 142 is provided with a plurality of cooling holes 13, including a plurality of first cooling holes 13a and a plurality of second cooling holes 13b. The plurality of first cooling holes 13a are arranged on the outer periphery of the plurality of gas outlets 142, and the plurality of second cooling holes 13b are arranged at the center of the plurality of gas outlets 142. Figure 2 As shown, a plurality of first cooling holes 13a are arranged at intervals on the outer circumference, and a plurality of second cooling holes 13b are arranged at intervals on the center circumference.

[0038] In this embodiment, multiple first cooling holes 13a located on the outer periphery and multiple second cooling holes 13b located at the center are provided, so that cooling air can be sprayed out from the outer periphery and center of multiple gas outlets 142 respectively, thereby facilitating the formation of a cooling air protective film on the entire jet end and effectively protecting the jet end.

[0039] It is understood that the arrangement of the cooling holes 13 is not limited to the above-mentioned arrangement, and can also be other arrangements. For example, more cooling holes 13 can be set in the high-temperature area of ​​the jet end.

[0040] In one embodiment, such as Figure 3 As shown, the nozzle body 1 is also provided with a fuel chamber 17 and a fuel channel 16 for inputting fuel into the fuel chamber 17. A micro-mixing pipe section 15 with a micro-mixing channel 14 passes through the fuel chamber 17. A connecting hole 151 is provided on the pipe wall of the micro-mixing pipe section 15 to connect the micro-mixing channel 14 and the fuel chamber 17. The inlet end of the micro-mixing channel 14 is set as an air inlet 141. The fuel entering from the connecting hole 151 and the air entering from the air inlet 141 are mixed in the micro-mixing channel 14 and then sprayed out from the gas outlet 142.

[0041] This embodiment, by setting up a fuel chamber 17, allows fuel within the fuel chamber 17 to enter the micro-mixing channel 14 through a connecting hole 151 on the micro-mixing pipe section 15, thereby achieving fuel-air mixing. This mixing method enhances the mixing effect of fuel and air and enables rapid and uniform mixing of fuel and air under high flow rate conditions, significantly improving combustion stability and efficiency, and reducing spontaneous combustion and backfire phenomena caused by uneven fuel concentration. Furthermore, in the high-temperature and high-pressure environment of a gas turbine, a uniform fuel-air mixture can achieve more efficient combustion and reduce harmful NOx emissions.

[0042] exist Figure 3 In the example, the fuel chamber 17 and the cooling chamber 12 are separated by a partition 18. The cooling chamber 12 is closer to the jet end of the nozzle body 1 than the fuel chamber 17. The micro-mixing pipe section 15 passes through the fuel chamber 17, the partition 18, and the cooling chamber 12 in sequence. Since the cooling chamber 12 is closer to the jet end than the fuel chamber 17, the cooling chamber 12 separates the fuel from the high-temperature area of ​​the jet end, which can further improve the protection performance of the nozzle.

[0043] In one embodiment, each micro-mixing pipe section 15 is provided with at least one set of connecting holes 151, and each set of connecting holes 151 includes multiple connecting holes 151 arranged at the same height position and circumferentially spaced on the micro-mixing pipe section 15. Since the fuel at different positions in the fuel chamber 17 may have different pressures, the provision of multiple connecting holes 151 circumferentially spaced on each micro-mixing pipe section 15 allows the fuel in the fuel chamber 17 to enter the micro-mixing pipe section 15 from different directions, which helps to improve the uniformity of fuel entering the multiple micro-mixing channels 14.

[0044] In one example, the injection angle of at least one set of connecting holes 151 is set such that when fuel is injected from the connecting holes 151 into the micro-mixing channel 14, a swirling flow is formed. The swirling flow formed when fuel is injected into the micro-mixing channel 14 can enhance the mixing effect with the air flowing in the micro-mixing channel 14, so that the fuel and the air in the micro-mixing channel 14 are fully mixed.

[0045] like Figures 3-4In the example, each micro-mixing pipe section 15 is provided with a set of connecting holes 151, and each set of connecting holes 151 is provided with four connecting holes 151. The depth direction of each connecting hole 151 (the depth direction determines the injection direction of the hole) is deviated from the radial direction of the micro-mixing pipe section 15. That is, the multiple connecting holes 151 in each set form an approximately spiral arrangement, so that the fluid injected into the micro-mixing channel 14 through the multiple connecting holes 151 can form a swirling flow.

[0046] It is understood that multiple sets of connecting holes 151 can be provided on each micro-mixing pipe section 15, not limited to one set, and each set can be provided with three or five or other numbers of connecting holes 151. In addition, the connecting holes 151 can also adopt other arrangements, not limited to the arrangements described in the above embodiments.

[0047] In one embodiment, the nozzle body 1 is provided with a fuel pipe having the fuel passage 16. The fuel pipe includes an extension section 161 extending into the fuel chamber 17, so that the gas delivered to the fuel chamber 17 by the fuel passage 16 flows back from bottom to top and enters the connecting hole 151. Here, "up" and "down" are defined according to the upstream and downstream directions of the gas delivery direction of the fuel passage 16, and the position located relatively upstream is defined as "up".

[0048] By providing the extension pipe section 161, fuel can be guided to a specific position within the fuel chamber 17. The fuel then flows back from the bottom up at that position within the fuel chamber 17 before re-entering the connecting hole 151. Because the re-flowing fuel is more evenly distributed throughout the fuel chamber 17, the pressure within the fuel chamber 17 becomes uniform, allowing the fuel to be evenly distributed across multiple micro-mixing channels 14, preventing localized rich or lean combustion. The length of the extension pipe section 161 can be set such that it extends a certain distance from the bottom of the fuel chamber 17, or that the outlet of the extension pipe section 161 is more than a certain distance from the connecting hole 151 in the gas delivery direction of the fuel channel 16.

[0049] The fuel line may also include a connecting section 162 connected to the extension section 161, which can be easily connected to a fuel supply device.

[0050] In one embodiment, the cooling channels 11 are provided with multiple channels, and the cooling micro-mixing nozzle further includes at least one baffle 3. Each baffle 3 is configured to open and close a cooling air inlet 111 of one cooling channel 11. By adjusting the number of cooling air inlets 111 open by adjusting the baffle 3, the flow rate of the cooling air can be adjusted. For different combustion conditions, such as when using different fuels, the flow rate of the cooling air can be adjusted to ensure that the cooling effect of the nozzle and the combustion effect are optimally balanced.

[0051] exist Figure 1In the example, multiple air inlets 141 of the multiple micro-mixing channels 14 and cooling air inlets 111 of the multiple cooling channels 11 are located at the same end. An air supply chamber can be provided at this end, and the air in the air supply chamber is simultaneously supplied to the micro-mixing channels 14 and the cooling channels 11. By changing the flow rate of the cooling air entering the cooling channels 11, the flow rate of the air entering the micro-mixing channels 14 can also be changed. Therefore, by precisely controlling the flow rate of cooling air entering the cooling channels, optimal combustion performance can be ensured.

[0052] exist Figures 1-3 In the example, multiple cooling air inlets 111 are spaced apart on the outer periphery of the micro-mixing channel 14. To facilitate the installation of the baffles 3, the cooling micro-mixing nozzle also includes a retaining ring 2 detachably mounted on the nozzle body 1. Multiple receiving grooves corresponding to the cooling air inlets 111 are formed between the retaining ring 2 and the nozzle body 1. When the retaining ring 2 is fixed to the nozzle body 1, the baffles 3 are fixed to the receiving grooves. By installing different numbers of baffles 3, the number of opening cooling air inlets 111 can be changed. To adjust the number of opening cooling air inlets 111, the retaining ring 2 is removed, and the number of installed baffles 3 is adjusted.

[0053] Figure 6 A retaining ring 2 is shown in one embodiment. The retaining ring 2 has a groove 21 on the side facing the nozzle body 1, corresponding to each cooling air inlet 111. When the retaining ring 2 is installed on the nozzle body 1, the groove 21 and the nozzle body 1 together form a receiving groove for the receiving baffle 3. Additionally, to facilitate the positioning of the retaining ring 2 on the nozzle body 1, such as... Figure 5 As shown, the nozzle body 1 is provided with an annular limiting recess 19, which is substantially the same shape as the fixing ring 2, so that the fixing ring 2 can be installed in conjunction with the limiting recess 19. When each baffle 3 is placed between the fixing ring 2 and the nozzle body 1, and the fixing ring 2 is fixed to the nozzle body 1, the baffle 3 can be fixed in the receiving groove between the two. The fixing ring 2 can be fixed to the nozzle body 1 by bolts.

[0054] It is understandable that the baffle 3 can also be installed in other ways, for example, the baffle 3 can be rotatably installed, the cooling air inlet 111 is opened when the baffle 3 is rotated to the first position, and the cooling air inlet 111 is closed when it is rotated to the second position.

[0055] Embodiments of this application also provide a burner including at least one cooling micro-mixing nozzle as described above.

[0056] Embodiments of this application also provide a gas turbine, including the burner described above.

[0057] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0058] Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first," "second," etc., may explicitly or implicitly include at least one of those features.

[0059] In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise expressly and specifically limited.

[0060] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," "fixing," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral part; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0061] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0062] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0063] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A cooling micro-mixing nozzle for a gas turbine, characterized in that, The cooling micro-mixing nozzle includes a nozzle body, and the jet end of the nozzle body is provided with a gas outlet and a plurality of cooling holes. The gas outlet is configured to inject combustible gas, and the cooling holes are configured to eject cooling air to cool the jet end. The nozzle body is provided with a micro-mixing channel, a cooling channel and a cooling chamber. The micro-mixing channel is configured to transport combustible gas and the outlet end of the micro-mixing channel is the gas outlet. The cooling channel, the cooling chamber and the cooling hole are connected in sequence so that the cooling channel provides cooling air to the cooling chamber and the cooling air in the cooling chamber is ejected from the cooling hole. The nozzle body is also provided with a fuel chamber and a fuel channel for inputting fuel into the fuel chamber. A micro-mixing pipe section with the micro-mixing channel passes through the fuel chamber. The pipe wall of the micro-mixing pipe section is provided with a connecting hole that connects the micro-mixing channel and the fuel chamber. The inlet end of the micro-mixing channel is set as an air inlet so that the fuel entering from the connecting hole and the air entering from the air inlet are mixed in the micro-mixing channel and then sprayed out from the gas outlet. The cooling channels are provided in multiple ways, and the cooling micro-mixing nozzle also includes at least one baffle. Each baffle is configured to open and close a cooling air inlet of one of the cooling channels. The flow rate of cooling air is adjusted by adjusting the number of cooling air inlets opened by the baffle. Multiple cooling air inlets are arranged at intervals around the periphery of the micro-mixing channel; The cooling micro-mixing nozzle also includes a fixing ring detachably installed on the nozzle body. The fixing ring and the nozzle body form a plurality of receiving grooves corresponding to the cooling air inlets. When the fixing ring is installed on the nozzle body, the baffle is fixed in the receiving groove. The number of openings of the cooling air inlets can be changed by installing different numbers of baffles.

2. The cooling micro-mixing nozzle according to claim 1, characterized in that, The gas outlet is provided with multiple cooling holes, including multiple first cooling holes and multiple second cooling holes. The multiple first cooling holes are arranged on the outer periphery of the multiple gas outlets, and the multiple second cooling holes are arranged at the center of the multiple gas outlets.

3. The cooling micro-mixing nozzle according to claim 1, characterized in that, The fuel chamber and the cooling chamber are separated by a partition. The cooling chamber is closer to the jet end than the fuel chamber. The micro-mixing pipe section passes through the fuel chamber, the partition and the cooling chamber in sequence.

4. The cooling micro-mixing nozzle according to claim 1, characterized in that, Each of the micro-mixing pipe sections is provided with at least one set of connecting holes, and each set of connecting holes includes multiple connecting holes arranged at the same height position of the micro-mixing pipe section and spaced apart in the circumferential direction. The injection angle of at least one set of connecting holes is set such that when fuel is injected from the set of connecting holes into the micro-mixing channel, a swirling flow is formed.

5. The cooling micro-mixing nozzle according to any one of claims 1-4, characterized in that, The nozzle body is provided with a fuel pipe having the fuel passage. The fuel pipe includes an extension section that extends into the fuel chamber, so that the gas delivered to the fuel chamber by the fuel passage flows back from bottom to top and then enters the connecting hole.

6. A burner, characterized in that, It includes at least one cooling micro-mixing nozzle according to any one of claims 1-5.

7. A gas turbine, characterized in that, Includes the burner according to claim 6.

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