A gas turbine and its nozzle

Abstract

This application discloses a gas turbine and its nozzle, relating to the field of nozzle technology. The nozzle includes an end cap; a first fuel injector disposed on the end cap, the first fuel injector including a first flow channel and a second flow channel, and a plurality of first nozzle holes at the end of the first fuel injector, each of which communicates with the first flow channel; and a plurality of second fuel injectors disposed on the end cap, the second fuel injectors being evenly distributed around the first fuel injector. Through the arrangement of the first and second fuel injectors, this application allows for diffusion combustion of fuel ejected from the first fuel injector and premixed combustion of fuel ejected from the second fuel injectors. During the entire combustion process, the flowing air can only disturb the diffusion combustion flame, but cannot disturb the premixed combustion flame, thus effectively avoiding ignition difficulties or unstable combustion during gas turbine startup or at low operating conditions.

Description

Technical Field

[0001] This application relates to the field of nozzle technology, specifically a gas turbine and its nozzle. Background Technology

[0002] A gas turbine is a thermal engine that uses a continuously flowing gas as the working fluid to drive a turbine at high speed, converting the thermal energy of fuel into mechanical work. Currently, with increasing environmental awareness, compliance with pollutant emission standards has become a prerequisite for gas turbines to enter the market. To reduce emissions of pollutants such as nitrogen oxides (NOx), most mainstream gas turbines employ lean combustion technology. Lean combustion refers to a clean combustion technology where the fuel in the air-fuel mixture is lower than the normal stoichiometric ratio, effectively reducing emissions of nitrogen oxides, hydrocarbons, and carbon monoxide. Because of the low fuel content in the air-fuel mixture during lean combustion, the flame is extremely sensitive to flow disturbances, often making ignition and stable combustion difficult during gas turbine startup or under low operating conditions. Summary of the Invention

[0003] The purpose of this application is to provide a gas turbine and its nozzle to solve the technical problem of unstable combustion in lean premixed combustion of gas turbines in the prior art.

[0004] To achieve the above objectives, this application provides the following technical solution:

[0005] In a first aspect, this application proposes a nozzle comprising an end cap; a first fuel injector disposed on the end cap, the first fuel injector including a first flow channel and a second flow channel, the end of the first fuel injector having a plurality of first nozzle holes, each of the first nozzle holes communicating with the first flow channel; a plurality of second fuel injectors disposed on the end cap, each of the second fuel injectors being evenly distributed around the first fuel injector, each of the second fuel injectors having a plurality of second nozzle holes, the length of each of the second fuel injectors being less than the length of the first fuel injector; and a first feed pipe disposed on the end cap, the first feed pipe communicating with the first flow channel and also communicating with each of the second fuel injectors.

[0006] As one embodiment of this application, the first fuel injector bar also includes a third flow channel, and the end of the first fuel injector bar is also provided with a plurality of third injection holes, each of which is connected to the third flow channel; the end cap is also provided with a second feed pipe, which is connected to the third flow channel.

[0007] As one embodiment of this application, the angle between the centerline of each third nozzle and the centerline of the first fuel injector is greater than or equal to 20° and less than or equal to 60°.

[0008] As one embodiment of this application, it further includes: a plurality of third fuel injectors disposed on the end cap, each third fuel injector being evenly distributed around the first fuel injector, and the length of each third fuel injector being less than the length of the first fuel injector; each third fuel injector being provided with a plurality of fourth nozzles; each fourth nozzle being evenly distributed around the axis of the corresponding third fuel injector; and a third feed pipe disposed on the end cap, the third feed pipe being connected to each third fuel injector.

[0009] As one embodiment of this application, along the radial direction of the first fuel injector, the distance between each third fuel injector and the first fuel injector is greater than the distance between each second fuel injector and the first fuel injector.

[0010] As one embodiment of this application, the end of the first fuel injector bar further includes a swirling fan blade, which is used to cause the air in the second flow channel to form a swirling flow.

[0011] As one embodiment of this application, the axis of each second nozzle is perpendicular to the axis of the first fuel injector; the axis of each fourth nozzle is perpendicular to the axis of the first fuel injector.

[0012] As one embodiment of this application, the first fuel injector includes a first fuel pipe, a second fuel pipe, and a third fuel pipe that are sequentially sleeved from the outside to the inside; a first flow channel is formed inside the third fuel pipe; a second flow channel is formed between the second fuel pipe and the third fuel pipe; and a third flow channel is formed between the first fuel pipe and the second fuel pipe.

[0013] As one embodiment of this application, the first fuel pipe includes an air intake notch for allowing air from inside the combustion chamber to enter the second flow channel.

[0014] In a second aspect, this application proposes a gas turbine including a nozzle as described in any of the first aspects.

[0015] Compared with the prior art, the beneficial effects of this application are:

[0016] By setting up a first fuel injector and a second fuel injector, the fuel injected from the first fuel injector undergoes diffusion combustion, while the fuel injected from the second fuel injector undergoes premixed combustion. Throughout the combustion process, the flowing air can only disturb the flame of diffusion combustion, but cannot disturb the flame of premixed combustion. This effectively avoids the occurrence of ignition difficulties or unstable combustion when the gas turbine starts up or is under low operating conditions. Attached Figure Description

[0017] Figure 1 This is a perspective view of the nozzle proposed in the embodiments of this application;

[0018] Figure 2 This is a cross-sectional view of the nozzle proposed in the embodiment of this application;

[0019] Figure 3 for Figure 2 Enlarged view of section E in the middle;

[0020] Figure 4 This is a cross-sectional view of an embodiment of this application without the second and third fuel injectors.

[0021] Figure 5 This is a perspective view of an embodiment of this application with the second and third fuel injectors removed.

[0022] Figure 6 for Figure 5 Enlarged view of section G in the middle;

[0023] Figure 7 This is a schematic diagram of the nozzle installation in the combustion chamber according to an embodiment of this application.

[0024] In the diagram: 1. End cap; 2. Third fuel injector; 21. Fourth nozzle; 3. Second fuel injector; 31. Second nozzle; 4. First fuel injector; 41. First fuel pipe; 42. Second fuel pipe; 43. Third fuel pipe; 44. Third flow channel; 45. Second flow channel; 46. First flow channel; 47. Inlet notch; 48. Third nozzle; 49. First nozzle; 5. Third feed pipe; 6. Second feed pipe; 7. First feed pipe; 8. Swirl fan blade; 9. Combustion chamber. Detailed Implementation

[0025] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] It should be noted that in the description of this application, the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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. Therefore, they should not be construed as limitations on this application.

[0027] Furthermore, it should be understood that, for ease of description, the dimensions of the various components shown in the accompanying drawings are not drawn to actual scale; for example, the thickness or width of some layers may be exaggerated relative to other layers.

[0028] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined or described in one figure, it will not need to be discussed or described in detail in the description of the subsequent figures.

[0029] Before understanding this application, it is important to understand that lean combustion refers to controlling the proportion of fuel in the fuel-air mixture during combustion, generally below the stoichiometric ratio of fuel combustion, thereby controlling the flame temperature and reducing pollutants generated during combustion. Specifically, combustion is divided into premixed combustion and diffusion combustion. Premixed combustion refers to the combustible gas being mixed in a specific area after being ejected from the nozzle before entering the flame zone for combustion. Diffusion combustion, on the other hand, refers to the combustible gas burning immediately after being ejected from the nozzle; that is, diffusion combustion involves mixing and combustion simultaneously. During diffusion combustion or premixed combustion, if the air velocity or the combustible gas velocity is too high, it will disrupt the combustion balance, leading to flame extinguishing. In other words, when combustible gas and air are separately introduced into the combustion chamber for diffusion combustion or premixed combustion, if the combustible gas ejection velocity is too high (i.e., the air velocity is too slow) or the combustible gas ejection velocity is too low (i.e., the air velocity is too fast), flame extinguishing may occur.

[0030] Specifically, during the operation of a gas turbine, the combustion chamber needs to supply a corresponding amount of fuel under different operating conditions; that is, the nozzles need to inject a corresponding amount of fuel. If the gas turbine is under low operating conditions, the fuel injection rate is small; if the gas turbine is under high operating conditions, the fuel injection rate is large.

[0031] It's important to understand that the fuel injection rate depends on the cross-sectional area of ​​the nozzle and the fuel injection velocity. Normally, the nozzle cross-sectional area is fixed, meaning the fuel injection rate can only be controlled by adjusting the fuel injection velocity. Specifically, during nozzle design, the nozzle cross-sectional area must consider not only the gas turbine's ignition and low-temperature stability but also the full-load fuel flow rate. If the nozzle cross-sectional area is too small, the gas velocity will be too high when the gas turbine is under high operating conditions, potentially causing rich-fuel flameout or flame backlash damaging turbine components. If the nozzle cross-sectional area is too large, the injection velocity cannot be established for combustion when the gas turbine is under low operating conditions, potentially leading to ignition failure or flameout, i.e., poor combustion stability. As mentioned earlier, if the combustion gas injection velocity is too fast or too slow relative to the air injection velocity, it can easily lead to flameout (i.e., unstable combustion). Therefore, if... Figures 1 to 6 As shown, this application proposes a nozzle to solve the above-mentioned technical problems.

[0032] like Figures 1 to 6 As shown, in order to solve the above-mentioned technical problems, this application proposes a nozzle, which includes an end cap 1, a first fuel injection bar 4 disposed on the end cap 1, a plurality of second fuel injection bars 3 and a first feed pipe 7.

[0033] Specifically, the first fuel injector 4 includes a first flow channel 46 and a second flow channel 45. The end of the first fuel injector 4 is provided with multiple first nozzles 49, each of which is connected to the first flow channel 46. The first flow channel 46 is used to transport fuel, while the second flow channel 45 is used for air circulation. Fuel ejected from the first nozzles 49 at the end of the first fuel injector 4 can diffuse and burn with the air ejected from the second flow channel 45. The first nozzles 49 can be evenly distributed around the first fuel injector 4.

[0034] As mentioned above, lean combustion easily leads to combustion instability during the diffusion combustion process of fuel. Therefore, in the embodiments of this application, such as Figure 1 and Figure 2As shown, each second fuel injector 3 can be evenly distributed around the first fuel injector 4, and each second fuel injector 3 can be provided with multiple second nozzles 31. The length of each second fuel injector 3 is less than the length of the first fuel injector 4. It should be clear that in the embodiments of this application, combustion occurs at the end of the first fuel injector 4, and since the length of the second fuel injector 3 is less than the length of the first fuel injector 4, the fuel injected from the second fuel injector 3 needs to flow to the end of the first fuel injector 4 to burn. In other words, the fuel injected from the second fuel injector 3 needs to be mixed with the air in the combustion chamber (i.e., premixed) during its flow before combustion can occur. Compared with diffusion combustion, premixed combustion is less affected by the airflow velocity in the second flow channel 45, thus making the combustion in the combustion chamber more stable and the flame less likely to extinguish.

[0035] It is important to understand that, in the embodiments of this application, the primary purpose of designing the first feed pipe 7 is to deliver fuel to the first flow channel 46 and each of the second fuel injectors 3. Therefore, the first feed pipe 7 is connected to the first flow channel 46 and to each of the second fuel injectors 3. Specifically, the fuel path ejected from the first nozzle 49 is as follows: Figure 2 As shown in route D, a portion of the fuel located in the first feed pipe 7 passes through the first flow channel 46 and is then ejected from the first nozzle 49. The fuel ejected from the second nozzle 31 follows the path shown in the diagram. Figure 2 As shown in route C, another portion of the fuel located in the first feed pipe 7 is ejected through the second fuel injector 3 and then through the second nozzle 31. It is readily understood that, under the same pressure, the amount of fuel ejected from the first nozzle 49 and the second nozzle 31 mainly depends on the cross-sectional area of ​​the nozzles. In the embodiments of this application, the ratio of fuel ejected from the first nozzle 49 and the second nozzle 31 can be controlled by reasonably controlling the cross-sectional areas of the first nozzle 49 and the second nozzle 31, which will not be elaborated further here.

[0036] Specifically, in the embodiments of this application, the end cap 1 mainly serves two functions, such as... Figure 2 As shown, complex flow channels need to be created in end cap 1 to connect the various feed pipes and fuel injectors; for example... Figure 7 As shown, the end cap 1 also needs to seal the combustion chamber 9. Therefore, in the embodiments of this application, the shape of the end cap 1 only needs to match the fuel inlet of the combustion chamber 9, and there are no restrictions on its shape. The internal flow channels can also be designed according to requirements without any limitations.

[0037] As mentioned earlier, during the boost operation of a gas turbine, it is necessary to increase the amount of fuel injected. In existing technology, this is generally achieved by increasing the fuel pressure in the first feed pipe 7 to increase the fuel injection velocity, thereby increasing the fuel quantity. However, this method can easily cause the fuel injection velocity to exceed the air velocity, leading to unstable combustion or flame extinction. Figure 2 and Figure 3 As shown, in one embodiment of this application, to ensure combustion stability, the gas turbine does not need to adjust the fuel injection rate by changing the fuel injection speed during the operating condition upgrade process. The first fuel injector 4 also includes a third flow channel 44. The end of the first fuel injector 4 is provided with multiple third nozzles 48, each of which is connected to the third flow channel 44. The third nozzles 48 are evenly distributed around the axis of the first fuel injector 4. The end cap 1 is also provided with a second feed pipe 6, which is connected to the third flow channel 44. In this embodiment, the third flow channel 44 is also used for fuel delivery, and the fuel flow path in the third flow channel 44 is as follows: Figure 2 As shown in route B, the fuel in the second feed pipe 6 passes through the third flow channel 44 and is then ejected from the third nozzle 48. The arrangement of the second feed pipe 6, the third flow channel 44, and the third nozzle 48 effectively increases the cross-sectional area of ​​the nozzle at the end of the first fuel injector 4. In other words, in the embodiments of this application, it is not necessary to increase the fuel quantity by increasing the fuel injection speed, thus enabling more stable combustion in the combustion chamber.

[0038] It should be clear that the third nozzle 48 is mainly used to increase the fuel quantity; therefore, in the embodiments of this application, there is no need to restrict the position of the third nozzle 48. It can be distributed as needed at the end of the first fuel injection bar 4, or as... Figure 6 The lines are evenly distributed around the axis of the first fuel injector 4.

[0039] It is important to understand that the combustion at the end of the first fuel injector 4 is diffusion combustion. Diffusion combustion produces high-temperature flames with concentrated heat release. To prevent the end of the first fuel injector 4 from being eroded during long-term use, such as... Figure 3 As shown, the angle H formed by the centerline of each third nozzle 48 and the centerline of the first fuel injection rod 4 is greater than or equal to 20° and less than or equal to 60°. Specifically, this angle can be any degree among 20°, 25°, 30°, 35°, 40°, 45°, 50°, 55°, and 60°, or any degree between two adjacent degrees mentioned above. This design allows the fuel to be ejected in a trumpet shape, avoiding concentrated heat release that could burn the end of the first fuel injection rod 4.

[0040] In the embodiments of this application, diffusion combustion involves the fuel burning immediately after being injected from the nozzle, while premixed combustion involves the fuel mixing with air in the combustion chamber after being injected from the nozzle before combustion. It is readily understood that, during full-load operation of a gas turbine, premixed combustion produces fewer pollutants compared to diffusion combustion. Furthermore, in premixed combustion, the better the uniformity of the fuel-air mixture, the fewer pollutants are produced during combustion.

[0041] To reduce the amount of contaminants generated by the nozzle during operation, in a specific embodiment of this application, such as... Figure 1 and Figure 2 As shown, the nozzle also includes a plurality of third fuel injection rods 2 disposed on the end cap 1 and a third feed pipe 5 disposed on the end cap 1. Each third fuel injection rod 2 is evenly distributed around the first fuel injection rod 4, and the length of each third fuel injection rod 2 is less than the length of the first fuel injection rod 4; each third fuel injection rod 2 is provided with a plurality of fourth injection holes 21; each fourth injection hole 21 is evenly distributed around the corresponding third fuel injection rod 2; the third feed pipe 5 is connected to each third fuel injection rod 2.

[0042] It should be clear that, in this embodiment, as Figure 1 and Figure 2 As shown, the length of the third fuel injector 2 is less than the length of the first fuel injector 4, meaning that the combustion of the fuel injected from the third fuel injector 2 is also premixed combustion. By increasing the proportion of fuel used for premixed combustion in the total fuel by using the third fuel injector 2, the pollutants generated during combustion can be effectively reduced.

[0043] In the embodiments of this application, the second nozzle 31 and the fourth nozzle 21 can be opened in any way. For example, the axis of the second nozzle 31 and the fourth nozzle 21 can be parallel to the first fuel injection rod 4, or the axis of the second nozzle 31 and the fourth nozzle 21 can intersect the first fuel injection rod 4.

[0044] In one specific embodiment of this application, in order to ensure that the fuel and air undergoing premixed combustion are uniformly mixed, as... Figure 1 and Figure 2 As shown, the axis of each second nozzle 31 is perpendicular to the axis of the first fuel injection rod 4; the axis of each fourth nozzle 21 is also perpendicular to the axis of the first fuel injection rod 4. In other words, the fuel ejected from the second nozzles 31 and fourth nozzles 21 is perpendicular to the first fuel injection rod 4. Compared to fuel ejected from other directions, fuel ejected perpendicular to the first fuel injection rod 4 can be mixed to the maximum extent along the radial direction of the first fuel injection rod 4, thereby improving the uniformity of fuel-air mixing.

[0045] It should be clear that, in order to further improve the uniformity of fuel-air mixing, in one embodiment of this application, such as... Figure 1 and Figure 2 As shown, along the radial direction of the first fuel injector 4, the distance between each third fuel injector 2 and the first fuel injector 4 is greater than the distance between each second fuel injector 3 and the first fuel injector 4. That is to say, the fuel ejected from the second nozzle 31 and the fourth nozzle 21 can form a counter-current, and the fuel molecules after the counter-current can generate different directions of motion. The fuel molecules with different directions are conducive to uniform mixing with air.

[0046] It is important to understand that, as mentioned above, the combustion occurring at the end of the first fuel injector 4 is diffusion combustion. In diffusion combustion, the fuel mixes with air while burning. To ensure a uniform mixture of air and fuel at the end of the first fuel injector 4, in one embodiment of this application, as follows... Figure 5 and Figure 6 As shown, the end of the first fuel injector 4 also includes a swirl fan blade 8, which is used to create a swirling flow of gas (i.e., air) in the second flow channel 45. After the air forms a swirling flow, it facilitates the uniform diffusion of air and fuel.

[0047] It is readily understood that, in one embodiment of this application, in order to create a swirling flow of fuel from the first nozzle 49 and the third nozzle 48, the first nozzles 49 are arranged in a circumferential array around the axis of the first fuel injection rod 4, and the axis of each first nozzle 49 forms a straight line skewed from the axis of the first fuel injection rod 4. It is important to understand that the fuel ejected from the nozzle moves parallel to the axis of the nozzle. However, the axis of the first nozzle 49 and the axis of the first fuel injection rod 4 form a straight line skewed from each other; that is, the axis of the first nozzle 49 and the axis of the first fuel injection rod 4 are neither parallel nor intersecting. In other words, the fuel ejected from the first nozzle 49 is inclined relative to the first fuel injection rod 4, and since the inclination angle of the fuel ejected from multiple first nozzles 49 is consistent, a swirling flow is formed. For the same reasons mentioned above, each of the third nozzles 48 is arranged in a circular array around the axis of the first fuel injector 4, and the axis of each third nozzle 48 and the axis of the first fuel injector 4 also form a straight line in a different plane.

[0048] It should be clear that, in the embodiments of this application, air can be introduced into the second flow channel 45 in any manner. In one embodiment of this application, a fourth feed pipe (not shown in the figure), similar to the first feed pipe 7, the second feed pipe 6, and the third feed pipe 5, can be provided on the end cap 1. Air can be introduced into the second flow channel 45 through the fourth feed pipe.

[0049] In another embodiment of this application, such as Figure 4 and Figure 5As shown, the first fuel pipe 41 includes an intake notch 47, which allows air from inside the combustion chamber 9 to enter the second flow channel 45. Specifically, the gas turbine operates by burning fuel in the combustion chamber to produce high-temperature gas that performs work on the turbine, thus converting the chemical energy of the fuel into mechanical energy. During the release of the high-temperature gas from the combustion chamber, the gas pressure inside the combustion chamber becomes lower than the gas pressure at the intake notch 47, allowing air from the combustion chamber to enter the second flow channel 45 through the intake notch 47 and exit from the end of the first fuel injector 4. The air flow path is as follows: Figure 4 Route F is shown in the diagram.

[0050] It should be clear that, in the embodiments of this application, the shape and structure of the first flow channel 46, the second flow channel 45, and the third flow channel 44 in the first fuel injector 4 can be adopted in any way without any limitation. For example, the first flow channel 46, the second flow channel 45, and the third flow channel 44 can be curved or straight flow channels.

[0051] To facilitate the fabrication of the first flow channel 46, the second flow channel 45, and the third flow channel 44, in a specific embodiment of this application, such as... Figure 2 and Figure 3 As shown, the first fuel injector 4 includes a first fuel pipe 41, a second fuel pipe 42 and a third fuel pipe 43 that are sequentially connected from the outside to the inside; a first flow channel 46 is formed inside the third fuel pipe 43; a second flow channel 45 is formed between the second fuel pipe 42 and the third fuel pipe 43; and a third flow channel 44 is formed between the first fuel pipe 41 and the second fuel pipe 42.

[0052] The nozzle proposed in this application embodiment, through the setting of a first fuel injection bar and a second fuel injection bar, allows the fuel injected from the first fuel injection bar to undergo diffusion combustion, and the fuel injected from the second fuel injection bar to undergo premixed combustion. During the entire combustion process, the flowing air can only disturb the flame of diffusion combustion, but cannot disturb the flame of premixed combustion. This can effectively avoid the phenomenon of difficult ignition or unstable combustion when the gas turbine starts up or is under low operating conditions.

[0053] After describing all embodiments of the nozzles proposed in this application, a gas turbine proposed in this application is described below, which includes the nozzles as described in any of the above nozzle embodiments.

[0054] like Figure 7 As shown, it is assumed that the combustion chamber 9 of the gas turbine is equipped with the nozzles in the nozzle embodiment proposed in this application.

[0055] When a gas turbine transitions from ignition to idle speed, such as Figure 2As shown, fuel is supplied from the first feed pipe 7, and a portion of the fuel is ejected from the first flow channel 46 and the first nozzle 49 (as shown). Figure 2 In the first fuel injection line 4, diffusion combustion occurs at the end of the first fuel injection bar 4 (route D). That is, the end of the first fuel injection bar 4 includes a combustion zone. Another portion of the fuel entering the first feed pipe 7 is ejected from the second fuel injection bar 3 and the second nozzle 31 (e.g., Figure 2 The air (in route C) mixes with the air outside the second fuel injector 3 and flows to the combustion zone for premixed combustion. Air inside the combustion chamber 9 passes through the intake notch 47 at the bottom of the first fuel injector 4, then through the second flow channel 45 and the swirl fan blades 8 to form a swirling flow before being ejected from the end of the first fuel injector 4 (e.g., ...). Figure 4 Route F in the middle.

[0056] When the gas turbine transitions from idle to 80% operating condition, fuel is supplied to the combustion zone through the second feed pipe 6. The fuel in the second feed pipe 6 undergoes diffusion combustion at the end of the first fuel injector 4 through the third flow channel 44 and the third nozzle 48. This ensures stable combustion of the flame in the combustion zone during the gas turbine's acceleration process.

[0057] When the gas turbine operates from 80% to 100% capacity, part of the fuel is supplied through the first feed pipe 7, and the other part is supplied through the third feed pipe 5. The fuel entering the third feed pipe 5 can be ejected through the fourth nozzle 21 on the third fuel injector 2 (e.g., Figure 2 As shown in route A), the fuel ejected from the fourth nozzle 21 and the second nozzle 31 can be mixed with each other, improving the uniformity of the mixture and reducing combustion pollutants.

[0058] It should be clear that the above-described operating condition adjustment is only one feasible embodiment proposed in this application. In other embodiments of this application, corresponding adjustments can be made according to actual needs. For example, changing the operating condition ratio or changing the selection of the fuel supply channel, which will not be listed here.

[0059] Although embodiments of this application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A nozzle, characterized in that, include: End cap (1); The first fuel injector (4) is provided on the end cap (1). The first fuel injector (4) includes a first flow channel (46) and a second flow channel (45). The end of the first fuel injector (4) is provided with a plurality of first nozzles (49), and each first nozzle (49) is connected to the first flow channel (46). Multiple second fuel injectors (3) are provided on the end cap (1). Each second fuel injector (3) is evenly distributed around the first fuel injector (4). Each second fuel injector (3) is provided with multiple second nozzles (31). The length of each second fuel injector (3) is less than the length of the first fuel injector (4). The first feed pipe (7) is disposed on the end cap (1), the first feed pipe (7) is connected to the first flow channel (46), and the first feed pipe (7) is connected to each of the second fuel injectors (3); The first fuel injector (4) also includes a third flow channel (44), and the end of the first fuel injector (4) is also provided with a plurality of third nozzles (48), each of the third nozzles (48) being connected to the third flow channel (44); the end cap (1) is also provided with a second feed pipe (6), the second feed pipe (6) being connected to the third flow channel (44); The end of the first fuel injector (4) also includes a swirl fan blade (8) for causing the air in the second flow channel (45) to swirl.

2. The nozzle according to claim 1, characterized in that, The angle between the centerline of each third nozzle (48) and the centerline of the first fuel injector (4) is greater than or equal to 20° and less than or equal to 60°.

3. The nozzle according to claim 1 or 2, characterized in that, Also includes: Multiple third fuel injectors (2) are provided on the end cap (1), and each third fuel injector (2) is evenly distributed around the first fuel injector (4). The length of each third fuel injector (2) is less than the length of the first fuel injector (4). Each third fuel injector (2) is provided with multiple fourth nozzles (21). Each fourth nozzle (21) is evenly distributed around the axis of the corresponding third fuel injector (2). The third feed pipe (5) is provided on the end cap (1) and is connected to each third fuel injector (2).

4. The nozzle according to claim 3, characterized in that, Along the radial direction of the first fuel injector (4), the distance between each third fuel injector (2) and the first fuel injector (4) is greater than the distance between each second fuel injector (3) and the first fuel injector (4).

5. The nozzle according to claim 3, characterized in that, The axis of each second nozzle (31) is perpendicular to the axis of the first fuel injector (4); the axis of each fourth nozzle (21) is perpendicular to the axis of the first fuel injector (4).

6. The nozzle according to claim 3, characterized in that, The first fuel injector (4) includes a first fuel pipe (41), a second fuel pipe (42) and a third fuel pipe (43) that are sequentially connected from the outside to the inside; the first flow channel (46) is formed inside the third fuel pipe (43); the second flow channel (45) is formed between the second fuel pipe (42) and the third fuel pipe (43); and the third flow channel (44) is formed between the first fuel pipe (41) and the second fuel pipe (42).

7. The nozzle according to claim 6, characterized in that, The first fuel pipe (41) includes an air intake notch (47) for allowing air from inside the combustion chamber (9) to enter the second flow channel (45).

8. A gas turbine, characterized in that, Includes the nozzle as described in any one of claims 1 to 7.

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