Gas turbine engine and its mixing assembly, combustion chamber, and fuel atomization method therefor

Abstract

This invention relates to a gas turbine engine and a mixer assembly, combustion chamber, and method for atomizing fuel therefor. The mixer assembly for the gas turbine engine includes a pre-combustion stage, a main combustion stage, and an interstage section. The pre-combustion stage includes a first annular chamber and a second annular chamber; the main combustion stage surrounds the pre-combustion stage and includes a third annular chamber; wherein the first annular chamber constitutes a fuel passage for injecting hydrogen-based fuel into the pre-combustion stage outlet, the second annular chamber constitutes an air passage for injecting air mixed with hydrogen-based fuel into the pre-combustion stage outlet, and the third annular chamber constitutes a mixing passage for the main combustion stage, providing another fuel premixed with air to form a mixture that is injected from the main combustion stage outlet, this other fuel being different from the hydrogen-based fuel. This achieves stable combustion with low carbon emissions and low pollution.

Description

Technical Field

[0001] This invention relates to the field of aircraft engines, and more particularly to gas turbine engines and mixer assemblies, combustion chambers, and methods for atomizing fuel therein. Background Technology

[0002] Increased environmental awareness has made reducing pollutant emissions during combustion one of the main challenges in the development of aero engines. Current gas turbine engines use aviation kerosene as fuel, necessitating further reductions in carbon emissions. Summary of the Invention

[0003] The object of this invention is to provide a mixer assembly for a gas turbine engine.

[0004] Another object of the present invention is to provide a burner.

[0005] Another object of the present invention is to provide a gas turbine engine.

[0006] Another object of the present invention is to provide a method for operating a fuel nozzle for a gas turbine engine.

[0007] According to one aspect of the present invention, a mixer assembly for a gas turbine engine includes: a pre-combustion stage, comprising an annular inner wall and an annular outer wall of the pre-combustion stage, the annular outer wall of the pre-combustion stage forming a first annular chamber around at least a portion of the annular inner wall of the pre-combustion stage, and the annular inner wall of the pre-combustion stage forming a second annular chamber; a main combustion stage, the pre-combustion stage being surrounded by the main combustion stage, the main combustion stage including an annular inner wall and an annular outer wall of the main combustion stage, the annular outer wall of the main combustion stage forming a third annular chamber around at least a portion of the annular inner wall of the main combustion stage; and an interstage section having an inner surface. The annular chamber comprises an outer surface, the inner surface forming the annular outer wall of the pre-combustion stage, and the outer surface forming the annular inner wall of the main combustion stage; wherein, the first annular chamber forms a pre-combustion stage fuel passage for injecting hydrogen-based fuel into the outlet of the pre-combustion stage, the second annular chamber forms a pre-combustion stage air passage for injecting air mixed with the hydrogen-based fuel into the outlet of the pre-combustion stage; and the third annular chamber forms a main combustion stage mixing passage for providing another fuel premixed with air to form a mixed fluid that is injected from the outlet of the main combustion stage, the other fuel being different from the hydrogen-based fuel.

[0008] The technical solution of this application employs a first annular chamber and a second annular chamber in the pre-combustion stage to directly inject hydrogen-based fuel and air, respectively, and a third annular chamber in the main combustion stage to premix another fuel with air. The interstage section provides the annular outer wall of the pre-combustion stage and the annular inner wall of the main combustion stage. This structure allows for stable combustion of hydrogen-based fuel in the main combustion stage-pre-combustion stage mixer assembly structure. Furthermore, the mixer assembly using hydrogen-based fuel can flexibly adjust the ratio of the pre-combustion stage flame to the main combustion stage flame to meet different engine operating conditions and emission requirements. Moreover, the mixer assembly of this embodiment requires minimal structural modification compared to the widely used main combustion stage-pre-combustion stage mixer assemblies for conventional fuels. That is, it can achieve rational combustion of hydrogen-based fuel in the combustion chamber with minimal structural modifications based on the combustion chamber structure of conventional fuels such as aviation kerosene, thereby reducing carbon emissions and pollutants with lower development risks and costs. In one or more embodiments of the mixer assembly, the second annular chamber is provided with a second cyclone separator, the third annular chamber is provided with a third cyclone separator, and the number of stages of the second cyclone separator is less than the number of stages of the third cyclone separator.

[0009] In one or more embodiments of the mixer assembly, the axial position of the second cyclone is upstream of the axial position of the third cyclone.

[0010] In one or more embodiments of the mixer assembly, the outlet of the first annular chamber is provided with a partition ring, the partition ring having a plurality of spaced outlets evenly distributed along its circumference for providing an outlet for the injection of the hydrogen-based fuel, with adjacent outlets blocked by baffles to allow the hydrogen-based fuel to be injected from the outlets.

[0011] In one or more embodiments of the mixer assembly, the separator ring has 12-24 outlets evenly distributed circumferentially, the radially inner end of the separator ring is connected to the annular inner wall of the pre-combustion stage, and the radially outer end of the separator ring is connected to the annular outer wall of the pre-combustion stage.

[0012] In one or more embodiments of the mixer assembly, the interstage section is provided with a fuel passage for the other fuel, and the outer surface of the interstage section is provided with a plurality of nozzles corresponding to the fuel passage, the plurality of nozzles being evenly distributed circumferentially, and the axial position of the plurality of nozzles being upstream of the axial position of the third cyclone.

[0013] In one or more embodiments of the mixer assembly, the jetting direction of the nozzles is radial, and the number of the plurality of nozzles is 12-24, which are uniformly distributed circumferentially.

[0014] In one or more embodiments of the mixer assembly described above, the hydrogen-based fuel is gaseous and the other fuel is liquid.

[0015] In one or more embodiments of the mixer assembly, the hydrogen-based fuel is an axial jet, and the other fuel is a spray in the third annular chamber.

[0016] According to another aspect of the present invention, a burner includes: a mixer assembly as described above; a combustion chamber; wherein the mixer assembly is located upstream of and connected to the combustion chamber, the hydrogen-based fuel is directly injected into the combustion chamber from the first annular chamber, the first air is directly injected into the combustion chamber from the second annular chamber, and a mixture formed by premixing the other fuel with the second air flows out into the combustion chamber from the third annular chamber.

[0017] In one or more embodiments of the burner, the wall of the combustion chamber has a cooling channel through which a third air enters the combustion chamber.

[0018] According to another aspect of the present invention, a gas turbine engine includes a burner as described above.

[0019] According to another aspect of the present invention, a method for using a fuel nozzle to operate a gas turbine engine includes: in a pre-combustion stage, directly injecting hydrogen-based fuel from a first annular chamber into a combustion chamber and directly injecting air from a second annular chamber into a combustion chamber; in a main combustion stage, premixing another fuel with air to form a mixed fluid, and then outputting it to the combustion chamber. Attached Figure Description

[0020] The above and other features, properties, and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features. It should be noted that these drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection actually claimed by the present invention, wherein:

[0021] Figure 1 This is a schematic diagram of the structure of a mixer assembly according to one embodiment;

[0022] Figure 2 According to one embodiment Figure 1 A cross-sectional view of the separator ring in the AA direction shown;

[0023] Figure 3 According to one embodiment Figure 1 A cross-sectional view of the mixer assembly in the AA direction shown (separator ring not shown);

[0024] Figure 4This is a schematic diagram of the structure of a burner according to one embodiment. Detailed Implementation

[0025] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0026] In the following description, the terms "upstream," "radial," "axial," "inner," "outer," or other directional terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These are used solely for the convenience of describing the invention and for simplification, and do not indicate or imply that the device or component 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 the invention. Furthermore, upstream and downstream are distinguished based on the direction of fuel or air flow; for example, air flows from upstream to downstream.

[0027] Furthermore, this application uses specific terms to describe its embodiments. For example, "an embodiment" and / or "one embodiment" refers to a particular feature, structure, or characteristic associated with at least one embodiment of this application. Therefore, it should be emphasized and noted that "an embodiment" or "one embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0028] Currently, with increasing demands for reducing carbon emissions, further improvements to gas turbine engines are needed.

[0029] Through in-depth research, the inventors discovered that hydrogen combustion, as one of the most environmentally friendly combustion organization methods currently available, features zero combustion carbon emissions and other combustion pollutants, making it a highly promising low-carbon fuel. However, hydrogen combustion also presents challenges, including difficulties in storage, high transportation costs per unit volume, excessively fast combustion speed, and high flame temperatures. These challenges pose difficulties in rationally organizing combustion within the combustion chamber of aero-engines. Furthermore, due to uncertainties such as development costs and risks associated with pure hydrogen combustion in aero-engines, traditional liquid fuels and sustainable fuels will remain the primary fuels for aero-engines for a considerable period. Therefore, to further reduce carbon emissions while simultaneously reducing traditional pollutant emissions (such as NOx), further research is needed on combustion organization methods based on sustainable fuels and other fuels.

[0030] Based on the above considerations, the inventors, after in-depth research, designed a gas turbine engine mixer assembly. The beneficial effects of the above embodiments are that by using a first annular chamber and a second annular chamber in the pre-combustion stage to directly inject hydrogen-based fuel and air respectively, and using a third annular chamber in the main combustion stage for premixing another fuel with air, and the structure of the interstage section providing the pre-combustion stage annular outer wall and the main combustion stage annular inner wall, the combustion of hydrogen-based fuel can be stably achieved in the main combustion stage-pre-combustion stage mixer assembly structure. This allows the hydrogen-based fuel mixer assembly to also have the advantage of flexibly adjusting the ratio of the pre-combustion stage flame and the main combustion stage flame to meet different engine operating conditions and emission requirements. Furthermore, the mixer assembly of the embodiments requires minimal structural modification compared to the widely used main combustion stage-pre-combustion stage conventional fuel mixer assemblies. That is, it can achieve reasonable combustion of hydrogen-based fuel in the combustion chamber with minimal structural modifications based on the combustion chamber structure of conventional fuels such as aviation kerosene, thereby reducing carbon emissions and pollutants with lower development risks and costs.

[0031] Although the mixer assembly disclosed in the embodiments of this application is applicable to gas turbine engines to achieve the effect of low carbon, low pollution and stable combustion, it is not limited thereto. Any engine can be equipped with the mixer assembly disclosed in the embodiments of this application.

[0032] refer to Figure 1 As shown, in one embodiment, the specific structure of the mixer assembly 100 for a gas turbine engine may include a pre-combustion stage 10, a main combustion stage 20, and an interstage section 30. The pre-combustion stage 10 includes an annular inner wall 11 and an annular outer wall 12. The annular outer wall 12 forms a first annular chamber 101 around at least a portion of the annular inner wall 11, and the annular inner wall 11 forms a second annular chamber 102. The pre-combustion stage 10 is surrounded by the main combustion stage 20, which includes an annular inner wall 21 and an annular outer wall 22. The annular outer wall 22 forms a third annular chamber 203 around at least a portion of the annular inner wall 21. The interstage section 30 has an inner surface 31 and an outer surface 32. The inner surface 31 constitutes the annular outer wall 12 of the pre-combustion stage 10, and the outer surface 32 constitutes the annular inner wall 21 of the main combustion stage 20. The first annular chamber 101 forms a pre-combustion stage fuel passage 103 for injecting hydrogen-based fuel a into the outlet of the pre-combustion stage 10; the second annular chamber 102 forms a pre-combustion stage air passage 104 for injecting air mixed with hydrogen-based fuel a into the outlet of the pre-combustion stage 10; and the third annular chamber 203 forms a main combustion stage mixing passage for providing another fuel b premixed with air to form a mixed fluid that is injected from the outlet of the main combustion stage 20. This other fuel b is different from hydrogen-based fuel a.

[0033] Here, "hydrogen-based fuel a" means that the hydrogen content in the gaseous fuel is greater than or equal to 90%. For example, hydrogen-based fuel a can be pure hydrogen. Hydrogen-based fuel a can be stored in various forms, such as liquid hydrogen, compressed gaseous hydrogen, etc.

[0034] The “other fuel b” here can be traditional aviation kerosene or sustainable alternative fuels, such as those synthesized from vegetable oils, animal fats, etc., or those made from ethanol, methanol, etc., to form carbon-neutral, low-pollution combustion.

[0035] The beneficial effects of the above embodiments are that by using a first annular chamber and a second annular chamber in the pre-combustion stage to directly inject hydrogen-based fuel and air respectively, and using a third annular chamber in the main combustion stage for premixing another fuel with air, and by providing the structure of the pre-combustion stage annular outer wall and the main combustion stage annular inner wall in the interstage section, the combustion of hydrogen-based fuel can be stably achieved in the main combustion stage-pre-combustion stage mixer assembly structure. This allows the hydrogen-based fuel mixer assembly to also have the advantage of flexibly adjusting the ratio of the pre-combustion stage flame and the main combustion stage flame to meet different engine operating conditions and emission requirements. Furthermore, the mixer assembly of the embodiments requires minimal structural modification compared to the widely used main combustion stage-pre-combustion stage conventional fuel mixer assembly. That is, the combustion of hydrogen-based fuel in the combustion chamber can be rationally organized with minimal structural modifications based on the combustion chamber structure of conventional fuels such as aviation kerosene, thereby reducing carbon emissions and pollutants with lower development risks and costs.

[0036] In some embodiments, as Figure 1 As shown, the first annular chamber 101, the second annular chamber 102, and the third annular chamber 203 are coaxially arranged, making the structure more compact, the fuel injection more uniform, and easier to adjust and control.

[0037] In some embodiments, as Figure 1 As shown, the pre-combustion stage annular outer wall 12 surrounds the entire pre-combustion stage annular inner wall 11 to form a first annular chamber 101, and the main combustion stage annular outer wall 22 surrounds the entire main combustion stage annular inner wall 21 to form a third annular chamber 203. The structure is simple and easy to process.

[0038] refer to Figure 1As shown, in some embodiments, the mixer assembly 100 may have the following specific structure: a second annular chamber 102 is provided with a second swirler 1022, and a third annular chamber 203 is provided with a third swirler 2033. The number of stages of the second swirler 1022 is less than the number of stages of the third swirler 2033. By providing a second swirler with a smaller number of stages and a lower swirling number in the pre-combustion stage, the air velocity is relatively slow, allowing the hydrogen-based fuel a to form a longer jet flame, which facilitates diffusion ignition. By providing a third swirler with a larger number of stages and a higher swirling number in the main combustion stage, the air velocity is relatively fast, allowing the other fuel b to mix thoroughly with the air, which facilitates lean combustion and low pollution.

[0039] refer to Figure 4 As shown, in some embodiments, the mixer assembly 100 may be specifically structured such that the axial position of the second swirler 1022 is upstream of the axial position of the third swirler 2033. The advantage of this arrangement is that it allows the hydrogen-based fuel a in the pre-combustion stage to form a longer jet flame, facilitating diffusion ignition, and allows for better mixing of the other fuel b in the main combustion stage with air, facilitating lean, low-pollution combustion.

[0040] refer to Figure 1 Combination Figure 2 As shown, in some embodiments, the specific structure of the first annular chamber 101 may be such that the outlet of the first annular chamber 101 is provided with a partition ring 1011, and the partition ring 1011 has a plurality of spaced outlet portions 1012 evenly distributed along its circumference for providing outlets for the injection of hydrogen-based fuel a. Adjacent outlet portions 1012 are blocked by baffle portions 1013, so that hydrogen-based fuel a is injected from the outlet portions 1012. The beneficial effect of this arrangement is that the injected hydrogen-based fuel a forms a high-speed jet and its velocity distribution in the circumferential direction is more uniform, resulting in stable flame combustion.

[0041] Continue to refer Figure 1 Combination Figure 2 As shown, in some embodiments, the specific structure of the separator ring 1011 may be that it has 12-24 outlets 1012 evenly distributed circumferentially, with the radially inner end 1014 of the separator ring 1011 connected to the annular inner wall 11 of the pre-combustion stage, and the radially outer end 1015 of the separator ring 1011 connected to the annular outer wall 12 of the pre-combustion stage. The beneficial effect of this arrangement is that it can better form a circumferentially uniformly distributed hydrogen-based fuel a jet, resulting in stable flame combustion.

[0042] refer to Figure 1 Combination Figure 3 , Figure 4As shown, in some embodiments, the specific structure of the interstage section 30 may include a fuel passage 301 with the other fuel b, and a plurality of nozzles 302 corresponding to the fuel passage 301 on the outer surface 32 of the interstage section 30. The plurality of nozzles 302 are evenly distributed circumferentially, and the axial position of the plurality of nozzles 302 is located upstream of the axial position of the third cyclone separator 2033. The beneficial effect of this configuration is that it improves the premixing effect between the main combustion stage air and the other fuel b, and the mixed fluid forms a lean combustion flame, reducing the generation of pollutants.

[0043] Continue to refer Figure 1 Combination Figure 3 As shown, in some embodiments, the specific structure of the nozzle 302 can be such that the injection direction of the nozzle 302 is radial, and the number of nozzles 302 is 12-24, evenly distributed circumferentially. The beneficial effect of this arrangement is that the injection direction of the other fuel b forms an angle with the main combustion stage air inlet direction, enhancing the shearing effect of the air on the droplets of the other fuel b spray, making the air and the other fuel b mix more uniformly, and reducing pollutant generation.

[0044] refer to Figures 1 to 4 As shown, in some embodiments, the specific structure of the mixer assembly 100 may be such that hydrogen-based fuel a is in a gaseous state and another fuel b is in a liquid state, thus constituting staged combustion of multiple fuels. This can not only effectively reduce carbon emissions and pollutant products, but also meet the requirements of different engine operating conditions by adjusting the ratio of hydrogen-based fuel a and the other fuel b.

[0045] Continue to refer Figures 1 to 4 As shown, in some embodiments, the mixer assembly 100 may be characterized by a hydrogen-based fuel a being an axial jet, and another fuel b being a spray in the third annular chamber 203. Here, "jet" refers to a stream of fluid ejected from the outlet and mixed with the surrounding fluid to form a single fluid flow, distinct from the spray-like appearance of the other fuel b. The beneficial effect of this arrangement is that it facilitates the formation of a longer flame diffusion combustion in the pre-combustion stage of the hydrogen-based fuel a jet, and allows for more uniform mixing of the other fuel b with air in the main combustion stage, reducing pollutant generation.

[0046] refer to Figure 1 Combination Figure 4As shown, in one embodiment, the burner 1000 may specifically include a mixer assembly 100 and a combustion chamber 200 as described above. The mixer assembly 100 is located upstream of and connected to the combustion chamber 200. Hydrogen-based fuel a is directly injected into the combustion chamber 200 from the first annular chamber 101, and first air c is directly injected into the combustion chamber 200 from the second annular chamber 102. A mixture formed by premixing another fuel b with second air d flows out into the combustion chamber 200 from the third annular chamber 203. The hydrogen-based fuel a and first air c mix to form a zero-carbon emission pre-combustion stage flame, while the other fuel b and second air d are fully premixed to form a lean, low-pollution main combustion stage flame. By flexibly adjusting the ratio of the pre-combustion stage flame to the main combustion stage flame, different engine operating conditions and emission requirements can be met. The resulting multi-fuel flames exhibit different combustion speeds and ignition / quenching characteristics. Typically, hydrogen-based fuel is used as the pre-combustion stage flame for ignition. After the main combustion stage flame is activated, backfire, flameout, and combustion oscillations can be avoided by adjusting the ratio of hydrogen-based fuel to another fuel, resulting in stable, low-carbon, and low-pollution combustion. Furthermore, by using the combustion chamber structure of traditional fuels such as aviation kerosene, the combustion of hydrogen-based fuel within the burner can be rationally organized with minimal modifications, achieving reduced carbon emissions and pollutants with low risk and low development costs.

[0047] refer to Figure 4 As shown, in some embodiments, the combustion chamber 200 may have a cooling channel (not shown in the figure) on its wall, through which the third air e enters the combustion chamber 200. The third air e enters the combustion chamber 200 for combustion, resulting in a simple structure and uniform air distribution, placing the pre-combustion stage flame A in the middle of the combustion chamber 200, with the main combustion stage flame B radially outside the pre-combustion stage flame A.

[0048] refer to Figure 4 As shown, in one embodiment, the specific structure of the gas turbine engine may include the burner 1000 as described above. The advantage of this configuration is that it allows for the efficient combustion of hydrogen-based fuels within the burner with minimal modifications to the combustion chamber structure, building upon traditional fuels such as aviation kerosene. This reduces carbon emissions and pollutants with low risk and low development costs. By forming different fuel flames in the pre-combustion stage and the main combustion stage, the ratio of the pre-combustion stage flame to the main combustion stage flame can be flexibly adjusted to meet different engine operating conditions and emission requirements. Furthermore, it avoids backfire, flameout, and combustion oscillations, resulting in stable, low-carbon, and low-pollution combustion.

[0049] In some embodiments, a method for operating a fuel nozzle in a gas turbine engine includes: in a pre-combustion stage, directly injecting hydrogen-based fuel from a first annular chamber into a combustion chamber and directly injecting air from a second annular chamber into a combustion chamber; in the main combustion stage, premixing another fuel with air to form a mixed fluid, and then outputting it to the combustion chamber. Continuing from the above, as... Figures 1 to 4 As shown, hydrogen-based fuel a enters combustion chamber 200 through a hydrogen-based fuel jet formed by a separator ring 1011 in the first annular chamber 11. First air c enters combustion chamber 200 through a second cyclone separator 1022 located in the second annular chamber 102, mixing with hydrogen-based fuel a to form a zero-carbon emission pre-combustion stage flame A. Another fuel b and second air d are premixed in the third annular chamber 203, further mixed by a third cyclone separator 2033 located in the third annular chamber 203, and then enter combustion chamber 200 to form a lean, low-pollution main combustion stage flame B. Third air e enters combustion chamber 200 through cooling channels on the walls of combustion chamber 200. Pre-combustion stage flame A is located in the middle of combustion chamber 200, and main combustion stage flame B is located radially outside of pre-combustion stage flame A. This method allows for the rational organization of hydrogen-based fuel combustion within the combustion chamber with minimal modifications to the combustion chamber structure, building upon the existing structure of conventional fuels such as aviation kerosene, achieving reduced carbon emissions and pollutants with low risk and low development costs. By forming different fuel flames in the pre-combustion stage and the main combustion stage, the ratio of the pre-combustion stage flame to the main combustion stage flame can be flexibly adjusted to meet different engine operating conditions and emission requirements. It can also avoid phenomena such as backfire, flameout and combustion oscillation, thus forming low-carbon, low-pollution, and stable combustion.

[0050] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A mixer assembly (100) for a gas turbine engine, characterized in that, include: The pre-combustion stage (10) includes an annular inner wall (11) and an annular outer wall (12), wherein the annular outer wall (12) forms a first annular chamber (101) around at least a portion of the annular inner wall (11), and the annular inner wall (11) forms a second annular chamber (102). The main combustion stage (20) is surrounded by the pre-combustion stage (10). The main combustion stage (20) includes an annular inner wall (21) and an annular outer wall (22) of the main combustion stage. The annular outer wall (22) of the main combustion stage forms a third annular chamber (203) around at least a portion of the annular inner wall (21) of the main combustion stage. Interstage section (30), the interstage section (30) having an inner surface (31) and an outer surface (32), the inner surface (31) forming the annular outer wall (12) of the pre-combustion stage (10), and the outer surface (32) forming the annular inner wall (21) of the main combustion stage (20); The first annular chamber (101) constitutes a pre-combustion stage fuel passage (103) for injecting hydrogen-based fuel into the outlet of the pre-combustion stage (10); the second annular chamber (102) constitutes a pre-combustion stage air passage (104) for injecting air mixed with the hydrogen-based fuel into the outlet of the pre-combustion stage (10); and the third annular chamber (203) constitutes a main combustion stage mixing passage for providing another fuel premixed with air to form a mixed fluid that is injected from the outlet of the main combustion stage (20), the other fuel being different from the hydrogen-based fuel.

2. The mixer assembly (100) as claimed in claim 1, characterized in that, The second annular chamber (102) is provided with a second cyclone separator (1022), and the third annular chamber (203) is provided with a third cyclone separator (2033). The number of stages of the second cyclone separator (1022) is less than the number of stages of the third cyclone separator (2033).

3. The mixer assembly (100) as claimed in claim 2, characterized in that, The second hydrocyclone (1022) is located upstream of the third hydrocyclone (2033) in terms of axial position.

4. The mixer assembly (100) as claimed in claim 1, characterized in that, The first annular chamber (101) is provided with a partition ring (1011) at its outlet. The partition ring (1011) has a plurality of spaced outlets (1012) evenly distributed along its circumference to provide an outlet for the hydrogen-based fuel injection. Adjacent outlets (1012) are blocked by baffles (1013) so that the hydrogen-based fuel is injected from the outlets (1012).

5. The mixer assembly (100) as claimed in claim 4, characterized in that, The separator ring (1011) has 12-24 outlets (1012) evenly distributed in the circumferential direction. The radial inner end (1014) of the separator ring (1011) is connected to the annular inner wall (11) of the pre-combustion stage, and the radial outer end (1015) of the separator ring (1011) is connected to the annular outer wall (12) of the pre-combustion stage.

6. The mixer assembly (100) as claimed in claim 2, characterized in that, The interstage section (30) is provided with a fuel passage (301) for the other fuel. The outer surface (32) of the interstage section (30) is provided with a plurality of nozzles (302) corresponding to the fuel passage (301). The plurality of nozzles (302) are evenly distributed in the circumferential direction, and the axial position of the plurality of nozzles (302) is located upstream of the axial position of the third cyclone separator (2033).

7. The mixer assembly (100) as claimed in claim 6, characterized in that, The spray direction of the nozzle (302) is radial, and the number of the plurality of nozzles (302) is 12-24, which are evenly distributed in the circumferential direction.

8. The mixer assembly (100) as claimed in any one of claims 1-7, characterized in that, The hydrogen-based fuel is in a gaseous state, and the other fuel is in a liquid state.

9. The mixer assembly (100) as claimed in claim 8, characterized in that, The hydrogen-based fuel is an axial jet, and the other fuel is a spray in the third annular chamber (203).

10. A burner (1000), characterized in that, include: The mixer assembly (100) as described in any one of claims 1-9; Combustion chamber (200); The mixer assembly (100) is located upstream of the combustion chamber (200) and connected thereto. The hydrogen-based fuel is directly injected into the combustion chamber (200) from the first annular chamber (101), and the first air is directly injected into the combustion chamber (200) from the second annular chamber (102). The mixture formed by the premixing of the other fuel and the second air flows out into the combustion chamber (200) from the third annular chamber (203).

11. The burner (1000) as claimed in claim 10, characterized in that, The combustion chamber (200) has cooling channels on its walls, through which third air enters the combustion chamber (200).

12. A gas turbine engine, characterized in that, Includes the burner (1000) as described in claim 10 or 11.

13. A method for operating a fuel nozzle in a gas turbine engine, characterized in that, include: In the pre-combustion stage, hydrogen-based fuel is directly injected into the combustion chamber from the first annular chamber and air is directly injected into the combustion chamber from the second annular chamber, respectively. In the main combustion stage, another fuel is premixed with air to form a mixed fluid, which is then output to the combustion chamber.

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