A gas turbine axial and radial staged pure hydrogen combustor and method of use

Abstract

The application discloses a kind of gas turbine axial and radial hierarchical pure hydrogen combustor and use method, belong to gas turbine technical field, including combustor main body, on duty fuel pipe, secondary premixed fuel pipe, main premixed fuel pipe, mounting flange, on duty fuel mixing cone, main premixed fuel mixing cone ring, secondary premixed fuel mixing cone ring and metal grid etc.;Combustor main body, mounting flange, on duty fuel pipe center axis alignment, secondary, main premixed fuel pipe is evenly distributed to the outside of on duty fuel pipe, and each fuel pipe end is connected with mixing cone and cone ring corresponding. Mixing cone and cone ring cone surface are provided with corresponding fuel injection hole, and metal grid is arranged at the end of combustor, and inside forms on duty, main premixed, secondary premixed fuel cavity and mixing, air cavity. The present application forms low pressure area on the cone surface by cone body turbulence, effectively solves the problem of low hydrogen injection momentum.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine technology, specifically relating to an axial and radial staged pure hydrogen burner for a gas turbine and its usage method. Background Technology

[0002] In the global transition to a zero-carbon energy structure, gas turbines, as highly efficient energy conversion equipment, are seeing a key focus on upgrading to cleaner fuels. Hydrogen, as an ideal zero-carbon fuel, produces only water vapor as a combustion product, completely eliminating carbon dioxide emissions from the combustion of traditional fossil fuels. A single 30-megawatt pure hydrogen gas turbine can reduce carbon emissions by over 300,000 tons annually. Furthermore, pure hydrogen gas turbines can form a closed-loop system with renewable energy sources such as wind and solar power, encompassing "green electricity to hydrogen production—hydrogen storage—hydrogen power generation," effectively addressing the problem of renewable energy curtailment, improving grid regulation capabilities and power supply stability, and demonstrating broad application prospects in distributed energy, industrial park power supply, and zero-carbon data centers.

[0003] Currently, pure hydrogen combustion in gas turbines mainly employs two technical pathways: diffusion flame combustion and micro-premixed combustion. Diffusion flame combustion systems reduce combustion temperature and control nitrogen oxide emissions by injecting water or nitrogen into the combustion chamber to dilute the flame. However, this technology requires complex water injection and control devices, resulting in a large system size, increased cost, and impact on the unit's cycle thermal efficiency. Micro-premixed combustion technology optimizes the mixing method of fuel and air, allowing them to be fully mixed within a micro-mixing tube. However, the micro-mixing tube has a high flow resistance coefficient, leading to significant pressure loss through the micro-mixer, which also reduces energy utilization efficiency to some extent. Summary of the Invention

[0004] This invention provides an axial and radial staged pure hydrogen burner for gas turbines and a method for using it, with the aim of overcoming the shortcomings of current pure hydrogen combustion in gas turbines.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: An axial and radial staged pure hydrogen burner for a gas turbine includes a burner body, a standby fuel chamber, a main premixed fuel chamber, a secondary premixed fuel chamber, a mixing chamber, a standby fuel pipe, a secondary premixed fuel pipe, a main premixed fuel pipe, an air inlet, a mounting flange, an air chamber, a grid hole, a standby fuel mixing cone, a main premixed fuel mixing cone ring, a secondary premixed fuel mixing cone ring, a standby fuel injection hole, a secondary premixed fuel injection hole, a main premixed fuel injection hole, and a metal grid; The burner body, mounting flange, and standby fuel pipe are arranged aligned along a central axis; the air intake port is located on the cylindrical wall of the burner body near the burner mounting flange; the secondary premixed fuel pipe and the main premixed fuel pipe are evenly arranged circumferentially outside the standby fuel pipe; the end of the standby fuel pipe is connected to the standby fuel mixing cone, the end of the secondary premixed fuel pipe is connected to the secondary premixed fuel mixing cone ring, and the end of the main premixed fuel pipe is connected to the main premixed fuel mixing cone ring; standby fuel injection holes are evenly spaced on the cone surface of the standby fuel mixing cone, secondary premixed fuel injection holes are evenly spaced on the cone surface of the secondary premixed fuel mixing cone ring, and main premixed fuel injection holes are evenly spaced on the cone surface of the main premixed fuel mixing cone ring; a metal grid is arranged at the end of the burner. The standby fuel chamber is located within the standby fuel mixing cone; the main premixed fuel chamber is located within the main premixed fuel mixing cone ring; the secondary premixed fuel chamber is located within the secondary premixed fuel mixing cone ring; the mixing chamber is located inside the burner body, in the mixing space between the metal grid and the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring; the air chamber is located inside the burner body, in the space to the left of the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring; The grid holes are formed by the metal wires of the metal grid.

[0006] A further improvement of the present invention is that the air intake holes are square air intake structures, and the number is 4 to 16.

[0007] A further improvement of the present invention is that the inner diameter of the duty fuel pipe is 15~30 mm.

[0008] A further improvement of the present invention is that the inner diameter of the secondary premixed fuel pipe is 20~40 mm.

[0009] A further improvement of the present invention is that the inner diameter of the main premixed fuel pipe is 25~50 mm.

[0010] A further improvement of the present invention is that the grid holes are square holes.

[0011] A further improvement of the present invention is that the duty fuel injection holes have a diameter of 0.5~1.5 mm and a quantity of 4~16.

[0012] A further improvement of the present invention is that the secondary premixed fuel injection holes, with a diameter of 0.5~1.8 mm, are uniformly distributed on the secondary premixed fuel blending cone ring.

[0013] A further improvement of the present invention is that the main premixed fuel injection holes, with a diameter of 0.5~2.0 mm, are uniformly distributed on the main premixed fuel blending cone ring.

[0014] A method of using an axial and radial staged pure hydrogen burner for a gas turbine includes: Air participating in the combustion of the gas turbine enters the air chamber through air inlets on the burner body. Then, under the action of the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring, the airflow separates at the sharp corner where the bottom and surface of the cone meet. A low-pressure zone is then formed on the cone surface of the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring, which mixes with the fuel injected from the standby fuel injection hole, the secondary premixed fuel injection hole, and the main premixed fuel injection hole, respectively. At the same time, a large number of vortices are generated. The vortices further enhance the deep mixing of fuel and air in the mixing chamber. Finally, the mixture is injected into the combustion chamber through the grid holes on the metal grid for combustion. The standby fuel participating in the gas turbine combustion enters the standby fuel chamber directly through the standby fuel pipe, and is then ejected through the standby fuel injection holes on the standby fuel mixing cone, where it mixes with air in the low-pressure zone formed outside the cone surface. The secondary premixed fuel participating in the gas turbine combustion enters the secondary premixed fuel chamber directly through the secondary premixed fuel pipe, and is then ejected through the secondary premixed fuel injection holes on the secondary premixed fuel mixing cone ring, where it mixes with air in the low-pressure zone formed outside the cone surface. The primary premixed fuel participating in the gas turbine combustion enters the primary premixed fuel chamber directly through the primary premixed fuel pipe, and is then ejected through the primary premixed fuel injection holes on the primary premixed fuel mixing cone ring, where it mixes with air in the low-pressure zone formed outside the cone surface. The mixed fuel-air mixture enters the mixing chamber with a vortex, where it is further mixed, and finally is injected into the combustion chamber through the metal grid at the end of the burner for combustion.

[0015] Compared with the prior art, the present invention has at least the following beneficial technical effects: 1. The cone-shaped turbulence creates a low-pressure zone on the cone surface, effectively solving the inherent problem of low momentum in hydrogen injection. This invention incorporates a cone and cone-ring structure within the burner. As the airflow surrounds the cone surface, a stable low-pressure zone forms in the cone region due to the gradual change in flow area and the fluid flow effect, creating a significant pressure difference with the fuel injection port. Hydrogen fuel does not rely solely on its own momentum for ejection; instead, it is ejected at high speed under suction, fundamentally addressing the problem of insufficient injection penetration caused by the low density and small momentum of hydrogen. This design allows hydrogen fuel to effectively overcome airflow obstruction and diffuse uniformly into the mainstream area of ​​the cone surface, avoiding defects such as hydrogen adhering to the walls, localized enrichment, or insufficient injection range, thus providing a basis for uniform fuel distribution in subsequent combustion.

[0016] 2. The two-stage mixing mode of cone vortex + mixing chamber enhances the uniformity of hydrogen-air mixing, suppresses the formation of local hydrogen-rich zones, and improves combustion stability. This invention constructs a two-stage mixing system—"conical pre-mixing + secondary strong mixing in the mixing cavity"—through the synergistic design of the cone and mixing cavity. In the first stage, the low-pressure zone of the cone achieves initial mixing of hydrogen and air, allowing hydrogen to quickly integrate into the mainstream flow field and preventing local fuel accumulation. In the second stage, the vortex flow field generated by the flow around the cone enters the downstream mixing cavity with the airflow. The shearing and entrainment effects of the vortex further tear and mix the pre-mixed hydrogen and air mixture. Simultaneously, the mixing cavity provides ample space for the development and mixing of the vortex flow field, significantly improving the spatiotemporal uniformity of the mixture. The uniformly mixed combustible gas effectively avoids the formation of local hydrogen-rich zones, solving the problems of intense combustion and large temperature gradients caused by localized hydrogen richness in hydrogen combustion. It also ensures a uniform flame distribution, significantly improving the stability of pure hydrogen combustion and reducing the risk of combustion oscillations.

[0017] 3. Staged fuel injection significantly suppresses NO. x generate The rapid flame propagation and the tendency to form localized high-temperature zones during pure hydrogen combustion lead to the formation of thermal NO. x Addressing a major industry challenge, this invention employs a staged axial and radial fuel injection strategy. This staged fuel injection method abandons the single-nozzle concentrated injection approach, instead using multiple axial and radial nozzles to inject hydrogen fuel into the combustion flow field in zones and stages. This disperses the originally concentrated heat release process across multiple spatial regions, preventing localized temperature spikes on a single flame surface caused by concentrated fuel combustion, thereby effectively suppressing thermal NOx. x Generate, to achieve low emission targets. Attached Figure Description

[0018] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a cross-sectional view of the center of a pure hydrogen burner; Figure 2 Isometric drawing of a pure hydrogen burner; Figure 3 This is a magnified view of a portion of the head of a pure hydrogen burner. Figure 4 This is a magnified view of a portion of the interior of a pure hydrogen burner; Figure 5 This is an isometric view of a pure hydrogen burner.

[0020] Explanation of reference numerals in the attached figures: 1. Burner body; 2. Standby fuel chamber; 3. Main premixed fuel chamber; 4. Secondary premixed fuel chamber; 5. Blending chamber; 6. Standby fuel pipe; 7. Secondary premixed fuel pipe; 8. Main premixed fuel pipe; 9. Air inlet; 10. Mounting flange; 11. Air chamber; 12. Grid hole; 13. Standby fuel blending cone; 14. Main premixed fuel blending cone ring; 15. Secondary premixed fuel blending cone ring; 16. Standby fuel injection hole; 17. Secondary premixed fuel injection hole; 18. Main premixed fuel injection hole; 19. Metal grid. Detailed Implementation

[0021] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of the invention. Therefore, the drawings and description are considered to be exemplary in nature and not restrictive.

[0022] In the description of this invention, 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," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention 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 invention.

[0023] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0024] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a communication connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0025] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0026] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0027] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0028] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0029] The accompanying drawings illustrate various structural schematic diagrams according to embodiments disclosed in this invention. These drawings are not to scale, and some details have been enlarged for clarity, and some details may have been omitted. The shapes of the various regions and layers shown in the drawings, as well as their relative sizes and positional relationships, are merely exemplary and may deviate from reality due to manufacturing tolerances or technical limitations. Furthermore, those skilled in the art can design regions / layers with different shapes, sizes, and relative positions as needed.

[0030] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0031] Example 1 like Figures 1 to 5As shown, the present invention provides an axial and radial staged pure hydrogen burner for a gas turbine, mainly comprising a burner body 1, a standby fuel chamber 2, a main premixed fuel chamber 3, a secondary premixed fuel chamber 4, a mixing chamber 5, a standby fuel pipe 6, a secondary premixed fuel pipe 7, a main premixed fuel pipe 8, an air inlet 9, a mounting flange 10, an air chamber 11, a grid hole 12, a standby fuel mixing cone 13, a main premixed fuel mixing cone ring 14, a secondary premixed fuel mixing cone ring 15, a standby fuel injection hole 16, a secondary premixed fuel injection hole 17, a main premixed fuel injection hole 18, and a metal grid 19, etc.

[0032] The connection relationships between the components are as follows: The burner body 1, mounting flange 10, and standby fuel pipe 6 are arranged aligned along their central axis; the air inlet 9 is located on the cylindrical wall of the burner body 1 near the burner mounting flange 10; the secondary premixed fuel pipe 7 and the main premixed fuel pipe 8 are evenly arranged circumferentially outside the standby fuel pipe 6; the end of the standby fuel pipe 6 is connected to the standby fuel mixing cone 13, the end of the secondary premixed fuel pipe 7 is connected to the secondary premixed fuel mixing cone ring 15, and the end of the main premixed fuel pipe 8 is connected to the main premixed fuel mixing cone ring 14; standby fuel injection holes 16 are evenly spaced on the cone surface of the standby fuel mixing cone 13, secondary premixed fuel injection holes 17 are evenly spaced on the cone surface of the secondary premixed fuel mixing cone ring 15, and the main premixed fuel mixing cone ring 14 is evenly spaced on the cone surface of the main premixed fuel mixing cone ring 14. The main premixed fuel injection holes 18 are evenly spaced on the conical surface of the burner; the metal grid 19 is arranged at the end of the burner; the standby fuel chamber 2 is located inside the standby fuel mixing cone 13; the main premixed fuel chamber 3 is located inside the main premixed fuel mixing cone ring 14; the secondary premixed fuel chamber 4 is located inside the secondary premixed fuel mixing cone ring 15; the mixing chamber 5 is located inside the burner body 1, in the mixing space between the metal grid 19 and the standby fuel mixing cone 13, the main premixed fuel mixing cone ring 14, and the secondary premixed fuel mixing cone ring 15; the air chamber 11 is located inside the burner body 1, in the space to the left of the standby fuel mixing cone 13, the main premixed fuel mixing cone ring 14, and the secondary premixed fuel mixing cone ring 15; the grid holes 12 are separated by the metal wires of the metal grid 19.

[0033] This invention, by incorporating a cone and cone-ring structure within the burner, creates a stable low-pressure zone around the cone surface as the airflow flows. This zone, due to the gradual change in flow area and the fluid flow effect, forms a significant pressure difference with the fuel injection port, causing hydrogen fuel to be ejected at high speed under suction. This compensates for the insufficient penetration caused by the low density and momentum of hydrogen, allowing it to effectively overcome airflow obstruction and diffuse uniformly into the mainstream area of ​​the cone surface. This avoids defects such as hydrogen adhering to the walls, local enrichment, or insufficient injection range, providing a uniform fuel distribution foundation for subsequent combustion. Simultaneously, a two-stage mixing system is constructed: "pre-mixing on the cone surface + secondary strong mixing in the mixing chamber." The low-pressure zone on the cone surface achieves initial mixing of hydrogen and air, allowing hydrogen to quickly integrate into the mainstream flow field, preventing local fuel accumulation. The vortex flow field generated around the cone... As the airflow enters the downstream mixing chamber, the shearing and entrainment effects of the vortex further tear and mix the premixed hydrogen and air. The mixing chamber provides ample space for the development and mixing of the vortex flow field, significantly improving the spatiotemporal uniformity of the mixture, effectively preventing the formation of local hydrogen-rich zones, and solving the problems of intense combustion and large temperature gradients caused by local hydrogen richness in hydrogen combustion. This ensures uniform flame distribution, improves the stability of pure hydrogen combustion, and reduces the risk of combustion oscillation. Furthermore, this invention employs a staged axial and radial fuel injection strategy, abandoning the single-nozzle concentrated injection method. By using multiple axial and radial nozzles, hydrogen fuel is injected into the combustion flow field in regions and stages, dispersing the concentrated combustion heat release process across multiple spatial regions. This avoids sudden temperature rises on a single flame surface due to concentrated fuel combustion, effectively suppressing thermal NO. x Generate, to achieve low emission targets.

[0034] In this embodiment, the air intake holes 9 are square intake structures, and the number of them is 4 to 16. The inner diameter of the standby fuel pipe 6 is 15 to 30 mm. The inner diameter of the secondary premixed fuel pipe 7 is 20 to 40 mm. The inner diameter of the main premixed fuel pipe 8 is 25 to 50 mm. The grid holes 12 are square holes, separated by metal wires of the metal grid 19. The standby fuel injection holes 16 have a diameter of 0.5 to 1.5 mm, and the number of them is 4 to 16. The secondary premixed fuel injection holes 17 have a diameter of 0.5 to 1.8 mm and are evenly distributed on the secondary premixed fuel blending cone ring 15. The main premixed fuel injection holes 18 have a diameter of 0.5 to 2.0 mm and are evenly distributed on the main premixed fuel blending cone ring 14.

[0035] Example 2 like Figures 1 to 5As shown, the present invention provides a method for using an axial and radial staged pure hydrogen burner for a gas turbine, comprising: air participating in the combustion of the gas turbine enters the air chamber 11 through an air inlet 9 opened on the burner body 1; then, under the action of the standby fuel mixing cone 13, the main premixed fuel mixing cone ring 14, and the secondary premixed fuel mixing cone ring 15, the airflow will separate at the sharp corner where the bottom surface and the surface of the cone meet; then, a low-pressure zone is formed at the cone surface of the standby fuel mixing cone 13, the main premixed fuel mixing cone ring 14, and the secondary premixed fuel mixing cone ring 15, which mixes with the fuel injected from the standby fuel injection hole 16, the secondary premixed fuel injection hole 17, and the main premixed fuel injection hole 18, respectively, and generates a large number of vortices. The vortices further enhance the deep mixing of fuel and air in the mixing chamber 5, and finally, the mixture is injected into the combustion chamber for combustion through the grid holes 12 opened on the metal grid 19.

[0036] The standby fuel participating in the gas turbine combustion enters the standby fuel chamber 2 directly through the standby fuel pipe 6, and is then ejected through the standby fuel injection hole 16 on the standby fuel mixing cone 13, where it mixes with air in the low-pressure zone formed outside the cone surface. The secondary premixed fuel participating in the gas turbine combustion enters the secondary premixed fuel chamber 4 directly through the secondary premixed fuel pipe 7, and is then ejected through the secondary premixed fuel injection hole 17 on the secondary premixed fuel mixing cone ring 15, where it mixes with air in the low-pressure zone formed outside the cone surface. The primary premixed fuel participating in the gas turbine combustion enters the primary premixed fuel chamber 3 directly through the primary premixed fuel pipe 8, and is then ejected through the primary premixed fuel injection hole 18 on the primary premixed fuel mixing cone ring 14, where it mixes with air in the low-pressure zone formed outside the cone surface. The mixed fuel-air mixture enters the mixing chamber 5 with a vortex, where it is further mixed, and finally injected into the combustion chamber for combustion through the metal grid 19 at the end of the burner.

[0037] The main innovative points of this invention are as follows: 1. Pneumatically driven fuel injection: Unique "cone turbulence-low-pressure suction" synergistic structure The primary structural innovation of this invention lies in its departure from the traditional approach of overcoming injection resistance by increasing the fuel's own pressure, and instead creatively designing a "cone-cone ring" assembly. Its innovation lies in the active generation of a stable and controllable local low-pressure zone on the conical surface when air flows around this assembly. This low-pressure zone forms a strong pressure difference with the fuel nozzle, converting aerodynamic energy into the driving force for fuel injection, thus efficiently solving the inherent problems of low momentum and poor penetration due to hydrogen's extremely low density. This structure frees fuel injection from its own physical properties, achieving a fundamental shift from "passive ejection" to "active intake," ensuring the uniformity and stability of the initial fuel distribution in the high-speed airflow.

[0038] 2. Spatiotemporally progressive turbulent eddy-enhanced mixing: Constructing a two-stage mixing system of "premixing + vortex enhancement". The core methodological innovation of this invention lies in the design of a spatiotemporally ordered turbulent mixing enhancement system. This system does not rely on a single mixing mechanism, but rather constructs two functionally distinct and coherent stages: the first stage (conical region) utilizes shear vortices generated around the cone to achieve rapid premixing of fuel and air, preventing initial agglomeration; the second stage (mixing chamber) provides ample space for the development of the vortices generated by the cone, utilizing the attenuation, breakup, and energy dissipation processes of the vortices to achieve microscale homogenization of the premixed gas. This two-stage design, separating yet connecting "rapid entrainment" and "refined homogenization," maximizes mixing efficiency and uniformity within a limited scale, representing a key process innovation to ensure stable and mild combustion of highly reactive hydrogen.

[0039] 3. Axial and radial staged fuel injection design This invention employs a multi-point, staged injection strategy combining axial and radial approaches, spatially discretizing the fuel delivery location and timing. This physically disperses the traditionally concentrated and intense exothermic reaction into multiple partitioned and phased, milder reactions. This design effectively avoids localized high-temperature peaks caused by the high flame velocity of hydrogen, fundamentally suppressing the formation pathway of thermal NOx.

[0040] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the scope of the invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0041] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that can be understood by those skilled in the art. The above content is only for illustrating the technical concept of the present invention and should not be construed as limiting the scope of protection of the present invention. Any modifications made based on the technical concept proposed in this invention shall fall within the scope of protection of the claims of this invention.

Claims

1. A gas turbine axial and radial staged pure hydrogen burner, characterized in that, It includes the burner body, standby fuel chamber, main premixed fuel chamber, secondary premixed fuel chamber, blending chamber, standby fuel pipe, secondary premixed fuel pipe, main premixed fuel pipe, air intake port, mounting flange, air chamber, grid hole, standby fuel blending cone, main premixed fuel blending cone ring, secondary premixed fuel blending cone ring, standby fuel injection hole, secondary premixed fuel injection hole, main premixed fuel injection hole and metal grid; The burner body, mounting flange, and standby fuel pipe are arranged aligned along a central axis; the air intake port is located on the cylindrical wall of the burner body near the burner mounting flange; the secondary premixed fuel pipe and the main premixed fuel pipe are evenly arranged circumferentially outside the standby fuel pipe; the end of the standby fuel pipe is connected to the standby fuel mixing cone, the end of the secondary premixed fuel pipe is connected to the secondary premixed fuel mixing cone ring, and the end of the main premixed fuel pipe is connected to the main premixed fuel mixing cone ring; standby fuel injection holes are evenly spaced on the cone surface of the standby fuel mixing cone, secondary premixed fuel injection holes are evenly spaced on the cone surface of the secondary premixed fuel mixing cone ring, and main premixed fuel injection holes are evenly spaced on the cone surface of the main premixed fuel mixing cone ring; a metal grid is arranged at the end of the burner. The standby fuel chamber is located within the standby fuel mixing cone; the main premixed fuel chamber is located within the main premixed fuel mixing cone ring; the secondary premixed fuel chamber is located within the secondary premixed fuel mixing cone ring; the mixing chamber is located inside the burner body, in the mixing space between the metal grid and the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring; the air chamber is located inside the burner body, in the space to the left of the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring; The grid holes are formed by the metal wires of the metal grid.

2. The axial and radial staged pure hydrogen burner for a gas turbine according to claim 1, characterized in that, The air intake vents are square and number 4 to 16.

3. The axial and radial staged pure hydrogen burner for a gas turbine according to claim 1, characterized in that, The inner diameter of the duty fuel pipe is 15~30 mm.

4. The axial and radial staged pure hydrogen burner for a gas turbine according to claim 1, characterized in that, The inner diameter of the secondary premixed fuel pipe is 20~40 mm.

5. A gas turbine axial and radial staged pure hydrogen burner according to claim 1, characterized in that, The inner diameter of the main premixed fuel pipe is 25~50 mm.

6. A gas turbine axial and radial staged pure hydrogen burner according to claim 1, characterized in that, The grid holes are square.

7. A gas turbine axial and radial staged pure hydrogen burner according to claim 1, characterized in that, The duty fuel injection holes have a diameter of 0.5~1.5 mm and a quantity of 4~16.

8. A gas turbine axial and radial staged pure hydrogen burner according to claim 1, characterized in that, The secondary premixed fuel injection holes, with a diameter of 0.5~1.8 mm, are evenly distributed on the secondary premixed fuel blending cone ring.

9. A gas turbine axial and radial staged pure hydrogen burner according to claim 1, characterized in that, The main premixed fuel injection holes, with a diameter of 0.5~2.0 mm, are evenly distributed on the main premixed fuel blending cone ring.

10. A method of using a gas turbine axial and radial staged pure hydrogen burner according to any one of claims 1 to 9, characterized in that, include: Air participating in the combustion of the gas turbine enters the air chamber through air inlets on the burner body. Then, under the action of the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring, the airflow separates at the sharp corner where the bottom and surface of the cone meet. A low-pressure zone is then formed on the cone surface of the standby fuel mixing cone, the main premixed fuel mixing cone ring, and the secondary premixed fuel mixing cone ring, which mixes with the fuel injected from the standby fuel injection hole, the secondary premixed fuel injection hole, and the main premixed fuel injection hole, respectively. At the same time, a large number of vortices are generated. The vortices further enhance the deep mixing of fuel and air in the mixing chamber. Finally, the mixture is injected into the combustion chamber through the grid holes on the metal grid for combustion. The standby fuel participating in the gas turbine combustion enters the standby fuel chamber directly through the standby fuel pipe, and is then ejected through the standby fuel injection holes on the standby fuel mixing cone, where it mixes with air in the low-pressure zone formed outside the cone surface. The secondary premixed fuel participating in the gas turbine combustion enters the secondary premixed fuel chamber directly through the secondary premixed fuel pipe, and is then ejected through the secondary premixed fuel injection holes on the secondary premixed fuel mixing cone ring, where it mixes with air in the low-pressure zone formed outside the cone surface. The primary premixed fuel participating in the gas turbine combustion enters the primary premixed fuel chamber directly through the primary premixed fuel pipe, and is then ejected through the primary premixed fuel injection holes on the primary premixed fuel mixing cone ring, where it mixes with air in the low-pressure zone formed outside the cone surface. The mixed fuel-air mixture enters the mixing chamber with a vortex, where it is further mixed, and finally is injected into the combustion chamber through the metal grid at the end of the burner for combustion.

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