Combustion chamber and pure hydrogen gas turbine with same

Abstract

The invention relates to the technical field of gas turbines, in particular to a combustion chamber and a pure hydrogen gas turbine with the same. The combustion chamber comprises at least one nozzle assembly, each nozzle assembly comprises a fuel flow channel, each fuel flow channel comprises a flow channel body and a nozzle body which are sequentially arranged, an arc-shaped transition section is arranged between each flow channel body and the corresponding nozzle body, and the inner side wall of the outlet end of each nozzle body is obliquely arranged to form an outflow angle; fuel gas forms an axial vortex at an outlet of the nozzle body; and the combustion-supporting gas flow channel is mounted on the outer side of the fuel flow channel in a sleeving manner. Under the action that the guide sharp corners are matched with air serving as combustion-supporting gas on the inner wall and the periphery of the combustion-supporting gas flow channel, hydrogen serving as fuel gas generates axial vortexes at the nozzle body, the axial vortexes develop towards the downstream of the nozzle body, the speed distribution of the axial vortexes does not generate reverse axial speed, formation of a backflow area is avoided, and the service life of the nozzle body is prolonged. Therefore, the risk of hydrogen flame tempering is reduced, and generation of nitric oxide is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a combustion chamber and a pure hydrogen gas turbine having the same. Background Art

[0002] As an efficient power device, gas turbines are widely used in power generation, aviation and industrial fields. As the global energy structure shifts towards low-carbonization, hydrogen energy has become an important choice to replace fossil fuels due to its zero-carbon emission characteristics. However, traditional gas turbine combustion chambers are mainly designed for hydrocarbon fuels such as natural gas. There are many challenges when using pure hydrogen directly as fuel. It is urgent to develop new combustion technologies that are adapted to the characteristics of hydrogen fuel to meet environmental protection requirements.

[0003] Most existing pure hydrogen fuel combustion chambers use micro-mixing combustion technology to suppress flashback by reducing the diameter of the fuel nozzle and increasing the mixing speed. However, the micro-mixing structure requires a large number of micro nozzles, which leads to complex processing and high cost, and it is easy to destroy the diffusion combustion form when increasing the single-hole fuel flow rate; some designs will also introduce swirl devices to enhance mixing, but the recirculation zone generated by the swirl will increase the risk of hydrogen flame flashback, and its structure is complex and the pressure loss is large, making it difficult to adapt to the high diffusion and low turbulence requirements of hydrogen fuel. Therefore, the axial vortex mixing technology is considered, which can not only avoid backflow, but also has a simple structure to implement. Therefore, based on the hydrogen fuel combustion chamber structure in the prior art, it can effectively balance the contradictory needs in hydrogen combustion, that is, on the one hand, it can achieve rapid mixing of hydrogen and air to reduce local high temperature and NO x On the other hand, it avoids the generation of recirculation zones or high turbulence during the mixing process, preventing flame flashback and thermoacoustic oscillations. Summary of the invention

[0004] In view of this, the present invention provides a combustion chamber and a pure hydrogen gas turbine having the same, so as to solve the problem that the hydrogen fuel combustion chamber structure in the prior art cannot avoid the recirculation zone or high turbulence during rapid mixing.

[0005] In a first aspect, the present invention provides a combustion chamber, comprising at least one set of nozzle assemblies, wherein the nozzle assembly comprises:

[0006] A fuel flow channel, comprising a flow channel body and a nozzle body arranged in sequence, an arc-shaped transition section is arranged between the flow channel body and the nozzle body, an inner side wall of an outlet end of the nozzle body is inclined away from the axis of the flow channel body to form an outlet angle, and at least one pair of guide sharp corners are formed at the outlet end of the nozzle body, so that the fuel gas forms at least one axial vortex at the outlet of the nozzle body;

[0007] The combustion-supporting gas flow channel is sleeved and installed on the outside of the fuel flow channel.

[0008] When the combustion chamber is working, the fuel gas is ejected from the fuel flow channel, and the combustion-supporting gas is ejected from the combustion-supporting gas flow channel. When the fuel gas is at the flow nozzle body, an axial vortex is formed under the action of the guide angle and the inner wall of the nozzle body, and then mixed with the combustion-supporting gas in the outer combustion-supporting gas flow channel. When the combustion chamber is applied to a pure hydrogen gas turbine, hydrogen is used as the fuel gas. When hydrogen burns, the maximum laminar flame speed in the air is more than 8 times that of the methane flame, which makes the hydrogen flame prone to flashback. By using the guide angle in conjunction with the inner wall of the combustion-supporting gas flow channel and the air as the combustion-supporting gas on the periphery, the hydrogen as the fuel gas generates an axial vortex at the nozzle body to achieve full mixing of hydrogen and air. The axial vortex develops downstream of the nozzle, and its velocity distribution does not produce reverse axial velocity, avoiding the formation of a reflow zone, thereby reducing the risk of hydrogen flame flashback and helping to reduce the generation of nitrogen oxides.

[0009] In an optional embodiment, the guide angles are provided in multiple pairs, the inner side edge of the nozzle body between the same pair of guide angles is a straight edge, and the inner side edge of the nozzle body between two adjacent guide angles of different pairs of guide angles is an inner concave edge. By providing multiple pairs of guide angles and adopting an inner concave edge design between different pairs of guide angles, the flow direction of the fuel gas can be effectively guided by using multiple pairs of guide angles and multiple inner concave edges, so that the fluid forms a specific multi-strand axial vortex flow path inside the nozzle, thereby enhancing the mixing effect of the fluid, improving the mixing uniformity of the fuel and air, promoting the full progress of the combustion reaction, and then improving the combustion efficiency, reducing the generation of incomplete combustion products, and reducing pollutant emissions.

[0010] In an optional embodiment, three pairs of guide sharp corners are arranged at intervals, and the three pairs of guide sharp corners are evenly arranged around the circumference of the fuel flow channel. The three pairs of guide sharp corners are evenly arranged around the circumference of the fuel flow channel, so that the fluid forms a symmetrical flow structure around the nozzle, enhances the mixing effect of the fluid, ensures the uniform mixing of fuel and air around the nozzle, avoids incomplete combustion caused by local uneven mixing, improves combustion efficiency, and reduces the emission of pollutants such as nitrogen oxides.

[0011] In an optional embodiment, multiple groups of the nozzle assemblies are arranged at intervals to form a nozzle cluster, and multiple nozzle clusters are arranged at intervals along the circumferential direction, and the multiple nozzle clusters are arranged in rotational symmetry. By arranging multiple groups of nozzle assemblies into nozzle clusters and arranging multiple nozzle clusters at intervals along the circumferential direction to form a rotationally symmetrical arrangement structure, a uniform flow field can be formed in the combustion chamber. It can ensure uniform mixing of fuel and air in the combustion chamber, improve combustion efficiency, reduce the formation of local high temperature areas, thereby reducing the emission of pollutants such as nitrogen oxides, and at the same time improve the stability and reliability of the combustion chamber.

[0012] In an optional embodiment, two rows of nozzle assemblies are radially arranged in the same nozzle cluster, one straight edge of the nozzle assembly arranged at the periphery is arranged toward the rotational symmetry axis between the plurality of nozzle clusters, and one straight edge of the nozzle assembly arranged at the inner side is arranged away from the rotational symmetry axis between the plurality of nozzle clusters. The axial vortices outputted from the plurality of nozzle assemblies can be guided to reinforce each other, thereby enhancing the mixing effect of the fuel gas and the combustion-supporting gas.

[0013] In an optional embodiment, the nozzle clusters are arranged in a fan shape, and a central angle of one of the nozzle clusters is 50° to 70°.

[0014] In an optional embodiment, the width of the straight edge is not greater than the width of the concave edge, so that the concave edge has sufficient width to guide the flow direction of the fuel gas, ensuring that the fuel gas output from the nozzle body can generate an axial vortex with sufficient kinetic energy to ensure that the forward direction will not be easily disturbed.

[0015] In an optional embodiment, the plurality of nozzle assemblies are arranged in a ring shape.

[0016] In an optional embodiment, a rounded corner is provided on the inner side of the guide tip, which can reduce the flow resistance of the fluid inside the nozzle, allowing the fluid to pass through the nozzle more smoothly, enhancing the mixing effect of the fluid, promoting the full progress of the combustion reaction, improving combustion efficiency, reducing the generation of incomplete combustion products, and at the same time reducing the emission of pollutants such as nitrogen oxides, thereby improving the stability and reliability of the combustion chamber.

[0017] In a second aspect, the present invention further provides a pure hydrogen gas turbine having the combustion chamber of the present invention. Since the pure hydrogen gas turbine includes a combustion chamber and has the same effect as the combustion chamber, it will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 A schematic structural diagram of a nozzle assembly provided in an embodiment of the present invention.

[0020] Figure 2 A schematic structural diagram of a nozzle assembly from another perspective provided in an embodiment of the present invention.

[0021] Figure 3A schematic diagram of the flow direction of the fuel gas at the outlet end of the nozzle assembly provided in an embodiment of the present invention.

[0022] Figure 4 A schematic diagram of another flow direction of the fuel gas at the outlet end of the nozzle assembly provided in an embodiment of the present invention.

[0023] Figure 5 A schematic structural diagram of a combustion chamber provided in an embodiment of the present invention.

[0024] Figure 6 A schematic structural diagram of a combustion chamber from another angle provided in an embodiment of the present invention.

[0025] Figure 7 A static temperature distribution cloud diagram of a nozzle assembly in an axial cross section provided by an embodiment of the present invention.

[0026] Figure 8 A schematic diagram of temperature distribution in a cross section of a nozzle assembly provided in an embodiment of the present invention.

[0027] Explanation of the reference numerals: 1. fuel flow channel; 101. flow channel body; 102. arc-shaped transition section; 103. nozzle body; 1031. guide angle; 1032. straight edge; 1033. inner concave edge; 2. combustion-supporting gas flow channel. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0029] Combine the following Figures 1 to 8 , describing an embodiment of the present invention.

[0030] In a first aspect, the present invention provides a combustion chamber, comprising at least one set of nozzle assemblies, wherein the nozzle assembly comprises a fuel flow channel 1 and a combustion-supporting gas flow channel 2.

[0031] like Figure 1 and Figure 2As shown, the fuel flow channel 1 includes a flow channel body 101 and a nozzle body 103 which are arranged in sequence, and an arc-shaped transition section 102 is arranged between the flow channel body 101 and the nozzle body 103 to accelerate the movement speed of the fuel gas upstream of the nozzle body 103 and increase the kinetic energy of the fuel gas. The inner side wall of the outlet end of the nozzle body 103 is inclined away from the axis of the flow channel body to form an outlet angle α, so that the fuel gas forms an axial vortex at the outlet of the nozzle body 103. The combustion-supporting gas flow channel 2 is sleeved and installed on the outside of the fuel flow channel 1.

[0032] When the combustion chamber is working, the fuel gas is ejected from the fuel flow channel 1, and the combustion-supporting gas is ejected from the combustion-supporting gas flow channel 2. When the fuel gas is at the flow nozzle body 103, an axial vortex is formed under the action of the guide sharp angle 1031 and the inner side wall of the nozzle body 103, and then mixed with the combustion-supporting gas in the outer combustion-supporting gas flow channel 2. When the combustion chamber is applied to a pure hydrogen gas turbine, hydrogen is used as the fuel gas. When hydrogen burns, the maximum laminar flame speed in the air is more than 8 times that of the methane flame, which makes the hydrogen flame prone to flashback. By using the guide sharp angle 1031 in conjunction with the inner wall of the combustion-supporting gas flow channel 2 and the air as the combustion-supporting gas on the periphery, the hydrogen as the fuel gas generates an axial vortex at the nozzle body 103 to achieve full mixing of hydrogen and air. The axial vortex develops downstream of the nozzle, and its velocity distribution does not produce a reverse axial velocity, avoiding the formation of a reflow zone, thereby reducing the risk of hydrogen flame flashback and helping to reduce the generation of nitrogen oxides.

[0033] In one embodiment, multiple pairs of guide angles 1031 are provided, and the inner side edge of the nozzle body 103 between the same pair of guide angles 1031 is a straight edge 1032, and the inner side edge of the nozzle body 103 between two adjacent guide angles 1031 of different pairs of guide angles 1031 is an inner concave edge 1033. By providing multiple pairs of guide angles 1031 and adopting the inner concave edge 1033 design between different pairs of guide angles 1031, and by using multiple pairs of guide angles 1031 and multiple inner concave edges 1033 to cooperate, the flow direction of the fuel gas can be effectively guided, so that the fluid forms a specific multi-strand axial vortex flow path inside the nozzle, thereby enhancing the mixing effect of the fluid, improving the mixing uniformity of the fuel and the air, promoting the full progress of the combustion reaction, and then improving the combustion efficiency, reducing the generation of incomplete combustion products, and reducing pollutant emissions. Among them, the shape of the inner concave edge 1033 can be designed as an arc, a parabola or other shapes suitable for guiding the fluid to optimize the flow path and mixing effect of the fluid. In some other embodiments, the number of guide corners 1031 can be set to two pairs or four pairs or any other number, and the specific number is adjusted according to actual needs and design parameters.

[0034] In this embodiment, three pairs of guide corners 1031 are arranged at intervals, and the three pairs of guide corners 1031 are evenly arranged around the circumference of the fuel flow channel 1. The three pairs of guide corners 1031 are evenly arranged around the circumference of the fuel flow channel 1, so that the fluid forms a symmetrical flow structure around the nozzle, enhances the mixing effect of the fluid, ensures the uniform mixing of fuel and air around the nozzle, avoids incomplete combustion caused by local uneven mixing, improves combustion efficiency, and reduces the emission of pollutants such as nitrogen oxides. In some other embodiments, the arrangement of the guide corners 1031 can be non-uniform, for example, arranged at specific angles to optimize the mixing effect and combustion performance of the fluid. Figure 3 and Figure 4 As shown, the flow form of the fuel gas after being output from the nozzle body 103 is that the streamline starting from the central fuel hole, that is, the nozzle body 103, is outwardly curved downstream, and axial vortices are generated at the six guide corners 1031 of the three outer straight edges 1032.

[0035] In one embodiment, Figure 5 and Figure 6 As shown, multiple groups of nozzle assemblies are arranged at intervals to form nozzle clusters, and multiple nozzle clusters are arranged at intervals along the circumferential direction, and the multiple nozzle clusters are arranged in rotational symmetry. By arranging multiple groups of nozzle assemblies into nozzle clusters and arranging multiple nozzle clusters at intervals along the circumferential direction to form a rotationally symmetrical arrangement structure, the fluid can form a uniform flow field in the combustion chamber. It can ensure the uniform mixing of fuel and air in the combustion chamber, improve combustion efficiency, reduce the formation of local high temperature areas, thereby reducing the emission of pollutants such as nitrogen oxides, and at the same time improve the stability and reliability of the combustion chamber. The number of nozzle clusters can be set to 3, 5 or more, and the specific number is adjusted according to actual needs and design parameters.

[0036] In one embodiment, two rows of nozzle assemblies are radially arranged in the same nozzle cluster, and one of the straight edges 1032 on the nozzle assembly arranged at the periphery is arranged toward the rotational symmetry axis between the multiple nozzle clusters, and one of the straight edges 1032 on the nozzle assembly arranged at the inner side is arranged away from the rotational symmetry axis between the multiple nozzle clusters. It is possible to guide the axial vortices output from the multiple nozzle assemblies to reinforce each other, thereby enhancing the mixing effect of the fuel gas and the combustion-supporting gas. In some other embodiments, the number of rows of nozzle assemblies can be set to three or more rows, and the specific number is adjusted according to actual needs and design parameters. The direction of the straight edge 1032 of the nozzle assembly can be adjusted, for example, the straight edge 1032 of the peripheral nozzle assembly can be toward or away from the rotational symmetry axis to optimize the mixing effect and combustion performance of the fluid.

[0037] In an optional embodiment, the nozzle clusters are arranged in a fan shape, and the center angle α of a nozzle cluster is 50° to 70°. The center angle β of the nozzle cluster can be set to 40°, 60°, 80° or other suitable angles, and the specific angle is adjusted according to actual needs and design parameters. In this embodiment, five nozzle clusters are provided in this embodiment, and the center angle of the nozzle cluster can be set to 60°. The shape of the nozzle cluster can be designed to other shapes, such as rectangle, ellipse, etc., to optimize the structure of the combustion chamber and the flow path of the fluid. In the combustion chamber, a group of nozzle clusters is composed of 3 nozzle assemblies, and 5 nozzle clusters are arranged at the head of the combustion chamber. In each nozzle assembly, hydrogen fuel is sprayed in the center, and the small circle on the outer periphery of the nozzle assembly sprays air. Various cooling effusion outlets and arc transition sections 102 of high-frequency thermoacoustic oscillation dampers are arranged on the head panel. Therefore, this design not only ensures that hydrogen fuel combustion can be carried out, but also panel cooling and noise reduction can be carried out.

[0038] In one embodiment, the width of the straight edge 1032 is not greater than the width of the inner concave edge 1033, so that the inner concave edge 1033 has enough width to guide the flow direction of the fuel gas, ensuring that the fuel gas output from the nozzle body 103 can generate an axial vortex with sufficient kinetic energy to ensure that the forward direction is not easily disturbed. The width of the inner concave edge 1033 can be optimized, for example, by increasing the width of the inner concave edge 1033 to enhance the guiding effect of the fluid, or by reducing the width of the inner concave edge 1033 to optimize the flow path of the fluid.

[0039] In one embodiment, multiple groups of nozzle assemblies are arranged in a ring. This enables the fluid to form a uniform flow field in the combustion chamber, ensures uniform mixing of fuel and air, improves combustion efficiency, reduces the formation of local high-temperature areas, thereby reducing the emission of pollutants such as nitrogen oxides, and improves the stability and reliability of the combustion chamber. The arrangement of the nozzle assemblies can be designed as a non-annular arrangement, such as arranging at specific angles to optimize the mixing effect and combustion performance of the fluid.

[0040] In one embodiment, the inner side of the guide corner 1031 is provided with a rounded corner, which can reduce the flow resistance of the fluid inside the nozzle, make the fluid pass through the nozzle more smoothly, enhance the mixing effect of the fluid, promote the full progress of the combustion reaction, improve the combustion efficiency, reduce the generation of incomplete combustion products, and reduce the emission of pollutants such as nitrogen oxides, and improve the stability and reliability of the combustion chamber. The rounded corner inside the guide corner 1031 can be designed to be other shapes, such as chamfers, parabolas, etc., to optimize the flow path and mixing effect of the fluid. The size of the rounded corner can be adjusted, such as increasing or decreasing the radius of the rounded corner to optimize the flow resistance and mixing effect of the fluid.

[0041] The combustion chamber provided in this embodiment is designed with a nozzle structure based on the axial vortex principle, which effectively solves the multiple technical problems faced by existing pure hydrogen gas turbine combustion chambers. In view of the problem that hydrogen combustion is prone to produce nitrogen oxides, the axial vortex is used to achieve full mixing of hydrogen and air. The axial vortex develops downstream of the nozzle, and its velocity distribution does not produce reverse axial velocity, avoiding the formation of a reflow zone, thereby reducing the risk of hydrogen flame flashback and helping to reduce the generation of nitrogen oxides. Figure 7 As shown, it can be seen that downstream of the nozzle body 103, the fuel and air are mixed and burned, and the cooling air is sucked into the inner circle of the flame, which reduces the center temperature and is conducive to reducing pollution. The flame has an irregular shape in the lower left corner, which is conducive to the stability of the mode. In order to solve the problem of hydrogen combustion stability, a Y-shaped nozzle design is adopted, with hydrogen placed in the center of the nozzle and air placed on the outside. Figure 8 As shown, hydrogen and air can be quickly and evenly mixed after the nozzle outlet, which improves the stability of combustion, avoids the problem of flame instability caused by excessive turbulence, and helps to reduce nitrogen oxide pollution emissions. Consider the structural complexity and manufacturing cost of the combustion chamber. The Y-shaped nozzle is simple in design and easy to process and manufacture. It can be integrally formed through technologies such as 3D printing, which reduces the difficulty and cost of manufacturing. At the same time, the nozzle itself will not produce a significant pressure drop, and only a small pressure drop will be produced in the downstream axial vortex area, which is conducive to maintaining a reasonable pressure distribution inside the combustion chamber, improving the combustion efficiency, and maintaining the outlet velocity to prevent backfire. In terms of the design of the combustion chamber head, by reasonably arranging the baffles and divergent cooling holes, the radiation and conduction heat of the hydrogen burning near-wall flame can be effectively reduced, and the thermal efficiency and durability of the combustion chamber can be improved. Through the arrangement and combination of multiple Y-shaped nozzle bodies 103, the combustion chamber head of an annular combustion chamber or a single or multiple flame tubes can be flexibly constructed to meet the needs of gas turbines of different powers. The combustion chamber provided in this embodiment effectively solves the comprehensive technical problems of the pure hydrogen gas turbine combustion chamber in preventing backfire, reducing NOx emissions, improving combustion stability, and simplifying structural design through an innovative axial vortex nozzle design, and has significant technical advantages and application prospects.

[0042] According to an embodiment of the present invention, on the other hand, a pure hydrogen gas turbine is also provided, which has the combustion chamber described in the present invention. Because the pure hydrogen gas turbine includes a combustion chamber, when the combustion chamber is working, the fuel gas is ejected from the fuel flow channel 1, and the combustion-supporting gas is ejected from the combustion-supporting gas flow channel 2. At the nozzle body 103, the fuel gas forms an axial vortex due to the action of the guide sharp angle 1031 and the inner side wall of the nozzle body 103. The axial vortex fully mixes the fuel gas and the combustion-supporting gas, avoids the formation of a recirculation zone, and reduces the risk of hydrogen flame flashback. At the same time, the axial vortex helps to reduce the generation of nitrogen oxides, improve combustion efficiency, reduce the generation of incomplete combustion products, and reduce pollutant emissions.

[0043] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A combustion chamber, characterized in that: The invention comprises at least one set of nozzle assemblies, wherein the nozzle assemblies include: A fuel flow channel (1), comprising a flow channel body (101) and a nozzle body (103) arranged in sequence, an arc-shaped transition section (102) being arranged between the flow channel body (101) and the nozzle body (103), an inner side wall of an outlet end of the nozzle body (103) being arranged to be inclined away from the axis of the flow channel body to form an outlet flow angle, and at least one pair of guide sharp corners (1031) being formed at the outlet end of the nozzle body (103), so that the fuel gas forms at least one axial vortex at the outlet of the nozzle body (103); The combustion-supporting gas flow channel (2) is sleeved and installed outside the fuel flow channel (1).

2. The combustion chamber according to claim 1, characterized in that The guide sharp corners (1031) are arranged in a plurality of pairs, the inner side edge of the nozzle body (103) between the same pair of the guide sharp corners (1031) is a straight side (1032), and the inner side edge of the nozzle body (103) between two adjacent guide sharp corners (1031) of different pairs of the guide sharp corners (1031) is an inner concave side (1033).

3. The combustion chamber according to claim 2, characterized in that The guide sharp corners (1031) are arranged in three pairs at intervals, and the three pairs of guide sharp corners (1031) are evenly arranged around the circumference of the fuel flow channel (1).

4. The combustion chamber according to claim 2 or 3, characterized in that A plurality of groups of the nozzle assemblies are arranged at intervals to form a nozzle cluster. A plurality of the nozzle clusters are arranged at intervals along the circumferential direction, and the plurality of the nozzle clusters are arranged in rotational symmetry.

5. The combustion chamber according to claim 4, characterized in that Two rows of nozzle assemblies are radially arranged in the same nozzle cluster, one of the straight edges (1032) on the outer nozzle assembly is arranged toward the rotational symmetry axis between the multiple nozzle clusters, and one of the straight edges (1032) on the inner nozzle assembly is arranged away from the rotational symmetry axis between the multiple nozzle clusters.

6. The combustion chamber according to claim 5, characterized in that The nozzle clusters are arranged in a fan shape, and a central angle of one nozzle cluster is 50° to 70°.

7. The combustion chamber according to claim 2 or 3, characterized in that The width of the straight edge (1032) is no greater than the width of the concave edge (1033).

8. The combustion chamber according to any one of claims 1 to 3, characterized in that The plurality of nozzle assemblies are arranged in a ring shape.

9. The combustion chamber according to any one of claims 1 to 3, characterized in that The inner side of the guide sharp corner (1031) is provided with a rounded corner.

10. A pure hydrogen gas turbine, characterized in that: A combustion chamber according to any one of claims 1 to 9.

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