Two-stage micro-hydrogen-mixing fuel combustion chamber head

Abstract

The invention belongs to the field of hydrogen fuel gas turbine engines, and discloses a two-stage micro-mixing hydrogen fuel combustion chamber head which comprises a pre-combustion stage structure and a main combustion stage structure, and the main combustion stage structure comprises an integrated main-stage hydrogen fuel nozzle and a streamline body mixer assembly. The tail end of the integrated main-stage hydrogen fuel nozzle in the airflow direction is in lap joint with the pre-combustion-stage structure, and a first hydrogen channel is formed in the integrated main-stage hydrogen fuel nozzle. The streamline body mixer assembly is arranged on the periphery of the integrated primary hydrogen fuel nozzle, an inner cavity communicated with the first hydrogen channel is formed in the streamline body mixer assembly, and a transverse injection hole communicated with the inner cavity is formed in the streamline body mixer assembly. The combustion stability of the hydrogen fuel combustion chamber can be achieved, meanwhile, the mixing quality and spatial distribution uniformity of the hydrogen fuel in the premixing process are improved, the retention time of the hydrogen fuel in the combustion chamber is shortened, the highest fuel gas temperature of a combustion area is effectively reduced, and emission of NOx is reduced.

Description

Technical Field

[0001] The invention belongs to the field of hydrogen fuel gas turbine engines and relates to a two-stage micro-mixed hydrogen fuel combustion chamber head. Background Art

[0002] As global environmental and energy issues become increasingly severe, low-carbon aviation and green energy transformation have become an inevitable trend for the sustainable development of the aviation industry. After several years of advancement of new energy industries and related technologies, hydrogen energy has been highly anticipated and has quickly become the center of green energy transformation and the main technical option for future green aviation power. It will also bring disruptive technological changes to aviation power within the "decarbonization" target cycle.

[0003] Among the current major carbon reduction technologies, hydrogen energy power is the ultimate solution to achieve net zero emissions. Common hydrogen combustion methods in the aviation field include micro-mixed premixed combustion and micro-mixed non-premixed combustion. Micro-mixed premixed combustion refers to the pre-mixing of hydrogen and air in the microchannel, and the mixed gas is ejected through the same nozzle. The use of premixed combustion can effectively reduce the emission of nitrogen oxides from hydrogen combustion. Under the condition of generating the same heat, the generation of nitrogen oxides from hydrogen premixed combustion can be reduced to 1 / 20 of aviation kerosene. However, the activity of hydrogen in the premixed reaction and the higher flame speed make the flame front thinner, and the flame is easier to move upstream, thereby increasing the risk of flashback. Micro-mixed non-premixed combustion is a new type of combustion method (also called diffusion combustion), which allows hydrogen and air to pass through the jet channel at high speed, hydrogen is injected at the air outlet, and the two are mixed and burned at the outlet of the microchannel. Compared with the micro-mixed premixed combustion mode, the micro-mixed non-premixed combustion mode can avoid the "backfire" problem of hydrogen combustion and improve combustion efficiency and stability. However, diffusion combustion has the problems of uneven mixing and higher nitrogen oxide emissions. Summary of the invention

[0004] In order to solve the technical problems of flashback problem in traditional micro-mixed premixed combustion mode and uneven mixing and high nitrogen oxide emissions in micro-mixed non-premixed combustion mode, the present invention discloses a two-stage micro-mixed hydrogen fuel combustion chamber head, the combustion chamber head includes a precombustion stage structure and a main combustion stage structure coaxially arranged outside the precombustion stage structure, the precombustion stage structure performs first stage combustion, and the main combustion stage structure performs second stage combustion.

[0005] The main combustion stage structure includes an integrated main stage hydrogen fuel nozzle and a streamlined body mixer assembly, the end of the integrated main stage hydrogen fuel nozzle along the airflow direction is overlapped on the pre-combustion stage structure, and a first hydrogen channel is provided in the integrated main stage hydrogen fuel nozzle. The streamlined body mixer assembly is arranged at the periphery of the integrated main stage hydrogen fuel nozzle, and an inner cavity connected to the first hydrogen channel is provided in the streamlined body mixer assembly, and a transverse injection hole connected to the inner cavity is opened on the streamlined body mixer assembly.

[0006] Furthermore, the integrated primary hydrogen fuel nozzle includes a coaxial inner shell and an outer shell, the outer circumferential wall of the inner shell and the inner circumferential wall of the outer shell form the first hydrogen channel, the front end of the first hydrogen channel is connected to the hydrogen supply rod, and the rear end of the outer shell is provided with a first hydrogen supply hole connected to the inner cavity of the streamlined mixer assembly.

[0007] Furthermore, the streamlined body mixer assembly includes a plurality of conical pneumatic stabilizers circumferentially distributed on the integrated main-stage hydrogen fuel nozzle, and a plurality of the lateral injection holes are formed on both side walls of the conical pneumatic stabilizer.

[0008] Furthermore, a concave surface is provided on the leeward side of the conical aerodynamic stabilizer connected to the two side walls, and the airflow forms a recirculation vortex on the concave surface.

[0009] Furthermore, the diameter of the lateral injection hole gradually increases along the height direction of the conical pneumatic stabilizer.

[0010] In an improved embodiment of the main combustion stage structure, the main combustion stage structure also includes a secondary cyclone assembly, which is located at the periphery of the streamlined body mixer assembly, and the streamlined body mixer assembly is provided with a second hydrogen supply hole facing the secondary cyclone assembly, and the secondary cyclone assembly is provided with a radial injection hole opposite to the position of the second hydrogen supply hole.

[0011] Furthermore, the secondary cyclone assembly includes a cyclone hub, cyclone blades and a cyclone sleeve, the cyclone hub is located at the periphery of the streamline mixer assembly, the cyclone blades are fixed on the cyclone hub, and the cyclone sleeve is located at the periphery of the cyclone blades; the radial injection hole corresponding to the position of the second hydrogen supply hole is opened on the cyclone hub downstream of the cyclone blade outlet position.

[0012] Furthermore, the end of the swirler hub along the airflow direction converges toward the swirler sleeve to form an aerodynamic throat.

[0013] Further, the pre-combustion stage structure comprises a coaxial primary swirler, a secondary hydrogen fuel nozzle and a venturi tube, wherein the primary swirler is fixed to the outer periphery of the secondary hydrogen fuel nozzle, the venturi tube is coaxially sleeved on the outside of the primary swirler, and an air passage is formed between the inner peripheral wall of the venturi tube and the primary swirler;

[0014] A second hydrogen channel is provided in the secondary hydrogen fuel nozzle, a hydrogen supply rod connected to the second hydrogen channel is provided at the front end of the secondary hydrogen fuel nozzle along the airflow direction, and a plurality of secondary injection holes are opened circumferentially at the rear end of the secondary hydrogen fuel nozzle along the airflow direction.

[0015] Furthermore, the venturi includes a straight section, a convergent section and an expansion section, the straight section is sleeved outside the primary swirler, the minimum diameter of the convergent section is spaced from the end of the secondary hydrogen fuel nozzle, and the expansion section is provided with a plurality of cooling holes.

[0016] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of this specification include at least: the head of the two-stage micro-mixed hydrogen fuel combustion chamber of the present invention adopts an integrated partition layout of the pre-combustion stage and the main combustion stage, the pre-combustion stage adopts a swirl micro-premixed flame-stabilizing combustion mode, and the main combustion stage adopts two hydrogen combustion modes of jet-cross flow mixing and swirl micro-premixing, so as to achieve both low- and high-condition combustion stability and high efficiency and low NOx emissions. At the same time, through the design of the integrated streamlined body mixer assembly of the main combustion stage, the gas flow is accelerated through the tapered channel formed between the adjacent rows of streamlined body mixers, and the hydrogen gas is rapidly mixed with the hydrogen cross flow of the staggered hydrogen injection holes on both sides embedded in the streamlined body mixer, which improves the mixing quality and spatial distribution uniformity of hydrogen fuel in the premixing process, shortens the residence time of hydrogen fuel in the combustion chamber, effectively reduces the maximum gas temperature in the combustion zone, and thus reduces NOx emissions. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 A schematic diagram of a two-stage micro-mixed hydrogen fuel combustion chamber head disclosed in an embodiment of the present invention;

[0019] Figure 2 A schematic diagram of the three-dimensional structure of a two-stage micro-mixed hydrogen fuel combustion chamber head disclosed in an embodiment of the present invention;

[0020] Figure 3A schematic diagram of the flow field of a streamline mixer assembly disclosed in an embodiment of the present invention;

[0021] Among them, 11, the first-stage swirler; 12, the secondary hydrogen fuel nozzle; 13, the venturi; 14, the integrated main-stage hydrogen fuel nozzle; 15, the streamline mixer assembly; 16, the second-stage swirler assembly; 17, the secondary injection hole; 18, the cooling hole; 19, the inner shell; 20, the outer shell; 21, the first hydrogen channel; 22, the conical aerodynamic stabilizer; 23, the inner cavity; 231, the second hydrogen supply hole; 24, the lateral injection hole; 25, the convergent channel; 26, the return vortex; 27, the swirler hub; 28, the swirler blades; 29, the swirler sleeve; 30, the radial injection hole; 31, the aerodynamic throat. DETAILED DESCRIPTION

[0022] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0023] The following describes the implementation methods of the present application through specific specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and the features of the embodiments can be combined with each other in the absence of conflict. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0024] In the description of this embodiment, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the invention.

[0025] In addition, the terms "first", "second", "third", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more features. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more.

[0026] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present disclosure. The illustrations only show components related to the present disclosure rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0027] An embodiment of the present invention discloses a two-stage micro-mixed hydrogen fuel combustion chamber head, which includes a pre-combustion stage structure and a main combustion stage structure coaxially arranged outside the pre-combustion stage structure. The pre-combustion stage structure performs first-stage combustion, and the main combustion stage structure performs second-stage combustion.

[0028] See also Figure 1 As shown, the pre-combustion stage structure is arranged at the center of the combustion chamber head, including a coaxial primary swirler 11, a secondary hydrogen fuel nozzle 12, a venturi 13 and a downstream combustion zone thereof. The primary swirler 11 is fixed on the periphery of the secondary hydrogen fuel nozzle 12 at a mid-section position, and the venturi 13 is coaxially sleeved on the outside of the primary swirler 11. An air channel is formed between the inner circumferential wall of the venturi 13 and the primary swirler 11.

[0029] A second hydrogen channel is provided in the secondary hydrogen fuel nozzle 12, a hydrogen supply rod connected to the second hydrogen channel is provided at the front end of the secondary hydrogen fuel nozzle 12 along the airflow direction, and a plurality of secondary injection holes 17 are opened circumferentially at the rear end of the secondary hydrogen fuel nozzle 12 along the airflow direction, wherein the plurality of secondary injection holes 17 are preferentially selected and uniformly arranged in an array, wherein two adjacent rows of secondary injection holes 17 are arranged in a staggered manner.

[0030] See also Figure 1 As shown, the venturi 13 includes a straight section, a convergent section and an expansion section. The straight section is mounted outside the primary swirler 11. The minimum diameter of the convergent section is spaced apart from the end of the secondary hydrogen fuel nozzle 12. The expansion section is provided with a plurality of cooling holes 18.

[0031] In this specific embodiment, the pre-combustion stage structure performs swirl micro-premixing and flame-stabilizing combustion, and a stable low-speed recirculation zone can be formed downstream of the outlet of the first-stage swirler 11. The fresh air flowing through the first-stage swirler 11 carries along the hydrogen ejected from the cross-flow of the secondary-stage injection hole 17 for uniform and efficient micro-premixing, thereby ensuring reliable ignition of the combustion chamber and good combustion stability. The convergent throat of the venturi 13 can prevent the "backfire" problem of hydrogen combustion, and the airflow flowing through the multiple rows of cooling holes 18 on the expansion section of the venturi 13 can prevent the hydrogen flame from adhering to the wall and avoid head ablation.

[0032] Among them, see Figure 1 and Figure 2As shown, the main combustion stage structure is arranged at the periphery of the pre-combustion stage structure, and includes an integrated main stage hydrogen fuel nozzle 14 and a streamlined body mixer assembly 15. The end of the integrated main stage hydrogen fuel nozzle 14 along the airflow direction is overlapped on the pre-combustion stage structure, and a first hydrogen channel 21 is provided in the integrated main stage hydrogen fuel nozzle 14. The streamlined body mixer assembly 15 is arranged at the periphery of the integrated main stage hydrogen fuel nozzle 14, and an inner cavity 23 communicating with the first hydrogen channel 21 is provided in the streamlined body mixer assembly 15, and a transverse injection hole 24 communicating with the inner cavity 23 is opened on the streamlined body mixer assembly 15.

[0033] Further, see Figure 1 As shown, the integrated primary hydrogen fuel nozzle 14 includes a coaxial inner shell 19 and an outer shell 20, the outer circumferential wall of the inner shell 19 and the inner circumferential wall of the outer shell 20 enclose the first hydrogen channel 21, the front end of the first hydrogen channel 21 is connected to the hydrogen supply rod, and the rear end of the outer shell 20 is provided with a first hydrogen supply hole connected to the inner cavity 23 of the streamlined mixer assembly 15. In specific implementation, the gas supply pipeline of the integrated primary hydrogen fuel nozzle 14 and the secondary hydrogen fuel nozzle 12 can adopt an integrated overall structure, and the hydrogen supply pipeline of the secondary hydrogen fuel nozzle 12 is built into the main gas supply pipeline of the integrated primary hydrogen fuel nozzle 14.

[0034] Further, see Figure 1 and Figure 2 As shown, the streamlined body mixer assembly 15 includes a plurality of conical pneumatic stabilizers 22 circumferentially distributed on the integrated main-stage hydrogen fuel nozzle 14 , and a plurality of transverse injection holes 24 are formed on both side walls of the conical pneumatic stabilizer 22 .

[0035] Further, see Figure 2 and Figure 3 As shown, the leeward side of the conical aerodynamic stabilizer 22 connected to the two side walls is provided with a concave surface, and the airflow forms a return vortex 26 on the concave surface, that is, the leading edge and the trailing edge of the conical aerodynamic stabilizer 22 are rounded into a streamlined shape.

[0036] The conical pneumatic stabilizer 22 with a conical structure can form a convergent channel 25 between two adjacent conical pneumatic stabilizers 22, which on the one hand accelerates the flow rate of the airflow between the two conical pneumatic stabilizers 22, and on the other hand forms a return vortex 26 on the leeward side of the airflow after passing through the conical pneumatic stabilizer 22.

[0037] Furthermore, the diameter of the transverse injection hole 24 gradually increases along the height direction of the conical pneumatic stabilizer 22, so that the hydrogen sprayed from the transverse injection hole 24 and the incoming air flow are mixed in the radial direction and the spatial distribution is more uniform. Figure 3As shown, the hydrogen ejected from the lateral injection hole 24 is accelerated to mix with the incoming air in the convergent channel 25, and then is carried by the airflow into the return vortex 26 located on the leeward side of the conical aerodynamic stabilizer 22 for stable combustion. On the one hand, the convergent channel 25 plays a role in improving the mixing quality and spatial distribution uniformity of hydrogen fuel during the premixing process, and at the same time can prevent hydrogen combustion "backfire". The multiple relatively independent and smaller hydrogen flame structures formed by the multiple circumferential conical aerodynamic stabilizers 22 can further improve the combustion performance and reduce NOx emissions.

[0038] In an improved embodiment of the main combustion stage structure, see Figure 1 As shown, the main combustion stage structure also includes a secondary cyclone assembly 16. The setting of the secondary cyclone assembly 16 enables the main combustion stage structure to add a swirl micro-premixed combustion mode on the basis of the jet-cross flow mixed combustion mode, so as to achieve both low- and high-operating-condition combustion stability and high efficiency and low NOx emissions. The secondary cyclone assembly 16 is located at the periphery of the streamlined body mixer assembly 15, and the streamlined body mixer assembly 15 is provided with a second hydrogen supply hole 231 facing the secondary cyclone assembly 16, and the secondary cyclone assembly 16 is provided with a radial injection hole 30 opposite to the second hydrogen supply hole 231. Among them, the number of radial injection holes 30 should be consistent with the number of conical aerodynamic stabilizers 22.

[0039] Further, see Figure 1 As shown, the secondary cyclone assembly 16 includes a cyclone hub 27, a cyclone blades 28 and a cyclone sleeve 29, the cyclone hub 27 is located at the periphery of the streamline mixer assembly 15, the cyclone blades 28 are fixed on the cyclone hub 27, and the cyclone sleeve 29 is located at the periphery of the cyclone blades 28; the cyclone hub 27 is provided with the radial injection hole 30 which is opposite to the position of the second hydrogen supply hole 231 and is located downstream of the outlet position of the cyclone blades 28.

[0040] Further, see Figure 1 As shown, the end of the swirler hub 27 along the airflow direction converges toward the swirler sleeve 29 to form an aerodynamic throat 31 .

[0041] During operation, the rotating air flowing into the secondary cyclone assembly 16 and the hydrogen ejected from the radial injection holes 30 are quickly swirled to achieve good mixing, and are accelerated at the aerodynamic throat 31, thereby enhancing the turbulence intensity, preventing backfire, achieving a wider range of spatially uniform distribution of the hydrogen-fuel mixture, and effectively reducing the maximum gas temperature in the combustion zone, thereby reducing NOx emissions.

[0042] The head of the two-stage micro-mixed hydrogen fuel combustion chamber of the present invention adopts a pre-combustion stage and a main combustion stage with an integrated partition layout. The pre-combustion stage adopts a swirl micro-premixed flame-stabilizing combustion mode, and the main combustion stage adopts two hydrogen combustion modes, jet-cross-flow mixing and swirl micro-premixing, to achieve both low- and high-condition combustion stability and high efficiency and low NOx emissions. At the same time, through the design of the integrated streamlined body mixer assembly of the main combustion stage, the gas flow is accelerated through the tapered channel formed between adjacent rows of streamlined body mixers, and the hydrogen gas is rapidly mixed with the hydrogen cross-flow of the staggered hydrogen injection holes on both sides embedded in the streamlined body mixer, which improves the mixing quality and spatial distribution uniformity of hydrogen fuel in the premixing process, shortens the residence time of hydrogen fuel in the combustion chamber, effectively reduces the maximum gas temperature in the combustion zone, and thus reduces NOx emissions.

[0043] Obviously, those skilled in the art should understand that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the embodiments of the present invention may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0044] In addition, although this specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A two-stage micro-mixed hydrogen fuel combustion chamber head, including a pre-combustion stage structure, the pre-combustion stage structure performs a first stage combustion, characterized in that: The periphery of the pre-combustion stage structure is coaxially provided with a main combustion stage structure, and the main combustion stage structure performs a second stage combustion, and the main combustion stage structure comprises: An integrated main-stage hydrogen fuel nozzle (14), wherein the end of the integrated main-stage hydrogen fuel nozzle (14) along the airflow direction is overlapped on the pre-combustion stage structure, and a first hydrogen channel (21) is provided in the integrated main-stage hydrogen fuel nozzle (14); A streamlined body mixer component (15), the streamlined body mixer component (15) being arranged at the periphery of the integrated primary hydrogen fuel nozzle (14), the streamlined body mixer component (15) being provided with an inner cavity (23) communicating with the first hydrogen channel (21), and the streamlined body mixer component (15) being provided with a transverse injection hole (24) communicating with the inner cavity (23).

2. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 1, characterized in that: The integrated primary hydrogen fuel nozzle (14) comprises a coaxial inner shell (19) and an outer shell (20), wherein the outer circumferential wall of the inner shell (19) and the inner circumferential wall of the outer shell (20) form the first hydrogen channel (21), the front end of the first hydrogen channel (21) is connected to the hydrogen supply rod, and the rear end of the outer shell (20) is provided with a first hydrogen supply hole connected to the upper inner cavity (23) of the streamlined mixer assembly (15).

3. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 1, characterized in that: The streamlined body mixer assembly (15) comprises a plurality of conical pneumatic stabilizers (22) distributed circumferentially on the integrated primary hydrogen fuel nozzle (14), and a plurality of transverse injection holes (24) are provided on both side walls of the conical pneumatic stabilizer (22).

4. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 3 is characterized in that: The leeward side of the conical pneumatic stabilizer (22) connected to the two side walls is provided with a concave surface, and the airflow forms a return vortex (26) on the concave surface.

5. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 3, characterized in that: The diameter of the lateral injection hole (24) gradually increases along the height direction of the conical pneumatic stabilizer (22).

6. The two-stage micro-mixed hydrogen fuel combustion chamber head according to any one of claims 1 to 5, characterized in that: The main combustion stage structure also includes a secondary cyclone assembly (16), the secondary cyclone assembly (16) is located at the periphery of the streamlined body mixer assembly (15), the streamlined body mixer assembly (15) is provided with a second hydrogen supply hole (231) facing the secondary cyclone assembly (16), and the secondary cyclone assembly (16) is provided with a radial injection hole (30) opposite to the second hydrogen supply hole (231).

7. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 6, characterized in that: The secondary cyclone assembly (16) comprises a cyclone hub (27), cyclone blades (28) and a cyclone sleeve (29); the cyclone hub (27) is located at the periphery of the streamline mixer assembly (15); the cyclone blades (28) are fixed on the cyclone hub (27); and the cyclone sleeve (29) is located at the periphery of the cyclone blades (28); and the radial injection hole (30) is provided on the cyclone hub (27) downstream of the outlet position of the cyclone blades (28) and is opposite to the position of the second hydrogen supply hole (231).

8. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 7, characterized in that: The end of the swirler hub (27) along the airflow direction converges toward the swirler sleeve (29) to form a pneumatic throat (31).

9. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 1, characterized in that: The pre-combustion stage structure comprises a coaxial primary swirler (11), a secondary hydrogen fuel nozzle (12) and a venturi (13); the primary swirler (11) is fixed to the outer periphery of the secondary hydrogen fuel nozzle (12); the venturi (13) is coaxially sleeved on the outside of the primary swirler (11); an air passage is formed between the inner peripheral wall of the venturi (13) and the primary swirler (11); A second hydrogen channel is provided in the secondary hydrogen fuel nozzle (12); a hydrogen supply rod connected to the second hydrogen channel is provided at the front end of the secondary hydrogen fuel nozzle (12) along the gas flow direction; and a plurality of secondary injection holes (17) are provided in the circumferential direction at the rear end of the secondary hydrogen fuel nozzle (12) along the gas flow direction.

10. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 9, characterized in that: The venturi (13) comprises a straight section, a convergent section and an expansion section, the straight section is sleeved on the outside of the primary cyclone (11), a minimum diameter on the convergent section is spaced from the end of the secondary hydrogen fuel nozzle (12), and a plurality of cooling holes (18) are provided on the expansion section.

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