A two-stage micro-hybrid fuel combustion chamber head

Abstract

The present application belongs to the field of hydrogen fuel gas turbine engine, and discloses a two-stage micro-mixed hydrogen fuel combustion chamber head, which comprises a pre-combustion stage structure and a main combustion stage structure, the main combustion stage structure comprises an integrated main-stage hydrogen fuel nozzle and a streamline body mixer assembly, the integrated main-stage hydrogen fuel nozzle is overlapped on the pre-combustion stage structure at the end along the airflow direction, and the integrated main-stage hydrogen fuel nozzle is provided with a first hydrogen gas passage. The streamline body mixer assembly is arranged on the periphery of the integrated main-stage hydrogen fuel nozzle, the streamline body mixer assembly is provided with an inner cavity in communication with the first hydrogen gas passage, and the streamline body mixer assembly is provided with a transverse injection hole in communication with the inner cavity. The present application can realize the stability of the hydrogen fuel combustion chamber, improve the mixing quality and spatial distribution uniformity of the hydrogen fuel in the premixing process, shorten the residence time of the hydrogen fuel in the combustion chamber, effectively reduce the maximum gas temperature in the combustion zone, and reduce the NOx emission.

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] With global environmental and energy challenges becoming increasingly severe, the transition to low-carbon aviation and green energy has become an inevitable trend for the sustainable development of the aviation industry. After several years of advancement in new energy industries and related technologies, hydrogen energy has been highly anticipated and has rapidly become a central element in the green energy transition, serving as a key technology option for future green aviation propulsion. It is also poised to bring about disruptive technological changes in aviation propulsion within the "decarbonization" target cycle.

[0003] Among the current major carbon emission reduction technologies, hydrogen 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 a microchannel, and the mixed gas is ejected through the same nozzle as a jet. 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 nitrogen oxide generation of hydrogen premixed combustion can be reduced to 1 / 20 of that 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 more likely to move upstream, thereby increasing the risk of flashback. Micro-mixed non-premixed combustion is a new type of combustion method (also known as diffusion combustion), which allows hydrogen and air to pass through the jet channel at high speed separately. 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 backfire in traditional micro-mixed premixed combustion and uneven mixing and high nitrogen oxide emissions in micro-mixed non-premixed combustion, the present invention discloses a two-stage micro-mixed hydrogen fuel combustion chamber head, wherein the combustion chamber head includes a pre-combustion stage structure and a main combustion stage structure coaxially arranged outside the pre-combustion stage structure, wherein the pre-combustion 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 mixer assembly. The end of the integrated main stage hydrogen fuel nozzle along the airflow direction overlaps the pre-combustion stage structure. The integrated main stage hydrogen fuel nozzle is provided with a first hydrogen channel. The streamlined mixer assembly is disposed on the periphery of the integrated main stage hydrogen fuel nozzle and has an inner cavity connected to the first hydrogen channel. The streamlined mixer assembly is provided with a transverse injection hole connected to the inner cavity.

[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 mixer assembly includes a plurality of conical aerodynamic stabilizers distributed circumferentially on the integrated main-stage hydrogen fuel nozzle, and a plurality of the transverse injection holes are formed on both side walls of the conical aerodynamic 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 backflow vortex on the concave surface.

[0009] Furthermore, the diameter of the transverse 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 on 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 streamlined 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 opposite 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] Furthermore, the pre-combustion stage structure includes a coaxial primary swirler, a secondary hydrogen fuel nozzle, and a venturi tube. 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. An air channel 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 on the outside of the first-stage swirler, the minimum diameter of the convergent section is spaced from the end of the secondary-stage hydrogen fuel nozzle, and the expansion section is provided with multiple cooling holes.

[0016] Compared with the prior art, the beneficial effects achieved by at least one of the above technical solutions adopted in the embodiments of this specification include at least the following: the two-stage micro-mixed hydrogen fuel combustion chamber head of the present invention adopts an integrated partitioned 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, jet-cross flow mixing and swirl micro-premixing, to achieve both low- and high-operating-condition combustion stability and high efficiency and low NOx emissions. At the same time, by designing the integrated streamlined body mixer assembly of the main combustion stage, the airflow is accelerated through the tapered channel formed between adjacent rows of streamlined body mixers and the hydrogen is rapidly mixed with the hydrogen cross-flow of the hydrogen injection holes arranged on both sides staggered and embedded in the streamlined body mixer, thereby improving the mixing quality and spatial distribution uniformity of the hydrogen fuel during the premixing process, shortening the residence time of the hydrogen fuel in the combustion chamber, effectively reducing the maximum gas temperature in the combustion zone, and thus reducing 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 following briefly introduces the drawings required for use in the embodiments. 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 any creative work.

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

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

[0021] Among them, 11, the first-stage swirler; 12, the secondary-stage hydrogen fuel nozzle; 13, the venturi; 14, the integrated main-stage hydrogen fuel nozzle; 15, the streamlined mixer assembly; 16, the second-stage swirler assembly; 17, the secondary-stage 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 transverse 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 embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents 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 embodiments, 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, in the absence of conflict, the features of the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this 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", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the invention.

[0025] Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, features qualified as "first," "second," etc., may explicitly or implicitly include one or more features. In the description of the present invention, unless otherwise specified, "plurality" means 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 and are not drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component can be changed at will, and the component layout type may also be more complicated.

[0027] An embodiment of the present invention discloses a two-stage micro-hybrid 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 its downstream combustion zone. The primary swirler 11 is fixed to the outer periphery of the secondary hydrogen fuel nozzle 12 at the middle 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 on the front end of the secondary hydrogen fuel nozzle 12 along the airflow direction. A plurality of secondary injection holes 17 are opened circumferentially on the rear end of the secondary hydrogen fuel nozzle 12 along the airflow direction. The plurality of secondary injection holes 17 are selectively selected and uniformly arranged in an array, and the secondary injection holes 17 in two adjacent rows 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 on the outside of the first-stage 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, which can form a stable low-speed recirculation zone 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 secondary-stage injection hole 17 across the flow, and is uniformly and efficiently micro-premixed, thereby ensuring reliable ignition and good combustion stability in the combustion chamber. The convergent throat of the venturi tube 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 tube 13 can prevent the hydrogen flame from adhering to the wall, thereby avoiding head ablation.

[0032] Among them, see Figure 1 and Figure 2As shown, the main combustion stage structure is arranged outside 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 outside the integrated main-stage hydrogen fuel nozzle 14 and has an inner cavity 23 in communication with the first hydrogen channel 21. The streamlined body mixer assembly 15 is provided with a transverse injection hole 24 in communication with the inner cavity 23.

[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 define a 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 that communicates with the upper cavity 23 of the streamlined mixer assembly 15. In a specific implementation, the gas supply pipelines of the integrated primary hydrogen fuel nozzle 14 and the secondary hydrogen fuel nozzle 12 can adopt an integrated structure, with the hydrogen supply pipeline of the secondary hydrogen fuel nozzle 12 embedded in 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 mixer assembly 15 includes a plurality of conical aerodynamic stabilizers 22 circumferentially distributed on the integrated primary hydrogen fuel nozzle 14 , and a plurality of transverse injection holes 24 are formed on both side walls of the conical aerodynamic 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 aerodynamic stabilizer 22 with a conical structure can form a convergent channel 25 between two adjacent conical aerodynamic stabilizers 22. On the one hand, it accelerates the flow rate of the airflow between the two conical aerodynamic stabilizers 22, and on the other hand, it forms a backflow vortex 26 on the leeward side of the airflow after flowing through the conical aerodynamic 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 ejected 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 backflow 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-scale 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, thereby achieving both low- and high-operating-condition combustion stability and high efficiency and low NOx emissions. The secondary cyclone assembly 16 is located on 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. The secondary cyclone assembly 16 is provided with a radial injection hole 30 opposite to the second hydrogen supply hole 231. 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, cyclone blades 28 and a cyclone sleeve 29. The cyclone hub 27 is located on the periphery of the streamlined mixer assembly 15, the cyclone blades 28 are fixed on the cyclone hub 27, and the cyclone sleeve 29 is located on the periphery of the cyclone blades 28. The radial injection hole 30 is opened 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.

[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 and well mixed, and are accelerated at the aerodynamic throat 31, thereby enhancing the turbulence intensity, preventing backfire, and achieving a wider range of uniform spatial distribution of the hydrogen-fuel mixture, effectively reducing the maximum gas temperature in the combustion zone, and thereby reducing NOx emissions.

[0042] The two-stage micro-mixed hydrogen fuel combustion chamber head of the present invention adopts an integrated partitioned 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: jet-cross flow mixing and swirl micro-premixing, achieving both low- and high-operating-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 airflow is accelerated through the tapered channel formed between adjacent rows of streamlined body mixers, and the hydrogen is rapidly mixed with the hydrogen cross-flow of the hydrogen injection holes arranged on both sides of the streamlined body mixer. This improves the mixing quality and spatial distribution uniformity of the hydrogen fuel during the premixing process, shortens the residence time of the 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 will understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations are possible in the embodiments of the present invention. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

[0044] In addition, although this specification is described according to implementation methods, not every implementation method contains only one independent technical solution. This narrative method 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 methods 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, wherein the pre-combustion stage structure performs the 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 the second stage combustion, and the main combustion stage structure includes: an integrated main-stage hydrogen fuel nozzle (14), wherein an 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 assembly (15), the streamlined body mixer assembly (15) being arranged on the periphery of the integrated primary hydrogen fuel nozzle (14), the streamlined body mixer assembly (15) being provided with an inner cavity (23) communicating with the first hydrogen channel (21), and the streamlined body mixer assembly (15) being provided with a transverse injection hole (24) communicating with the inner cavity (23); The streamlined body mixer assembly (15) includes a plurality of conical aerodynamic stabilizers (22) distributed circumferentially on the integrated main-stage hydrogen fuel nozzle (14), and a plurality of transverse injection holes (24) are provided on both side walls of the conical aerodynamic stabilizer (22); The pre-combustion stage structure comprises a coaxial primary swirler (11), a secondary hydrogen fuel nozzle (12) and a venturi (13); an air passage is formed between the inner peripheral wall of the venturi (13) and the primary swirler (11); a second hydrogen passage is provided in the secondary hydrogen fuel nozzle (12); and a plurality of secondary injection holes (17) are opened along the circumferential direction at the tail end of the secondary hydrogen fuel nozzle (12) in the direction of airflow.

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 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.

4. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 1, characterized in that: The aperture of the transverse injection hole (24) gradually increases along the height direction of the conical pneumatic stabilizer (22).

5. The two-stage micro-mixed hydrogen fuel combustion chamber head according to any one of claims 1 to 4, characterized in that: The main combustion stage structure further includes a secondary cyclone assembly (16), the secondary cyclone assembly (16) being located on the periphery of the streamlined body mixer assembly (15), the streamlined body mixer assembly (15) being provided with a second hydrogen supply hole (231) facing the secondary cyclone assembly (16), and the secondary cyclone assembly (16) being provided with a radial injection hole (30) opposite to the second hydrogen supply hole (231).

6. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 5, characterized in that: The secondary cyclone assembly (16) comprises a cyclone hub (27), cyclone blades (28) and a cyclone sleeve (29), wherein the cyclone hub (27) is located on the periphery of the streamlined mixer assembly (15), the cyclone blades (28) are fixed on the cyclone hub (27), and the cyclone sleeve (29) is located on the periphery of the cyclone blades (28); 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).

7. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 6, characterized in that: The end of the swirler hub (27) along the airflow direction converges toward the swirler sleeve (29) to form an aerodynamic throat (31).

8. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 1, characterized in that: The primary swirler (11) is fixed to the outer periphery of the secondary hydrogen fuel nozzle (12), and the venturi tube (13) is coaxially sleeved on the outside of the primary swirler (11); a hydrogen supply rod connected to the second hydrogen channel is provided on the front end of the secondary hydrogen fuel nozzle (12) along the airflow direction.

9. The two-stage micro-mixed hydrogen fuel combustion chamber head according to claim 8, characterized in that: The venturi (13) includes 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 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).

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