Hydrogen fuel combustion chamber and turbojet engine

Abstract

The application discloses a hydrogen fuel combustion chamber and a turbojet engine, wherein the hydrogen fuel combustion chamber comprises a combustion chamber casing, a flame tube and a turbine assembly; the combustion chamber casing comprises a casing, a first nozzle seat and a first electric nozzle seat; the first nozzle seat is used for mounting a hydrogen gas nozzle; and the first electric nozzle seat is used for mounting a spark plug; the flame tube is arranged in the casing; the flame tube comprises a tube body, a second nozzle seat and a second electric nozzle seat; an arc-shaped head is formed at an air inlet end of the tube body; a plurality of cooling fins are uniformly arranged on an inner wall of the arc-shaped head in a circumferential direction; an air inlet hole is arranged in a gap between the cooling fin and the arc-shaped head; a circumferential continuous air film is formed between the cooling fin and the arc-shaped head; the arc-shaped head forms a circumferential continuous annular vortex flow field; the second nozzle seat is used for allowing the hydrogen gas nozzle to extend into the tube body in a radial direction and for allowing the hydrogen gas nozzle to face the annular vortex flow field; the second electric nozzle seat is used for allowing the spark plug to extend into the tube body; and the turbine assembly is arranged at an outlet end of the tube body and is used for power output.

Description

Technical Field

[0001] This invention relates to the field of turbojet engine technology, and in particular, to a hydrogen fuel combustion chamber. Furthermore, this invention also relates to a turbojet engine including the aforementioned hydrogen fuel combustion chamber. Background Technology

[0002] With the comprehensive utilization of renewable energy and the in-depth development of energy conservation and emission reduction, the ability to flexibly use clean and efficient gas turbines with different hydrogen content ratios is of great significance to energy utilization. Traditional micro turbojet engines use a direct-injection nozzle matched with an evaporator tube for fuel injection and atomization. The biggest advantage of this fuel atomization scheme is its simple structure and low cost. However, this atomization scheme is not suitable for the combustion organization of hydrogen fuel. First, hydrogen is a gaseous fuel and does not require a series of crushing, atomization, and evaporation processes before combustion like liquid fuels. It can directly mix with air and burn at a certain concentration and velocity. Therefore, the evaporator tube plays no role in the combustion organization of hydrogen; on the contrary, it may even create a suitable hydrogen concentration field within the evaporator tube, leading to backfire and affecting combustion reliability. Second, for the direct-injection nozzle, the simple circular nozzle will result in excessively high hydrogen injection velocity, insufficient residence time of hydrogen in the combustion chamber, and hindering complete mixing and combustion with air.

[0003] In conclusion, when using hydrogen as fuel in the combustion chamber of a micro turbojet engine, the traditional evaporator-type fuel injection and atomization scheme cannot be directly applied. Adaptive improvements must be made to the hydrogen injection method and the hydrogen-air mixing method to meet the requirements of efficient and stable hydrogen combustion. Summary of the Invention

[0004] This invention provides a hydrogen fuel combustion chamber to solve the technical problem of how to achieve efficient and stable combustion of hydrogen in the combustion chamber when using hydrogen fuel.

[0005] The present invention also provides a turbojet engine employing the aforementioned hydrogen fuel combustion chamber.

[0006] According to one aspect of the present invention, a hydrogen fuel combustion chamber is provided, comprising a combustion chamber housing, a flame tube, and a turbine assembly. The combustion chamber housing includes a casing, a first nozzle seat, and a first spark plug seat. The first nozzle seat is disposed on the outer side of the casing and is used to mount a hydrogen nozzle. The first spark plug seat is disposed on the outer side of the casing and spaced apart from the nozzle seat, and is used to mount a spark plug. The flame tube is disposed within the casing and includes a cylinder, a second nozzle seat, and a second spark plug seat. Both the second nozzle seat and the second spark plug seat are disposed within the casing. On the cylinder body, the air inlet end of the cylinder body forms an arc-shaped head, and a plurality of cooling fins are evenly distributed circumferentially on the inner wall of the arc-shaped head. An air inlet hole is opened in the gap between the cooling fins and the arc-shaped head. The air inlet hole is used to introduce cooling gas and form a circumferentially continuous gas film in the gap between the cooling fins and the arc-shaped head, so that the arc-shaped head forms a circumferentially continuous annular vortex flow field. The second nozzle seat is used to allow the hydrogen nozzle to extend radially into the cylinder body and to make the hydrogen nozzle face the annular vortex flow field. The second spark plug seat is used to allow the spark plug to extend into the cylinder body.

[0007] Furthermore, the cylinder includes an inner ring and an outer ring disposed outside the inner ring 201. A plurality of first air film holes for heat dissipation are formed on the surface of the outer ring. A plurality of radiating holes for heat dissipation are formed at one end of the inner ring near the arc-shaped head. A plurality of second air film holes for heat dissipation are formed in the middle of the inner ring and at one end near the outlet end of the cylinder.

[0008] Furthermore, the hydrogen fuel combustion chamber also includes a hydrogen nozzle 400, which includes a connector, a mounting edge, and a nozzle body. The mounting edge is fixedly connected to the first nozzle seat. The connector is disposed on the mounting edge and is used to receive externally injected hydrogen fuel. The nozzle body is fixedly connected to the connector and extends into the cylinder. The end of the nozzle body is provided with a slope, and the nozzle on the nozzle body is located on the slope so that the nozzle faces the annular vortex field formed by the arc-shaped head.

[0009] Furthermore, the nozzle is provided with a plurality of spaced nozzle holes, the center line of the nozzle hole is at an angle of β to the center line of the nozzle body, and the center line of the nozzle hole is at an angle of γ to the central symmetry plane of the hydrogen nozzle, so that the gas flow of hydrogen ejected by the nozzle hole flows tangentially into the annular vortex field.

[0010] Furthermore, the housing is provided with a plurality of first nozzle seats, which are evenly distributed around the circumference of the housing, and the cylinder is provided with a plurality of second nozzle seats, which are evenly distributed around the circumference of the cylinder and correspond one-to-one with the first nozzle seats.

[0011] Furthermore, the second nozzle seat is fixedly connected to the cylinder body, and the nozzle body is connected to the second nozzle seat and used to support the cylinder body so that the cylinder body is fixed inside the housing.

[0012] Furthermore, a turbine assembly for power output is fixedly connected to the housing, and the cylinder is fixedly connected to the turbine assembly so that the cylinder is fixed inside the housing. The second nozzle seat adopts a movable bushing, and the nozzle body is clearance-fitted with the movable bushing.

[0013] Furthermore, the connector end is provided with a connecting cone surface to facilitate a sealed connection with an external connector.

[0014] According to another aspect of the present invention, a turbojet engine is also provided, which includes the aforementioned hydrogen fuel combustion chamber, and further includes a compressor and a turbine assembly, wherein the compressor is disposed on the housing and communicates with the air inlet, and the turbine assembly is disposed at the outlet end of the cylinder for power output.

[0015] Furthermore, the turbine assembly includes a guide and a turbine body, the guide being detachably connected to the outlet end of the cylinder, and the turbine body being connected to the guide.

[0016] The present invention has the following beneficial effects:

[0017] In the hydrogen fuel combustion chamber of this invention, compared with the traditional micro turbojet engine combustion chamber, the evaporator tube structure is eliminated. The fuel injection method of injecting hydrogen tangentially into the flame tube head is adopted, which is conducive to the mixing of hydrogen and air and avoids backfire. At the same time, by setting cooling fins on the arc-shaped head, oxygen or air enters the arc-shaped head through the air inlet and forms a circumferentially continuous gas film in the gap between the cooling fins and the arc-shaped head. This results in a circumferentially continuous annular vortex flow field structure within the arc-shaped head. The hydrogen injected by the hydrogen nozzle enters the annular vortex flow field and is directly premixed and combusted after being ignited by the spark plug. This overcomes the problem of the fast flame propagation speed of hydrogen and the easy occurrence of backfire, thus enabling hydrogen to burn efficiently and stably.

[0018] In practice, hydrogen is injected into the cylinder from the outside through a hydrogen nozzle, while air is injected into the cylinder through an air inlet. Under the action of the cooling fins, the air forms a circumferentially continuous gas film between the cooling fins and the arc-shaped head, which in turn forms a circumferentially continuous annular vortex flow field structure inside the arc-shaped head. The hydrogen injected by the hydrogen nozzle enters the annular vortex flow field and is ignited by a spark plug, then directly premixed and combusted. The energy generated by the combustion is converted into power output through the turbine assembly.

[0019] In summary, this hydrogen fuel combustion chamber makes full use of the spatial layout characteristics of micro combustion chambers. By designing a large annular vortex field structure at the head of the direct-flow combustion chamber and matching the hydrogen fuel injected tangentially along the flame tube for direct premixing, it overcomes combustion problems such as the fast flame propagation speed of hydrogen and the tendency for backfire, achieving the goal of efficient and stable combustion organization, enabling the hydrogen in the combustion chamber to burn efficiently and stably.

[0020] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0021] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0022] Figure 1 This is a schematic diagram of the hydrogen fuel combustion chamber according to a preferred embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the combustion chamber casing according to a preferred embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of the structure of the flame tube according to a preferred embodiment of the present invention.

[0025] Figure 4 A schematic diagram of the arrangement of cooling fins in a preferred embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the arrangement of the air inlet holes according to a preferred embodiment of the present invention;

[0027] Figure 6 This is a schematic diagram of the structure of the first air film pore in a preferred embodiment of the present invention;

[0028] Figure 7 This is a schematic diagram of the hydrogen nozzle according to a preferred embodiment of the present invention.

[0029] Legend:

[0030] 100. Housing; 101. First nozzle holder; 102. First electrical nozzle holder;

[0031] 200. Cylinder body; 201. Inner ring; 202. Outer ring; 203. Arc-shaped head; 204. Cooling fins; 205. Air inlet; 206. First air film hole;

[0032] 300. Second nozzle seat;

[0033] 400. Hydrogen nozzle; 401. Connector; 402. Mounting edge; 403. Nozzle body; 404. Nozzle port;

[0034] 500, Turbine assembly; 501, Compressor. Detailed Implementation

[0035] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0036] like Figures 1 to 7 As shown, a hydrogen fuel combustion chamber according to this embodiment includes a combustion chamber casing, a flame tube, and a turbine assembly 500. The combustion chamber casing includes a housing 100, a first nozzle seat 101, and a first spark plug seat 102. The first nozzle seat 101 is disposed on the outside of the housing 100 and is used to install a hydrogen nozzle 400. The first spark plug seat 102 is disposed on the outside of the housing 100 and spaced apart from the nozzle seat. The first spark plug seat 102 is used to install a spark plug. The flame tube is arranged inside the housing 100. The flame tube includes a cylinder body 200, a second nozzle seat 300, and a second spark plug seat. Both the second nozzle seat 300 and the second spark plug seat are disposed on the cylinder body 200. The cylinder 200 has an arc-shaped head 203 at its air inlet end. A plurality of cooling fins 204 are evenly distributed circumferentially on the inner wall of the arc-shaped head 203. An air inlet 205 is formed in the gap between the cooling fins 204 and the arc-shaped head 203. The air inlet 205 is used to introduce cooling gas and form a circumferentially continuous gas film in the gap between the cooling fins 204 and the arc-shaped head 203, so that the arc-shaped head 203 forms a circumferentially continuous vortex flow field. The second nozzle seat 300 is used to allow the hydrogen nozzle 400 to extend radially into the cylinder 200 and to orient the hydrogen nozzle 400 toward the vortex flow field. The second spark plug seat is used to allow the spark plug to extend into the cylinder 200.

[0037] In this embodiment, the cooling fin 204 has a "Z"-shaped structure with a height h1 ranging from 1 to 3 mm. An air inlet 205 is provided in the gap between the cooling fin 204 and the arc-shaped head 203. The gap between the cooling fin 204 and the arc-shaped head 203 forms a circumferentially continuous gas film, thereby creating a circumferentially continuous annular vortex field structure in the main combustion zone at the head of the flame tube, which is used to organize combustion and stabilize the flame. A compressor 501 is also connected to the housing 100 to supply air for hydrogen combustion to the air inlet 205.

[0038] Specifically, compared to traditional micro turbojet engines, the combustion chamber eliminates the evaporator tube structure and adopts a fuel injection method where hydrogen is injected tangentially into the head of the flame tube by a hydrogen nozzle 400. This facilitates the mixing of hydrogen and air, preventing backfire. At the same time, by setting cooling fins 204 on the arc-shaped head 203, oxygen or air enters the arc-shaped head 203 through the air inlet 205, and a circumferentially continuous gas film is formed in the gap between the cooling fins 204 and the arc-shaped head 203. This results in a circumferentially continuous annular vortex flow field structure within the arc-shaped head 203. This allows the hydrogen injected by the hydrogen nozzle 400 to enter the annular vortex flow field and be directly premixed and combusted after being ignited by the spark plug. This overcomes the problem of rapid hydrogen flame propagation and the tendency for backfire, thus enabling efficient and stable combustion of hydrogen.

[0039] In practice, hydrogen is injected into the cylinder 200 from the outside through the hydrogen nozzle 400, while air is injected into the cylinder 200 through the air inlet 205. Under the action of the cooling fins 204, the air forms a circumferentially continuous gas film through the gap between the cooling fins 204 and the arc-shaped head 203, thereby forming a circumferentially continuous annular vortex flow field structure inside the arc-shaped head 203. The hydrogen injected by the hydrogen nozzle 400 enters the annular vortex flow field and is directly premixed and combusted after being ignited by the spark plug. The energy generated by the combustion is converted into power output through the turbine assembly 500.

[0040] In summary, this hydrogen fuel combustion chamber makes full use of the spatial layout characteristics of micro combustion chambers. By designing a large annular vortex field structure at the head of the direct-flow combustion chamber and matching the hydrogen fuel injected tangentially along the flame tube for direct premixing, it overcomes combustion problems such as the fast flame propagation speed of hydrogen and the tendency for backfire, achieving the goal of efficient and stable combustion organization, enabling the hydrogen in the combustion chamber to burn efficiently and stably.

[0041] Furthermore, the cylinder 200 includes an inner ring 201 and an outer ring 202 disposed outside the inner ring 201. A plurality of first air film holes 206 for heat dissipation are formed on the surface of the outer ring 202. A plurality of radiating holes for heat dissipation are formed at one end of the inner ring 201 near the arc-shaped head 203. A plurality of second air film holes for heat dissipation are formed in the middle part of the inner ring 201 and at one end near the outlet end of the cylinder 200.

[0042] In this embodiment, both the first air film hole 206 and the second air film hole adopt a crescent-shaped air film hole structure. Specifically, the first air film hole 206 is formed by partial stamping of the outer ring 202 of the cylinder 200. First, a semi-circular circumferential seam is cut on the outer ring 202, such as... Figure 6The diameter D of the air film hole is 4-7 mm, and the distance L between two adjacent air film holes is 0.5-2.5D. The surface of the circumferential seam is then stamped to create a 0.5-1.5 mm step between the circumferential seam surface and the outer ring 202 wall. When cold air enters the cylinder 200 through the semi-circular seam, it forms a cold air cover around the first air film hole 206, thereby cooling the outer ring 202 of the cylinder 200. Several radiating holes are provided at the end of the inner ring 201 near the arc-shaped head 203 to dissipate heat from the front end of the inner ring 201. A second air film hole is provided at the rear end of the middle of the inner ring 201, and similarly, a cold air cover is formed around the second air film hole to cool the inner ring 201. In summary, by setting the first air film hole 206, the second air film hole, and the radiating holes, the cylinder 200 meets the heat dissipation requirements.

[0043] Furthermore, the hydrogen fuel combustion chamber also includes a hydrogen nozzle 400, which includes a connector 401, a mounting edge 402, and a nozzle body 403. The mounting edge 402 is fixedly connected to the first nozzle seat 101. The connector 401 is disposed on the mounting edge 402 and is used to receive externally injected hydrogen fuel. The nozzle body 403 is fixedly connected to the connector 401 and extends into the cylinder 200. The end of the nozzle body 403 is provided with a slope, and the nozzle 404 on the nozzle body 403 is located on the slope so that the nozzle 404 faces the annular vortex field formed by the arc-shaped head 203.

[0044] Reference Figure 7 In this embodiment, the nozzle body 403 primarily serves as a channel connecting the mounting edge 402 and the nozzle 404, while also acting as a hydrogen transporter and supporting the cylinder 200. Therefore, the nozzle body 403 is designed as a cylindrical structure, and its internal channel diameter is mainly determined by the hydrogen flow area of ​​the nozzle 404. The end of the nozzle body 403 is designed as a bevel, and the nozzle 404 is mounted on the bevel. The nozzle 404 is designed with hydrogen injection holes, which can be designed as simple circular holes or multi-point diverging holes. It is necessary to ensure that the hydrogen injection velocity is within a suitable range to avoid backfire.

[0045] Furthermore, the nozzle 404 is provided with a plurality of spaced nozzle holes, the center line of the nozzle hole is at an angle of β to the center line of the nozzle body 403, and the center line of the nozzle hole is at an angle of γ to the central symmetry plane of the hydrogen nozzle 400, so that the gas flow of hydrogen ejected by the nozzle hole flows tangentially into the annular vortex field.

[0046] In this embodiment, the inclined structure at the end of the nozzle body 403 is used to deviate the center line of the nozzle from the vertical direction by a certain angle β. The range of angle β is 15° to 40°. In the circumferential direction, it is deviated by an angle γ along the annular vortex flow of the main combustion zone. The range of angle γ is 10° to 30°. By adjusting the above angles, it is ensured that the hydrogen injection flow approaches the low-speed zone of the annular vortex flow field of the main combustion zone tangentially and follows the flow of the annular vortex flow, thereby achieving the best combustion stability and combustion efficiency.

[0047] Furthermore, the housing 100 is provided with a plurality of first nozzle seats 101, which are evenly distributed around the circumference of the housing 100. The cylinder 200 is provided with a plurality of second nozzle seats 300, which are evenly distributed around the circumference of the cylinder 200 and are arranged in a one-to-one correspondence with the first nozzle seats 101.

[0048] In this embodiment, multiple first nozzle seats 101 and multiple second nozzle seats 300 are provided, so that multiple hydrogen nozzles 400 can also be provided accordingly, thereby increasing the amount of hydrogen input, thereby increasing the energy generated after hydrogen combustion and increasing the upper limit of power. Furthermore, the hydrogen nozzles 400 can be used to position and support the installation of the cylinder 200.

[0049] Furthermore, the second nozzle seat 300 is fixedly connected to the cylinder 200, and the nozzle body 403 is connected to the second nozzle seat 300 and is used to support the cylinder 200 so that the cylinder 200 is fixed inside the housing 100.

[0050] In this embodiment, the cylinder 200 can be fixed to the housing 100 at the front end. Specifically, multiple hydrogen nozzles 400 are regarded as fixing pins. The second nozzle seat 300 is fixed to the cylinder 200 by welding or bolting. The hydrogen nozzles 400 pass through the second nozzle seat 300 and extend into the cylinder 200, so that the cylinder 200 is supported by the hydrogen nozzles 400 evenly distributed around the circumference, so that the cylinder 200 is fixed inside the housing 100. In order to release the thermal expansion beam at the flame tube outlet, the outlet of the cylinder 200 is connected to the guide.

[0051] Furthermore, a turbine assembly 500 for power output is fixedly connected to the housing (100), and the cylinder 200 is fixedly connected to the turbine assembly 500 so that the cylinder 200 is fixed inside the housing 100. The second nozzle seat 300 adopts a movable bushing, and the nozzle body 403 is clearance-fitted with the movable bushing.

[0052] In this embodiment, the cylinder 200 is also assembled with the housing 100 by fixing the tail end. Specifically, the outer ring 202 of the cylinder 200 is installed on the guide by screws. In order to avoid the cylinder 200 expanding and jamming against the hydrogen nozzle 400 under hot conditions, which would cause damage to the hydrogen nozzle 400, the second nozzle seat 300 is designed as a movable bushing to ensure that a clearance fit is formed between the nozzle body 403 and the movable bushing.

[0053] Furthermore, the connector 401 has a connecting cone surface at the external connection end to facilitate a sealed connection with an external connector.

[0054] In this embodiment, since the fuel delivered by the hydrogen nozzle 400 is hydrogen, and hydrogen has strong diffusivity, in order to ensure that the connector 401 used for connecting to the outside has a good sealing effect, the connecting surface of the connector 401 needs to be designed as a conical surface, and the connecting surface of the external connector needs to be a spherical surface, so that the connector 401 and the external connector form a "conical surface + spherical surface" sealing structure. The connector 401 is designed as an inner sealing cone structure, and the angle of its cone surface is in the range of 24° to 37°. If the angle of the cone surface is too small, it is not convenient for the external connector to be inserted and installed. If the angle of the cone surface is too large, it will be not conducive to the tight fit between the external connector and the connector 401.

[0055] According to another aspect of the invention, a turbojet engine is also provided, which includes the aforementioned hydrogen fuel combustion chamber, and further includes a compressor 501 and a turbine assembly 500. The compressor 501 is disposed on the housing 100 and communicates with the air inlet 205, and the turbine assembly 500 is disposed at the outlet end of the housing 200 for power output. Therefore, this turbojet engine includes all the beneficial effects of the aforementioned hydrogen fuel combustion chamber.

[0056] Furthermore, the turbine assembly 500 includes a guide vane and a turbine body. The guide vane is detachably connected to the outlet end of the cylinder 200, and the turbine body is connected to the guide vane. In this embodiment, the outlet of the cylinder 200 is connected to the guide vane to release the thermal expansion beam at the flame tube outlet. The guide vane is configured to transmit the gas flow generated by hydrogen combustion to the turbine body for energy conversion, enabling the turbine body to convert the energy generated by hydrogen combustion into kinetic energy for output.

[0057] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A hydrogen fuel combustion chamber, characterized in that, include The combustion chamber housing includes a housing (100), a first nozzle seat (101), and a first spark plug seat (102). The first nozzle seat (101) is disposed on the outside of the housing (100) and is used to install a hydrogen nozzle (400). The first spark plug seat (102) is disposed on the outside of the housing (100) and is spaced apart from the first nozzle seat (101). The first spark plug seat (102) is used to install a spark plug. A flame tube is arranged inside the housing (100). The flame tube includes a cylinder body (200), a second nozzle seat (300), and a second electric nozzle seat. The second nozzle seat (300) and the second electric nozzle seat are both disposed on the cylinder body (200). The air inlet end of the cylinder body (200) forms an arc-shaped head (203). A plurality of cooling fins (204) are evenly distributed circumferentially on the inner wall of the arc-shaped head (203). A gap is formed between the cooling fins (204) and the arc-shaped head (203). There is an air inlet (205) for introducing cooling gas and forming a circumferentially continuous gas film in the gap between the cooling plate (204) and the arc-shaped head (203), so that the arc-shaped head (203) forms a circumferentially continuous annular vortex flow field. The second nozzle seat (300) is used for the hydrogen nozzle (400) to extend radially into the cylinder (200) and to make the hydrogen nozzle (400) face the annular vortex flow field. The second spark plug seat is used for the spark plug to extend into the cylinder (200). The cylinder (200) includes an inner ring (201) and an outer ring (202) disposed outside the inner ring (201). A plurality of first air film holes (206) for heat dissipation are opened on the surface of the outer ring (202). A plurality of radiating holes for heat dissipation are opened at one end of the inner ring (201) near the arc-shaped head (203). A plurality of second air film holes for heat dissipation are opened in the middle part of the inner ring (201) and at one end near the outlet end of the cylinder (200). The hydrogen nozzle (400) includes a nozzle (401), a mounting edge (402), and a nozzle body (403). The mounting edge (402) is fixedly connected to the first nozzle seat (101). The nozzle (401) is disposed on the mounting edge (402) and is used to receive externally injected hydrogen fuel. The nozzle body (403) is fixedly connected to the nozzle (401) and extends into the cylinder (200). The end of the nozzle body (403) is provided with a slope. The nozzle (404) on the nozzle body (403) is located on the slope so that the nozzle (404) faces the annular vortex field formed by the arc-shaped head (203).

2. The hydrogen fuel combustion chamber according to claim 1, characterized in that, The nozzle (404) is provided with a plurality of spaced nozzle holes, and the angle between the center line of the nozzle hole and the center line of the nozzle body (403) is β, so that the gas flow of hydrogen injected by the nozzle hole flows into the annular vortex field.

3. The hydrogen fuel combustion chamber according to claim 1, characterized in that, The housing (100) is provided with a plurality of first nozzle seats (101), which are evenly distributed around the circumference of the housing (100). The cylinder (200) is provided with a plurality of second nozzle seats (300), which are evenly distributed around the circumference of the cylinder (200) and are provided in a one-to-one correspondence with the first nozzle seats (101).

4. The hydrogen fuel combustion chamber according to claim 3, characterized in that, The second nozzle seat (300) is fixedly connected to the cylinder (200), and the nozzle body (403) is connected to the second nozzle seat (300) and used to support the cylinder (200) so that the cylinder (200) is fixed inside the housing (100).

5. The hydrogen fuel combustion chamber according to claim 3, characterized in that, A turbine assembly (500) for power output is fixedly connected to the housing (100). The cylinder (200) is fixedly connected to the turbine assembly (500) so that the cylinder (200) is fixed inside the housing (100). The second nozzle seat (300) adopts a movable bushing, and the nozzle body (403) is clearance-fitted with the movable bushing.

6. The hydrogen fuel combustion chamber according to claim 1, characterized in that, The connector (401) has a connecting cone surface at the external connection end to facilitate sealing connection with the external connector.

7. A turbojet engine, characterized in that, The device includes a hydrogen fuel combustion chamber as described in any one of claims 1 to 6, and further includes a compressor (501) and a turbine assembly (500), wherein the compressor (501) is disposed on the housing (100) and communicates with the air inlet (205), and the turbine assembly (500) is disposed at the outlet end of the cylinder (200) for power output.

8. The turbojet engine according to claim 7, characterized in that, The turbine assembly (500) includes a guide and a turbine body, the guide being detachably connected to the outlet end of the cylinder (200), and the turbine body being connected to the guide.

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