A gas turbine combustor suitable for hydrogen combustion

Abstract

The application provides a gas turbine combustor suitable for hydrogen combustion, and belongs to the technical field of gas turbines, which can at least partially solve the problems that existing hydrogen is easy to diffuse and backfire, has a higher risk, and conventional gas turbine combustors are not suitable for hydrogen combustion, and the application comprises a combustor, a duty assembly, a hot jet assembly and a premixing assembly are arranged at the head of the combustor, the premixing assembly comprises a mixing hole, in the mixing hole, fuel and air are rapidly mixed, when the fuel is hydrogen, the hydrogen and air in the mixing hole form micro-premixing, and since the size of the mixing hole is smaller than the quenching distance of hydrogen, the combustion flame formed after micro-premixing will not backfire, and the premixed combustion can also reduce the combustion temperature compared with diffusion combustion, which is beneficial to reducing thermal nitrogen oxide emissions, and the environmental protection effect is more excellent.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine technology, and specifically relates to a gas turbine combustion chamber suitable for hydrogen combustion. Background Technology

[0002] Most existing heavy-duty gas turbines use natural gas as fuel, which releases a large amount of carbon dioxide during combustion, hindering carbon emission reduction. Therefore, researchers at home and abroad are trying to find a clean and renewable fuel to replace traditional hydrocarbon fuels. There are already practical application cases of hydrogen-blended combustion of natural gas in heavy-duty gas turbines, and the future focus will be on the research and development of all-hydrogen gas turbines. Hydrogen, as a clean and efficient energy source, is of great significance in energy technology reform and energy development strategy. In recent years, it has developed rapidly due to its advantages such as cleanliness, environmental friendliness, and sustainable utilization.

[0003] Hydrogen combustion produces only water as a combustion product. If pure hydrogen is used as fuel for gas turbines, carbon emissions can be significantly reduced. However, hydrogen is prone to diffusion and backfire, posing a high risk. Conventional gas turbine combustors are not suitable for hydrogen combustion. Therefore, we propose a gas turbine combustor suitable for hydrogen combustion. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art, and to provide a gas turbine combustion chamber suitable for hydrogen combustion.

[0005] This invention provides a gas turbine combustion chamber suitable for hydrogen combustion, comprising a combustion chamber, the head of which is provided with: The duty assembly includes a duty fuel flow path disposed in the central region of the combustion chamber head, a duty air flow path disposed outside the duty fuel flow path, and a duty vortex generator disposed at one end of the duty air flow path facing the combustion chamber, for igniting the fuel in the main combustion zone of the combustion chamber during operation and maintaining the flame from going out when the operating conditions of the combustion chamber fluctuate; The hot jet assembly includes a primary fuel flow path, a primary air flow path, a combustion chamber air flow path, and a secondary fuel flow path sequentially arranged outside the duty air flow path, for providing a heat source to the main combustion zone of the combustion chamber during operation; and The premixing assembly includes a secondary fuel supply chamber, a flame tube air flow path, and a flame tube arranged sequentially from the outside to the inside within the combustion chamber head. The secondary fuel supply chamber has multiple sets of micro nozzles on one side wall facing the flame tube air flow path, which are used to uniformly mix hydrogen and air during combustion and then deliver them into the main combustion zone of the combustion chamber.

[0006] Furthermore, the duty fuel flow path is closed at one end facing the combustion chamber, and its side wall is provided with multiple sets of duty fuel injection holes. The duty fuel flow path is a cylindrical flow path, and the duty air flow path is an annular flow path.

[0007] Specifically, the primary fuel flow path, the primary air flow path, the combustion chamber air flow path, and the secondary fuel flow path are annular flow paths, and the ends of the primary fuel flow path and the secondary fuel flow path facing the combustion chamber are closed. The sidewalls of the primary fuel flow path and the secondary fuel flow path are provided with multiple sets of injection holes facing the main combustion zone of the combustion chamber.

[0008] Specifically, a combustion chamber inlet flow path is provided on the outside of the secondary fuel supply chamber, and the combustion chamber inlet flow path is an annular flow path.

[0009] Preferably, the secondary fuel supply chamber is an annular supply chamber with both ends closed, and the secondary fuel flow path is connected to the secondary fuel supply chamber through a secondary fuel delivery pipe, wherein multiple sets of the secondary fuel delivery pipe are provided.

[0010] Specifically, one end of the wall of the combustion chamber air flow path is connected to one end of the flame tube, and the connection between the combustion chamber air flow path and the flame tube constitutes the intake airflow path splitting node of the combustion chamber, so that air can enter the combustion chamber air flow path and the flame tube air flow path respectively at the splitting node during combustion.

[0011] Furthermore, one end of the micro-nozzle is disposed in a mixing hole, which is formed on the side wall of the flame tube facing the air flow path of the flame tube.

[0012] Furthermore, the mixing hole is an oblique hole, and the diameter of the mixing hole is smaller than the quenching distance of the combustible mixture in the main combustion zone of the combustion chamber, and the outer diameter of the micro nozzle is less than or equal to half the diameter of the mixing hole.

[0013] Furthermore, the micro-nozzle is a cylindrical nozzle and is provided with fuel jet holes. The axial spacing between the mixing holes is 2 to 3 times the diameter of the mixing hole itself, and the circumferential spacing between the mixing holes is 1.5 to 2 times the diameter of the mixing hole itself.

[0014] Specifically, the other end of the micro nozzle is located inside the mixing hole and the end is closed. A fuel jet hole is formed on the side surface of the micro nozzle and is located inside the mixing hole.

[0015] The beneficial effects of this invention are as follows: The system includes a premixing assembly with mixing holes. Fuel and air are rapidly mixed within these holes. When the fuel is hydrogen, micro-premixing occurs between the hydrogen and air within the mixing holes. Because the size of the mixing holes is smaller than the quenching distance of hydrogen, the combustion flame formed after micro-premixing will not experience backfire. Furthermore, premixed combustion, compared to diffusion combustion, can lower the combustion temperature, which is beneficial for reducing thermal nitrogen oxide emissions and resulting in superior environmental performance. In addition to providing mixing space for fuel and air, the mixing holes also form a cooling gas film. The gas flow continuously removes heat from the wall surface, ensuring a uniform heat load distribution on the flame tube wall, preventing overheating, and extending its service life. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of a gas turbine combustion chamber suitable for hydrogen combustion according to a specific embodiment of the present invention; Figure 2 This is a schematic diagram of a micro-nozzle structure for a gas turbine combustion chamber suitable for hydrogen combustion, according to a specific embodiment of the present invention. Figure 3 This is a schematic diagram of a micro-nozzle and mixing hole structure for a gas turbine combustion chamber suitable for hydrogen combustion, according to a specific embodiment of the present invention. Figure 4 This is a schematic diagram of airflow in a gas turbine combustion chamber suitable for hydrogen combustion, according to a specific embodiment of the present invention.

[0017] Among them, 1 is the standby fuel flow path, 2 is the standby air flow path, 3 is the primary fuel flow path, 4 is the primary air flow path, 5 is the combustion chamber air flow path, 6 is the secondary fuel flow path, 7 is the secondary fuel delivery pipe, 8 is the combustion chamber intake flow path, 9 is the secondary fuel supply chamber, 10 is the flame tube air flow path, 11 is the micro nozzle, 12 is the mixing hole, 13 is the fuel jet hole, 14 is the standby swirler, 15 is the flame tube, and 16 is the combustion chamber. Detailed Implementation

[0018] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0019] like Figure 1 As shown in the figure, a specific embodiment of the present invention provides a gas turbine combustion chamber suitable for hydrogen combustion, including a combustion chamber 16, the head of which is provided with: The duty assembly includes a duty fuel flow path 1 located in the central region of the head of the combustion chamber 16, a duty air flow path 2 located outside the duty fuel flow path 1, and a duty swirler 14 located at one end of the duty air flow path 2 facing the combustion chamber 16, for igniting the fuel in the main combustion zone of the combustion chamber 16 during operation and maintaining the flame when the operating conditions of the combustion chamber 16 fluctuate; the hot jet assembly includes a primary fuel flow path 3, a primary air flow path 4, a combustion chamber air flow path 5, and a secondary fuel flow path 6 located sequentially outside the duty air flow path 2, for providing a heat source for the main combustion zone of the combustion chamber 16 during operation; and the premixing assembly includes a secondary fuel supply chamber 9, a flame tube air flow path 10, and a flame tube 15 located sequentially from the outside to the inside of the head of the combustion chamber 16, wherein a plurality of micro nozzles 11 are provided on the side wall of the secondary fuel supply chamber 9 facing the flame tube air flow path 10, for uniformly mixing hydrogen and air during combustion and then sending it into the main combustion zone of the combustion chamber 16.

[0020] Specifically, the standby component forms a strong swirling and recirculation zone within the combustion chamber 16, resulting in a stable flame that is always ignited and resistant to fluctuations in operating conditions. During startup, low load, and rapid changes in operating conditions, it is responsible for igniting the main combustion zone and preventing flameout. The standby fuel is ejected from the nozzles on the sidewall of the central cylindrical channel and is strongly stirred with the air from the outer annular channel under the action of the swirler. The swirling induces the recirculation core, drawing high-temperature products back to the vicinity of the nozzle. This flame directly ignites the adjacent combustible mixture on the one hand, and provides a continuous ignition source during load / incoming flow disturbances, stabilizing the main combustion zone on the other.

[0021] Furthermore, the hot jet assembly forms several controlled hot jets through primary and secondary staged combustion and interlayered air, providing a stable and mild heat source for the main combustion zone over a wide operating range, reducing dependence on the central standby flame and improving anti-flameout and anti-pulsation capabilities. Specifically, primary fuel is injected through nozzles, mixes with primary air in the near zone and combusts, generating a ring of high-temperature products / hot jets that are directed towards the main combustion zone. The outer combustion chamber 16 air flow path further provides dilution and temperature modulation, ensuring that the hot jets have sufficient temperature for ignition / stabilized combustion without overheating to suppress thermal NOx. Secondary fuel is injected further out through nozzles to supplement the heat source and reaction intensity. In terms of control strategy, it can be activated or increased as needed according to the load, thereby achieving staged stable combustion and load expansion.

[0022] Furthermore, the premixing component rapidly and uniformly premixes hydrogen and air in the air channel outside the flame tube 15 using a large number of micro-scale injections to form a combustible mixture with a controllable equivalence ratio. Through oblique mixing, backfire is significantly suppressed. The premixed gas is connected to the main combustion zone through the flame tube orifice to achieve combustion. Among them, the micro-premixed hydrogen flows from the hydrogen supply source to the secondary fuel flow path 6, and is transmitted to the secondary fuel supply chamber 9 through the secondary fuel delivery pipe 7. Finally, it is transmitted to the mixing hole 12 through several uniformly and densely distributed micro nozzles 11, where it is rapidly and uniformly mixed with the air in the mixing hole 12 and then transmitted from its outlet. It is then ignited and burned by the hot jet flame to form a micro-premixed flame.

[0023] Based on the above basic implementation method, the end of the duty fuel flow path 1 facing the combustion chamber 16 is closed, and its side wall is provided with multiple sets of duty fuel injection holes. The duty fuel flow path 1 is a cylindrical flow path, and the duty air flow path 2 is an annular flow path.

[0024] Specifically, the primary fuel flow path 3, the primary air flow path 4, the combustion chamber air flow path 5, and the secondary fuel flow path 6 are annular flow paths, and the ends of the primary fuel flow path 3 and the secondary fuel flow path 6 facing the combustion chamber 16 are closed. The sidewalls of the primary fuel flow path 3 and the secondary fuel flow path 6 are provided with multiple sets of nozzles facing the main combustion zone of the combustion chamber 16. The outer wall of the primary air flow path 4 is flush with the wall of the flame tube 15, and the distance between the outer wall and the inner wall of the primary air flow path 4 is 5-50 mm, depending on the size of the combustion chamber and the flow rate.

[0025] In one specific embodiment, a combustion chamber inlet flow path 8 is provided on the outside of the secondary fuel supply chamber 9, and the combustion chamber inlet flow path 8 is an annular flow path.

[0026] In this embodiment, the secondary fuel supply chamber 9 is an annular supply chamber and both ends of the secondary fuel supply chamber 9 are closed. The secondary fuel flow path 6 is connected to the secondary fuel supply chamber 9 through the secondary fuel delivery pipe 7, and multiple sets of the secondary fuel delivery pipe 7 are provided.

[0027] Furthermore, one end of the wall of the combustion chamber air flow path 5 is connected to one end of the flame tube 15, and the connection between the combustion chamber air flow path 5 and the flame tube 15 constitutes the intake airflow path splitting node of the combustion chamber 16, so that air can enter the combustion chamber air flow path 5 and the flame tube air flow path 10 respectively at the splitting node during combustion.

[0028] In another specific embodiment, such as Figure 2 , Figure 3 As shown, one end of the micro nozzle 11 is disposed in the mixing hole 12, which is opened on the side wall of the flame tube 15 facing the flame tube air flow path 10.

[0029] Specifically, the mixing hole 12 is an oblique hole, and its diameter is smaller than the quenching distance of the combustible mixture in the main combustion zone of the combustion chamber 16. The outer diameter of the micro-nozzle 11 is less than or equal to half the diameter of the mixing hole 12. The quenching distance refers to the minimum characteristic dimension of the channel required to extinguish the flame of the hydrogen / air combustible mixture when, under specified operating conditions, the flame cannot continue to propagate due to heat exchange and cooling effects from the solid wall. When the minimum characteristic dimension of the channel / gap / slit is smaller than the quenching distance, the flame is quenched and cannot pass through the channel. In this technical solution, it refers to the quenching distance of the hydrogen / air combustible mixture in the micro-scale channels at the head of the combustion chamber, such as the mixing hole 12, the micro-nozzle 11, and their gaps.

[0030] In one specific embodiment, the micro nozzle 11 is a cylindrical nozzle and is provided with fuel jet holes. The axial spacing between the mixing holes 12 is 2 to 3 times the diameter of the mixing holes 12 themselves, and the circumferential spacing between the mixing holes 12 is 1.5 to 2 times the diameter of the mixing holes 12 themselves.

[0031] In this embodiment, the other end of the micro nozzle 11 is located inside the mixing hole 12 and the end is closed. A fuel jet hole is provided on the side surface of the micro nozzle 11 and the fuel jet hole is located inside the mixing hole 12.

[0032] Specifically, the axial direction of the axial spacing between the mixing holes 12 is parallel to the direction of the central axis of the combustion chamber 16, and the circumferential direction of the circumferential spacing between the mixing holes 12 is the direction surrounding the central axis of the combustion chamber 16.

[0033] In another specific embodiment, such as Figure 4 As shown, during operation, air exits from the compressor outlet and enters the combustion chamber 16 intake airflow path 8 in the reverse direction at the tail end of the combustion chamber 16. When it reaches the connection between the head of the combustion chamber 16 and the wall of the combustion chamber 16, it splits into two parts: one part enters the combustion chamber airflow path 5, and the other part enters the flame tube airflow path 10. The air entering the combustion chamber airflow path 5 can also be split into two parts: one part enters the primary airflow path 4, and the other part enters the standby airflow path 2. Most of the air entering the flame tube airflow path 10 enters the mixing hole 12, and the remaining small portion of air exits from the outlet of the flame tube airflow path 10 to cool the downstream hot-end components of the combustion chamber.

[0034] Furthermore, hydrogen is supplied simultaneously with the air flow. Standby hydrogen flows from the hydrogen supply source to standby fuel flow path 1 and exits through the hydrogen jet orifice at its end (not shown in the figure). It rapidly mixes with the air in standby air flow path 2, forming a reflux zone under the action of standby cyclone separator 14. The mixture is ignited by the igniter to form a standby flame, acting as a stable ignition source. Air and hydrogen diffuse and burn simultaneously, preventing backfire. Simultaneously, hot jet hydrogen flows from the hydrogen supply source to primary fuel flow path 3 and exits through the hydrogen jet orifice at its end (not shown in the figure). It rapidly mixes with the air in primary air flow path 4 and is ignited by the standby flame, forming diffusion combustion and preventing backfire. Due to the small gap in primary air flow path 4 and the high gas flow velocity, a stable hot jet adhering to the wall can be formed. Micro-premixed hydrogen flows from the hydrogen supply source to the secondary fuel flow path 6, and is then transmitted through the secondary fuel delivery pipe 7 to the secondary fuel supply chamber 9. Finally, it is delivered through several uniformly and densely distributed micro-nozzles 11 to the mixing holes 12, where it is rapidly and uniformly mixed with the air in the mixing holes 12 before being delivered from its outlet and ignited by the hot jet flame to form a micro-premixed flame. Compared with diffusion combustion, this can reduce the flame temperature, thereby reducing the formation of thermal nitrogen oxides. In addition, since the size of the mixing holes 12 is smaller than the quenching distance of hydrogen, it can prevent backfire and ensure safe and stable combustion of hydrogen.

[0035] Furthermore, the narrow flow channel increases the heat loss of fuel combustion, while increasing the probability of free radicals colliding with the flow channel wall, reducing the number of free radicals participating in the reaction, thereby terminating combustion and effectively preventing backfire.

[0036] To aid in a better understanding of the invention, a more comprehensive and specific embodiment is described, in which the invention provides a gas turbine combustion chamber suitable for hydrogen combustion, comprising a combustion chamber 16, the head of which is provided with: The duty assembly includes a duty fuel flow path 1 located in the central region of the head of the combustion chamber 16, a duty air flow path 2 located outside the duty fuel flow path 1, and a duty swirler 14 located at one end of the duty air flow path 2 facing the combustion chamber 16, for igniting the fuel in the main combustion zone of the combustion chamber 16 during operation and maintaining the flame during fluctuations in the operating conditions of the combustion chamber 16; the heat jet assembly includes a primary fuel flow path 3, a primary air flow path 4, a combustion chamber air flow path 5, and a secondary fuel flow path 6 sequentially located outside the duty air flow path, for providing a heat source for the main combustion zone of the combustion chamber 16 during operation; and the premixing assembly includes a secondary fuel supply chamber 9, a flame tube air flow path 10, and a flame tube 15 sequentially located from the outside to the inside within the head of the combustion chamber 16, wherein a plurality of micro nozzles 11 are provided on one side wall of the secondary fuel supply chamber 9 facing the flame tube air flow path 10, for uniformly mixing hydrogen and air during combustion and then delivering it into the main combustion zone of the combustion chamber 16.

[0037] In this embodiment, the standby fuel flow path 1 is closed at one end facing the combustion chamber 16, and its sidewall is provided with multiple sets of standby fuel injection holes. The standby fuel flow path 1 is a cylindrical flow path, and the standby air flow path 2 is an annular flow path. The primary fuel flow path 3, the primary air flow path 4, the combustion chamber air flow path 5, and the secondary fuel flow path 6 are annular flow paths, and the primary fuel flow path 3 and the secondary fuel flow path 6 are closed at one end facing the combustion chamber 16. The sidewalls of the primary fuel flow path 3 and the secondary fuel flow path 6 are provided with multiple sets of injection holes facing the main combustion zone of the combustion chamber 16. The outer side of the secondary fuel supply chamber 9 is provided with a combustion chamber inlet. The airflow path 8 and the combustion chamber inlet airflow path 8 are annular flow paths; the secondary fuel supply chamber 9 is annular supply chamber and both ends of the secondary fuel supply chamber 9 are closed; the secondary fuel flow path 6 is connected to the secondary fuel supply chamber 9 through the secondary fuel delivery pipe 7, and multiple sets of the secondary fuel delivery pipe 7 are provided; one end of the wall of the combustion chamber air flow path 5 is connected to one end of the flame tube 15, and the connection between the combustion chamber air flow path 5 and the flame tube 15 constitutes the inlet airflow path diversion node of the combustion chamber, so that air can enter the combustion chamber air flow path 5 and the flame tube air flow path 10 respectively at the diversion node during combustion.

[0038] Furthermore, one end of the micro-nozzle 11 is disposed in the mixing hole 12, which is opened on the side wall of the flame tube 15 facing the flame tube air flow path 10; the mixing hole 12 is an oblique hole, and the diameter of the mixing hole 12 is smaller than the quenching distance of the combustible mixture in the main combustion zone of the combustion chamber 16; the outer diameter of the micro-nozzle 11 is less than or equal to half the diameter of the mixing hole 12; the micro-nozzle 11 is a cylindrical nozzle and is provided with fuel jet holes; the axial spacing between the mixing holes 12 is 2 to 3 times the diameter of the mixing hole 12 itself, and the circumferential spacing between the mixing holes 12 is 1.5 to 2 times the diameter of the mixing hole 12 itself; the other end of the micro-nozzle 11 is located inside the mixing hole 12 and is closed; the side surface of the micro-nozzle 11 is provided with fuel jet holes, which are disposed inside the mixing hole 12.

[0039] In summary, the embodiments disclosed herein have at least the following technical effects: This invention differs from traditional gas turbine combustors. It features several mixing holes 12 on the flame tube wall, each smaller than the quenching distance of the fuel. A secondary fuel supply chamber 9 is coaxially located outside the flame tube. Fuel from the secondary fuel supply chamber 9 is delivered to the mixing holes 12 via several columnar micro-nozzles. Simultaneously, air is also delivered to the mixing holes 12 from the combustion chamber intake airflow path 8. In the mixing holes 12, fuel and air are rapidly mixed. Due to the small size of the mixing holes 12 and the relatively small amount of fuel and air, micro-premixing is achieved. The mixture then enters the flame tube 15 and is ignited by the flame within the flame tube 15. During this process, the flame tube 15 wall can supply fresh premixed air into the flame tube 15, effectively functioning as a fuel nozzle and significantly reducing the complexity of the combustion chamber head 16. When the fuel is hydrogen, the hydrogen and air in the mixing hole 12 form micro-premix. Since the size of the mixing hole 12 is smaller than the quenching distance of hydrogen, the combustion flame formed after micro-premix will not backfire. At the same time, premixed combustion can reduce the combustion temperature compared with diffusion combustion, which is conducive to reducing thermal nitrogen oxide emissions and has a better environmental protection effect. The mixing hole 12 is smaller than the quenching distance of the fuel used and is an oblique hole, similar to the cooling gas film on the wall of the combustion chamber of a conventional gas turbine. Therefore, in this invention, the mixing hole 12 can not only provide a mixing space for fuel and air, but also form a cooling gas film. The flow of gas can continuously remove heat from the wall surface, ensuring that the heat load distribution on the wall of the combustion chamber 15 is uniform, avoiding overheating of the wall of the combustion chamber 15, and helping to extend its service life. A duty officer is set at the central axis of the combustion chamber 16. The duty fuel and duty air mix and burn after the duty swirler 14, i.e., diffusion combustion, to form a duty flame. This can avoid backfire and form a stable reflux zone, which can act as a stable ignition source to ignite the surrounding fresh air mixture. A hot jet stage is coaxially arranged outside the combustion chamber. The outer wall of the first-stage airflow path 4 is flush with the wall of the flame tube 15. The distance between the outer and inner walls of the first-stage airflow path 4 is 5-50 mm, depending on the size and flow rate of the combustion chamber. Fuel and air are transported to the outlet through the first-stage fuel flow path 3 and the first-stage airflow path 4, respectively, and then mix and burn simultaneously, i.e., diffusion combustion. Due to the small distance between the outer and inner walls of the first-stage airflow path 4, the gas propagation speed is fast, which can form a wall-attached hot jet on the inner wall of the flame tube 15. This helps to quickly ignite the micro-mixed gas transmitted from the mixing hole and also helps to distribute the heat load evenly within the flame tube.

[0040] It is understood that the above embodiments are merely exemplary implementations used to illustrate the principles of the present invention, and the present invention is not limited thereto. For those skilled in the art, various modifications and improvements can be made without departing from the spirit and essence of the present invention, and these modifications and improvements are also considered to be within the scope of protection of the present invention.

Claims

1. A gas turbine combustion chamber suitable for hydrogen combustion, characterized in that, Includes a combustion chamber, the head of which is provided with: The duty assembly includes a duty fuel flow path disposed in the central region of the combustion chamber head, a duty air flow path disposed outside the duty fuel flow path, and a duty vortex generator disposed at one end of the duty air flow path facing the combustion chamber, for igniting the fuel in the main combustion zone of the combustion chamber during operation and maintaining the flame from going out when the operating conditions of the combustion chamber fluctuate; The hot jet assembly includes a primary fuel flow path, a primary air flow path, a combustion chamber air flow path, and a secondary fuel flow path sequentially arranged outside the duty air flow path, for providing a heat source for the main combustion zone of the combustion chamber during operation; as well as The premixing assembly includes a secondary fuel supply chamber, a flame tube air flow path, and a flame tube arranged sequentially from the outside to the inside within the combustion chamber head. The secondary fuel supply chamber has multiple sets of micro nozzles on one side wall facing the flame tube air flow path, which are used to uniformly mix hydrogen and air during combustion and then deliver them into the main combustion zone of the combustion chamber.

2. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 1, characterized in that, The duty fuel flow path is closed at one end facing the combustion chamber, and its side wall is provided with multiple sets of duty fuel injection holes. The duty fuel flow path is a cylindrical flow path, and the duty air flow path is an annular flow path.

3. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 1, characterized in that, The primary fuel flow path, the primary air flow path, the combustion chamber air flow path, and the secondary fuel flow path are annular flow paths, and the ends of the primary fuel flow path and the secondary fuel flow path facing the combustion chamber are closed. The sidewalls of the primary fuel flow path and the secondary fuel flow path are provided with multiple sets of nozzles facing the main combustion zone of the combustion chamber.

4. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 1, characterized in that, The combustion chamber inlet flow path is provided on the outside of the secondary fuel supply chamber, and the combustion chamber inlet flow path is an annular flow path.

5. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 1, characterized in that, The secondary fuel supply chamber is an annular chamber with both ends closed. The secondary fuel flow path is connected to the secondary fuel supply chamber through a secondary fuel delivery pipe, and multiple sets of the secondary fuel delivery pipe are provided.

6. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 1, characterized in that, One end of the wall of the combustion chamber air flow path is connected to one end of the flame tube, and the connection between the combustion chamber air flow path and the flame tube constitutes the intake air flow path splitting node of the combustion chamber, so that air can enter the combustion chamber air flow path and the flame tube air flow path respectively at the splitting node during combustion.

7. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 1, characterized in that, One end of the micro-nozzle is disposed in a mixing hole, which is opened on the side wall of the flame tube facing the air flow path of the flame tube.

8. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 7, characterized in that, The mixing hole is an oblique hole, and the diameter of the mixing hole is smaller than the quenching distance of the combustible mixture in the main combustion zone of the combustion chamber. The outer diameter of the micro nozzle is less than or equal to half the diameter of the mixing hole.

9. The gas turbine combustion chamber suitable for hydrogen combustion according to claim 8, characterized in that, The micro-nozzle is a cylindrical nozzle and is provided with fuel jet holes. The axial spacing between the mixing holes is 2 to 3 times the diameter of the mixing hole itself, and the circumferential spacing between the mixing holes is 1.5 to 2 times the diameter of the mixing hole itself.

10. A gas turbine combustion chamber for hydrogen combustion according to any one of claims 1 to 9, wherein the other end of the micro-nozzle is located inside the mixing orifice and the end is closed, and a fuel jet orifice is provided on the side surface of the micro-nozzle, the fuel jet orifice being disposed inside the mixing orifice.

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