A combined multi-nozzle hydrogen burner and hydrogen combustion chamber

Abstract

This invention relates to the field of energy and power combustion devices, and more specifically, to a combined multi-nozzle hydrogen burner and a hydrogen combustion chamber. To achieve the above objectives, the combined multi-nozzle hydrogen burner provided by this invention adopts a centrally graded structure, including a pre-combustion stage region and a main combustion stage region: the pre-combustion stage region is located at the center of the burner, forming a pre-combustion stage flame; the main combustion stage region is located around the pre-combustion stage, forming a main combustion stage flame; the pre-combustion stage region and / or the main combustion stage region can be selectively activated according to operating conditions. This invention employs a centrally graded combustion organization mode combined with an innovative design such as a petal-shaped structure of the main combustion stage and a non-equidistant premixing tube arrangement, effectively solving problems such as power regulation, NOx emissions, backfire, and thermoacoustic oscillation in hydrogen combustion chambers under wide operating conditions, providing a stable, efficient, and low-emission solution for hydrogen fuel combustion.

Description

Technical Field

[0001] This invention relates to the field of energy and power combustion devices, and more specifically, to a combined multi-nozzle hydrogen burner and a hydrogen combustion chamber. Background Technology

[0002] With increasing environmental awareness, reducing pollutant emissions during combustion has become one of the key challenges in the research and development of aero-engines and gas turbines. In order to achieve lower nitrogen oxide (NOx) emissions while avoiding increasing the concentration of carbon monoxide and unburned hydrocarbons in the exhaust gas, low-emission combustion technologies such as lean fuel premixing and pre-evaporation and rich fuel quenching lean fuel combustion have been extensively studied and applied in the fields of gas turbines and aero-engines.

[0003] However, with the introduction of carbon neutrality goals, exhaust emissions from hydrocarbon fuels always contain carbon dioxide, failing to meet the requirements for low-carbon combustion. Recently, combustion organization forms based on sustainable fuels and other zero-carbon fuels have received widespread attention in aircraft engine and gas turbine combustors, with the main aim of further reducing carbon emissions while reducing traditional pollutant emissions (such as NOx).

[0004] Hydrogen combustion, as one of the most environmentally friendly combustion methods currently available, boasts advantages such as zero carbon emissions and the absence of combustion pollutants like non-volatile particulate matter (NVPM), making it a highly promising low-carbon fuel. However, hydrogen combustion also presents several challenges, including excessively fast combustion rates, high flame temperatures, and significant NOx emissions. These challenges pose difficulties for the efficient organization of combustion in aero-engines and gas turbine combustors.

[0005] Combustion chambers for aircraft engines and gas turbines that rely on traditional aviation kerosene combustion face numerous challenges when directly burning hydrogen, including difficulties in hydrogen fuel injection layout, high flame temperatures, high NOx emissions, susceptibility to backfire, and oscillating combustion.

[0006] Therefore, it is necessary to develop entirely new hydrogen burners and hydrogen combustion chambers to adapt to the characteristics of hydrogen combustion. Summary of the Invention

[0007] The purpose of this invention is to provide a combined multi-nozzle hydrogen burner and a hydrogen combustion chamber, which solves the problems of difficult hydrogen fuel injection arrangement and high flame temperature in existing combustion chambers.

[0008] Another objective of this invention is to provide a combined multi-nozzle hydrogen burner and a hydrogen combustion chamber that solves the problems of high NOx emissions, easy backfire, and oscillating combustion in existing combustion chambers.

[0009] To achieve the above objectives, the present invention provides a combined multi-nozzle hydrogen burner, which adopts a centrally staged structure, including a pre-combustion stage region and a main combustion stage region:

[0010] The pre-combustion stage zone is located at the center of the burner, forming a pre-combustion stage flame;

[0011] The main combustion stage region is located outside the pre-combustion stage, forming the main combustion stage flame;

[0012] Selectively open the pre-combustion zone and / or the main combustion zone according to the operating conditions.

[0013] In some embodiments, the pre-combustion stage region includes annularly arranged microjet nozzles;

[0014] The main combustion stage region includes multiple premixed nozzles arranged in an array, each equipped with a premixing tube.

[0015] In some embodiments, the main combustion stage region includes at least a main combustion stage hydrogen pipe, a main combustion stage hydrogen chamber, and a main combustion stage premixing pipe:

[0016] The main combustion stage hydrogen pipe is connected to the main combustion stage hydrogen chamber and provides main combustion stage hydrogen fuel to the main combustion stage flame.

[0017] The main combustion stage premixing pipe passes through the main combustion stage hydrogen chamber, and its upstream end is used to introduce main combustion stage air.

[0018] The main combustion stage premixing pipe has a main combustion stage hydrogen injection hole on its side wall for introducing main combustion stage hydrogen.

[0019] The main combustion stage hydrogen chamber is connected to the main combustion stage hydrogen pipe and the main combustion stage hydrogen nozzle, and stores and distributes the main combustion stage hydrogen to the main combustion stage hydrogen nozzle.

[0020] The main combustion stage premixing tube serves as a premixing nozzle, mixing the main combustion stage hydrogen with the main combustion stage air.

[0021] In some embodiments, the main combustion stage region further includes a main combustion stage ramp boss:

[0022] The main combustion stage ramp protrusion is located on the side wall of the internal air flow channel of the main combustion stage premixing pipe, upstream of the hydrogen injection hole of the main combustion stage.

[0023] In some embodiments, the number of the main combustion stage premixed tubes is multiple:

[0024] The spatial arrangement of the premixed tubes in the main combustion stage is an asymmetric, non-periodic distribution of a spatial array.

[0025] In some embodiments, the spatial arrangement of the main combustion stage premixed tubes includes a spiral arrangement and a radial arrangement.

[0026] In some embodiments, the internal airflow channel of the main combustion stage premixed pipe is a gradually expanding rotating channel or a gradually contracting rotating channel, and the cross-sectional shape of the channel is petal-shaped.

[0027] In some embodiments, the length of the internal airflow channel of the main combustion stage premixed pipe is 2mm-20mm, and the diameter of the main combustion stage hydrogen nozzle is 0.3mm-1mm.

[0028] In some embodiments, the number of main combustion stage premixed tube arrays is 3-12.

[0029] In some embodiments, the internal airflow channel of the main combustion stage premixed pipe is a straight circular pipe channel.

[0030] In some embodiments, the pre-combustion stage region includes at least a pre-combustion stage hydrogen pipe, a pre-combustion stage hydrogen nozzle, a pre-combustion stage throat flow channel, and a pre-combustion stage blunt body.

[0031] The pre-combustion stage hydrogen pipe is connected to the pre-combustion stage hydrogen nozzle to provide pre-combustion stage hydrogen to the pre-combustion stage flame;

[0032] The pre-combustion stage hydrogen nozzle is located at the end of the pre-combustion stage hydrogen pipe and surrounds the pre-combustion stage blunt body in an annular shape.

[0033] The pre-combustion stage throat channel is located outside the pre-combustion stage hydrogen nozzle and the pre-combustion stage blunt body, and is used to introduce pre-combustion stage air and mix it with pre-combustion stage hydrogen.

[0034] The pre-combustion stage blunt body is located at the center of the pre-combustion stage flame combustion zone.

[0035] To achieve the above objectives, the present invention provides a hydrogen combustion chamber, comprising at least a fuel supply line, a nozzle assembly, a combustion chamber flame tube, and a combustion chamber outer shell:

[0036] The fuel supply line is connected to the nozzle assembly and is used to supply hydrogen fuel to the nozzle assembly;

[0037] The nozzle assembly is connected upstream to the fuel supply line and downstream to the inlet of the combustion chamber flame tube, where it injects hydrogen fuel and mixes it with air to form a mixture.

[0038] The combustion chamber flame tube, which is integral with the combustion chamber shell, serves as the combustion zone to contain the mixture for combustion.

[0039] The nozzle assembly employs the aforementioned combined multi-nozzle hydrogen burner.

[0040] This invention provides a combined multi-nozzle hydrogen burner and hydrogen combustion chamber, which adopts a centrally staged combustion organization mode and incorporates innovative designs such as pre-combustion stage micro-jet, main combustion stage petal structure, and non-equidistant premixing tube arrangement. It effectively solves the problems of power regulation, NOx emission, backfire, and thermoacoustic oscillation in hydrogen combustion chambers under a wide range of operating conditions, providing a stable, efficient, and low-emission solution for hydrogen fuel combustion. Attached Figure Description

[0041] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features, wherein:

[0042] Figure 1 A schematic diagram of a hydrogen combustion chamber according to an embodiment of the present invention is disclosed;

[0043] Figure 2 A cross-sectional view of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed;

[0044] Figure 3 A top view of the first arrangement of the main combustion stage region of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed;

[0045] Figure 4a A top view of the second arrangement of the main combustion stage region of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed.

[0046] Figure 4b A top view of the third arrangement of the main combustion stage region of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed;

[0047] Figure 5a A schematic diagram of a petal-shaped, gradually expanding rotating flow channel according to an embodiment of the present invention is disclosed;

[0048] Figure 5b Revealed Figure 5a A schematic diagram of the cross-section AA of a petal-shaped, gradually expanding rotating flow channel;

[0049] Figure 6a A schematic diagram of a petal-shaped tapered rotating flow channel according to an embodiment of the present invention is disclosed;

[0050] Figure 6b Revealed Figure 6a A schematic diagram of the cross-section AA of a petal-shaped tapered rotating flow channel;

[0051] Figure 7a A first schematic diagram of a combustion chamber with a petal-shaped main combustion stage premixed tube array is disclosed according to an embodiment of the present invention;

[0052] Figure 7b A second schematic diagram of a combustion chamber with a petal-shaped main combustion stage premixed tube array is disclosed according to an embodiment of the present invention.

[0053] The meanings of the labels in the figures are as follows:

[0054] 1. Fuel supply pipeline;

[0055] 2. Nozzle assembly;

[0056] 3. Air;

[0057] 4. Combustion chamber flame tube;

[0058] 5. Pre-combustion stage hydrogen pipe; 6. Main combustion stage hydrogen pipe; 7. Main combustion stage air;

[0059] 8. Pre-combustion stage air; 9. Pre-combustion stage hydrogen nozzle; 10. Pre-combustion stage throat flow channel;

[0060] 11. Pre-combustion stage hydrogen; 12. Main combustion stage hydrogen; 13. Main combustion stage ramp boss;

[0061] 14. Main combustion stage hydrogen nozzle; 15. Pre-combustion stage flame; 16. Main combustion stage flame;

[0062] 17. Main combustion stage hydrogen chamber; 18. Pre-combustion stage air baffle;

[0063] 19. Main combustion stage premixed pipe; 20. Pre-combustion stage bluff body. Detailed Implementation

[0064] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the invention.

[0065] This invention proposes a combined multi-nozzle hydrogen burner and hydrogen combustion chamber, specifically targeting hydrogen combustion chambers that achieve zero carbon emissions and low pollutant emissions. It presents a hydrogen combustion organization scheme, main stage arrangement, and main stage aerodynamic structure design, capable of meeting the wide operating conditions of aero-engine and gas turbine combustion chambers while ensuring low NOx emissions. Furthermore, it addresses common problems in hydrogen combustion chambers such as spontaneous combustion, backfire, and thermoacoustic vibrations.

[0066] Figure 1 A schematic diagram of a hydrogen combustion chamber according to an embodiment of the present invention is shown, as follows. Figure 1 As shown, the hydrogen combustion chamber proposed in this invention includes at least a fuel supply pipeline 1, a nozzle assembly 2, a combustion chamber flame tube 4, and a combustion chamber outer shell:

[0067] The fuel supply line 1 is connected to the nozzle assembly 2 and is used to supply hydrogen fuel to the nozzle assembly 2.

[0068] The nozzle assembly 2 is connected upstream to the fuel supply pipeline 1 and downstream to the inlet of the combustion chamber flame tube 4. It injects hydrogen fuel and mixes it with the air 3 provided by the compressor to form a combustible mixture, ensuring the uniformity and stability of combustion.

[0069] The combustion chamber flame tube 4 surrounds the nozzle assembly 2 and forms an integral part with the combustion chamber shell. It serves as a combustion zone for containing the mixture of hydrogen and air for combustion, converting chemical energy into thermal energy.

[0070] In this embodiment, the nozzle assembly 2 adopts a specially designed combined multi-nozzle hydrogen burner.

[0071] Figure 2 A cross-sectional view of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed, such as... Figure 2 As shown, the combined multi-nozzle hydrogen burner proposed in this invention adopts a centrally staged structure, including a pre-combustion stage region and a main combustion stage region:

[0072] The pre-combustion stage area is located at the center of the burner, forming a pre-combustion stage flame 15;

[0073] The main combustion stage region is located outside the pre-combustion stage, forming the main combustion stage flame 16;

[0074] Selectively open the pre-combustion zone and / or the main combustion zone according to the operating conditions.

[0075] The combustion power of aero engines and gas turbines varies significantly under different operating conditions. The combustion power of a single fuel injector can range from several kilowatts to hundreds of kilowatts, or even reach the megawatt level. Therefore, it is essential to address the issues of power regulation, combustion organization, and outlet temperature distribution in hydrogen combustors across a wide range of operating conditions.

[0076] The combined multi-nozzle hydrogen burner proposed in this invention adopts a centrally staged combustion organization mode. At the head of the combustion chamber, the injection unit performs staged combustion, with a pre-combustion stage area set in the center and a main combustion stage area set around the pre-combustion stage area.

[0077] Center-stage combustion refers to the formation of staged combustion by arranging multiple different types of nozzles radially along the geometric center of the combustion chamber nozzle assembly.

[0078] In this embodiment, under low operating conditions, only the pre-combustion stage region is activated for combustion, while under high operating conditions, the pre-combustion stage and the main combustion stage regions are combined for combustion.

[0079] The main combustion stage region is an array of premixed tubes. By combining the hydrogen fuel nozzles in the pre-combustion stage and the main combustion stage region, and selectively opening different numbers of nozzles in the pre-combustion stage and the main combustion stage region, the system can adapt to the wide operating conditions of the engine, improve the combustor's adaptability to operating conditions, and thus solve the problems of power regulation, combustion organization and outlet temperature distribution in the hydrogen combustion chamber under wide operating conditions.

[0080] Furthermore, the pre-combustion stage region includes annularly arranged micro-jet nozzles. The main combustion stage region includes multiple arrayed premixed nozzles with premixing tubes.

[0081] In this embodiment, the pre-combustion stage flame 15 is a micro-jet flame, and the main combustion stage flame 16 is a micro-premixed flame.

[0082] The combustion of hydrogen in aircraft engines and gas turbines will generate a large amount of NOx emissions, and the problem of NOx emissions from hydrogen combustion needs to be solved.

[0083] The combined multi-nozzle hydrogen burner proposed in this invention has a pre-combustion stage region with annularly arranged micro-jet nozzles. By adjusting the local aerodynamic geometric parameters such as nozzle orifice and spacing, NOx emission suppression can be achieved while also meeting the requirements for stable combustion.

[0084] The single-orifice equivalence ratio of the pre-combustion stage hydrogen nozzle is 0.2 to 1.1, which can be adjusted according to design requirements.

[0085] The basic form of the main combustion stage is a series of premixed nozzles with premixing tubes arranged in an array. Multiple main combustion stage hydrogen injection holes are set in the main combustion stage premixing tube. By adjusting the position of the main combustion stage hydrogen injection holes in the premixing tube, the fuel and air are fully mixed. The fuel supports not only hydrogen fuel, but is also compatible with other hydrocarbon gaseous fuels.

[0086] The equivalence ratio of the main combustion stage hydrogen nozzle is 0.2 to 0.8, which can be adjusted according to specific design requirements.

[0087] More specifically, the pre-combustion stage region includes at least a pre-combustion stage hydrogen pipe 5, a pre-combustion stage hydrogen nozzle 9, a pre-combustion stage throat flow channel 10, and a pre-combustion stage blunt body 20.

[0088] The pre-combustion stage hydrogen pipe 5 is connected to the pre-combustion stage hydrogen nozzle 9 to provide pre-combustion stage hydrogen 11 to the pre-combustion stage flame 15;

[0089] The pre-combustion stage hydrogen nozzle 9 is located at the end of the pre-combustion stage hydrogen pipe 5 and surrounds the pre-combustion stage blunt body 20 in an annular shape.

[0090] The pre-combustion stage throat channel 10 is located outside the pre-combustion stage hydrogen nozzle 9 and the pre-combustion stage blunt body 20, and is used to introduce pre-combustion stage air and mix it with pre-combustion stage hydrogen.

[0091] The pre-combustion stage blunt body 20 is located at the center of the pre-combustion stage flame combustion zone;

[0092] The pre-combustion stage hydrogen nozzle 9 is combined with the pre-combustion stage throat channel 10 to form a micro-jet nozzle, thereby forming a pre-combustion stage flame 15.

[0093] Furthermore, the pre-combustion stage region also includes a pre-combustion stage air baffle 18, which is disposed outside the pre-combustion stage throat flow channel 10 to regulate the flow rate of the pre-combustion stage air.

[0094] It should be clarified that, in this invention, "inward" refers to the direction toward the center of the burner, while "outward" refers to the direction away from the center of the burner. Furthermore, in this invention, "upstream" refers to the starting direction of the gas flow path, while "downstream" refers to the ending direction of the gas flow path.

[0095] More specifically, the main combustion stage region includes at least the main combustion stage hydrogen pipe 6, the main combustion stage hydrogen chamber 17, and the main combustion stage premixing pipe 19:

[0096] The main combustion stage hydrogen pipe 6 is connected to the main combustion stage hydrogen chamber 17 and provides main combustion stage hydrogen 12 fuel to the main combustion stage flame 16.

[0097] The main combustion stage premixing pipe 19 passes through the main combustion stage hydrogen chamber 17, and its upstream end is used to introduce the main combustion stage air 7.

[0098] The main combustion stage premixing pipe 19 has a main combustion stage hydrogen injection hole 14 on its side wall for introducing main combustion stage hydrogen 12.

[0099] The main combustion stage hydrogen chamber 17 is connected to the main combustion stage hydrogen pipe 6 and the main combustion stage hydrogen nozzle 14, and stores and distributes the main combustion stage hydrogen 12 to the main combustion stage hydrogen nozzle 14.

[0100] The main combustion stage premixing tube 19 mixes the main combustion stage hydrogen with the main combustion stage air, and serves as a premixing nozzle to form the main combustion stage flame 16.

[0101] Furthermore, the diameter of the main combustion stage hydrogen nozzle 14 is preferably 0.3mm-1mm.

[0102] Furthermore, the main combustion stage region also includes a main combustion stage ramp boss 13:

[0103] The main combustion stage ramp protrusions 13 are multiple in number and are arranged in a ring on the side wall of the internal air flow channel of the main combustion stage premixing pipe 19. They are located upstream of the hydrogen nozzle 14 of the main combustion stage to optimize the mixing of air and hydrogen, improve the stability of the main combustion stage flame 16, enhance combustion efficiency, and prevent backfire.

[0104] Hydrogen combustion systems employing low-NOx emission technologies may encounter accompanying catastrophic combustion problems such as spontaneous combustion, backfire, and thermoacoustic oscillations. Therefore, while ensuring low NOx emissions in hydrogen fuel combustion chambers, challenges such as spontaneous combustion, backfire, and thermoacoustic oscillations must be addressed simultaneously.

[0105] The combined multi-nozzle hydrogen burner proposed in this invention achieves non-equidistant arrangement of flame heat release positions by adjusting the uniformity of the spacing of the premix tube spatial array in the main combustion stage. This is used to eliminate the pulsation phenomenon of collective heat release of the flame, reduce its response to oscillating combustion, and thus suppress thermoacoustic oscillation.

[0106] For example, the premixed tubes of the main combustion stage can be arranged in a non-equal spacing manner with radial or spiral lines. Of course, an equal spacing arrangement can also be selected according to the actual combustion conditions.

[0107] In this embodiment, there are multiple main combustion stage premixed tubes: the spatial arrangement of the main combustion stage premixed tubes is an asymmetric, non-periodic distribution of a spatial array.

[0108] Figure 3 A top view of the first arrangement of the main combustion stage region of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed, as shown below. Figure 3 As shown, the premixed tube array 19 of the main combustion stage is arranged asymmetrically and non-periodically in a spiral pattern. This spiral design optimizes the fuel-air mixture distribution within the combustion chamber, improving combustion efficiency. The asymmetrical and non-periodic design helps avoid hot spots or incomplete combustion within the combustion chamber.

[0109] like Figure 3 As shown, the pre-combustion stage blunt body 20, located in the central circular area, is the core part of the pre-combustion stage combustion zone. Its shape is relatively complex, containing multiple cut surfaces or slots, used for turbulence or flame stabilization, while guiding the pre-combustion stage flame to propagate to the main combustion stage area to ignite the main combustion stage.

[0110] The pre-burning blunt body 20 serves as a flame stabilizer, and its complex shape design helps to reduce flow rate fluctuations and prevent combustion instability.

[0111] The spatial arrangement of the main combustion stage premixed tube 19 includes a spiral pattern and a radial pattern.

[0112] Figure 4a A top view of the second arrangement of the main combustion stage region of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed, as shown below. Figure 4a As shown, the array of premixed tubes 19 in the main combustion stage is arranged in a non-equal spacing in a radial pattern.

[0113] The main combustion stage premixed tube 19 is arranged in multiple straight lines radiating outward from the center. The spacing between the main combustion stage premixed tubes 19 on each radial line gradually changes, forming an unequal spacing distribution.

[0114] The overall structure exhibits regular radial symmetry, but the spacing between the main combustion stage premixed tubes 19 within each radial line varies, with denser distribution on the inner side and sparser distribution on the outer side. The higher distribution density on the inner side improves the uniformity of fuel distribution in the core combustion zone, which is suitable for the stable control of the small flame core in the combustion chamber; the sparse arrangement on the outer side reduces the excessive richness of fuel distribution in the outer ring, avoiding overheating or incomplete combustion at the edges.

[0115] Figure 4b A top view of the third arrangement of the main combustion stage region of a combined multi-nozzle hydrogen burner according to an embodiment of the present invention is disclosed, as shown below. Figure 4b As shown, the array of premixed tubes 19 in the main combustion stage is arranged at equal intervals in a spiral pattern.

[0116] The main combustion stage premixed tubes 19 are arranged in a spiral pattern, with the spacing between each main combustion stage premixed tube 19 remaining consistent. The spiral gradually expands outward from the center, forming a circular and symmetrical distribution.

[0117] The evenly spaced spirals enable a more uniform mixing and distribution of fuel and air, reducing the generation of localized high-temperature zones within the combustion chamber.

[0118] In some embodiments, the internal airflow channel of the main combustion stage premixed pipe 19 is a straight circular pipe channel.

[0119] This invention proposes the following two types of main combustion stage premixed tubes 19. In the main combustion stage premixed tube 19, a microchannel is used to achieve rapid injection of hydrogen and air, reducing the risk of backfire in the fuel supply line within the premixed tube.

[0120] The cross-section of the main combustion stage premixed tube 19 adopts a petal-shaped design to strengthen the flow boundary layer at the outlet of the premixed tube and reduce the risk of backfire when the combustion chamber flame flows back into the premixed tube through the boundary layer.

[0121] By adjusting the number, size, angle, and channel length of the petals, different hydrogen mixing levels and mixture injection speeds can be achieved to meet the design requirements of different combustion chambers.

[0122] Figure 5a A schematic diagram of a petal-shaped, gradually expanding rotating flow channel according to an embodiment of the present invention is disclosed. Figure 5b for Figure 5a Schematic diagram of mid-section AA, as shown Figure 5a and Figure 5b As shown, the internal airflow channel of the main combustion stage premixed pipe 19 is a gradually expanding rotating channel with a petal-shaped cross-section.

[0123] The internal airflow channel can rotate at a certain angle and gradually expands along the axial direction, so that the main combustion stage hydrogen 12 and the main combustion stage air 7 will generate a rotational mixing effect when passing through, further improving the mixing uniformity.

[0124] The internal airflow channel length of the main combustion stage premixing pipe 19 is preferably 2mm-20mm, which can be adjusted according to combustion requirements to control the mixing distance and mixing efficiency.

[0125] The diameter of the main combustion stage hydrogen nozzle is preferably 0.3mm-1mm, which is used to precisely control the flow distribution of the main combustion stage hydrogen 12 and ensure combustion stability.

[0126] like Figure 5a and Figure 5b As shown, the main combustion stage premixing tube 19 combines a mixing structure with rotational and gradual diffusion characteristics. Through a complex internal geometry design, it significantly enhances the uniformity of the mixed gas, providing the main combustion stage burner with efficient and low-pollution combustion performance.

[0127] Figure 6a A schematic diagram of a petal-shaped tapered rotating flow channel according to an embodiment of the present invention is disclosed. Figure 6b for Figure 6a Schematic diagram of mid-section AA, as shown Figure 6a and Figure 6b As shown, the internal airflow channel of the main combustion stage premixed pipe 19 is a gradually narrowing rotating channel with a petal-shaped cross-section.

[0128] The internal airflow channel gradually narrows from the inlet to the outlet, which enhances the kinetic energy of the gas and increases the intensity of turbulence.

[0129] The internal airflow channel can rotate at a certain angle, and the channel wall is designed with rotational characteristics. The airflow generates rotational motion while contracting, which further enhances the mixing effect of the main combustion stage hydrogen 12 and the main combustion stage air 7.

[0130] The petal-shaped flow channel cross-section can optimize the rotation path and improve mixing efficiency.

[0131] The internal airflow channel length of the main combustion stage premixing pipe 19 is preferably 2mm-20mm, which can be adjusted according to combustion requirements to control the mixing distance and mixing efficiency.

[0132] The diameter of the main combustion stage hydrogen nozzle is preferably 0.3mm-1mm, which is used to precisely control the flow distribution of the main combustion stage hydrogen 12 and ensure combustion stability.

[0133] The aforementioned petal-shaped, gradually expanding rotating flow channel tends to improve mixing uniformity and is suitable for a wider range of applications; the petal-shaped, gradually contracting rotating flow channel enhances gas kinetic energy and turbulence intensity, making it more suitable for combustion environments with high requirements for flow rate and turbulence.

[0134] If the main combustion stage premixing tube 19 adopts the above-mentioned petal-shaped gradually expanding / contracting rotating flow channel, there are specific requirements for the number and arrangement of the main combustion stage premixing tube array.

[0135] In this embodiment, the number of main combustion stage premixed tube arrays is preferably 3-12.

[0136] Figure 7a A first schematic diagram of a combustion chamber with a petal-shaped main combustion stage premixed tube array according to an embodiment of the present invention is disclosed, as shown below. Figure 7a As shown, all the main combustion stage premixing tubes 19 are arranged in a uniform manner, forming a regular array. This layout facilitates the uniform mixing of fuel and oxidizer, making it suitable for more stable combustion conditions.

[0137] Figure 7b A second schematic diagram of a combustion chamber with a petal-shaped main combustion stage premixed tube array according to an embodiment of the present invention is disclosed, as shown below. Figure 7b As shown, all the main combustion stage premixed tubes 19 are arranged in a ring, with a hollow central area. The ring structure can be used for centralized combustion or to reserve space for specific combustion needs.

[0138] like Figure 7a and Figure 7b As shown, the combustion chamber adopts a premixed tube array structure with petal-shaped main combustion stage, which improves the combustion effect through flexible arrangement and adapts to different operating conditions. While ensuring mixing efficiency, it supports a stable and reliable combustion process.

[0139] The present invention provides a combined multi-nozzle hydrogen burner and a hydrogen combustion chamber, which specifically have the following features:

[0140] Beneficial effects:

[0141] 1) By combining the local micro-flame of hydrogen combustion with the spatial arrangement of the central stage, several micro-flames are classified into pre-combustion stage area and main combustion stage area. By selectively activating the main combustion stage and pre-combustion stage, it can adapt to the wide operating conditions of the combustion chamber of aero-engine and gas turbine and ensure that the combustion chamber outlet temperature distribution achieves the expected effect.

[0142] 2) A basic structure is proposed, which uses a micro-jet flame as the pre-combustion stage and a micro-premixed flame as the main combustion stage, to achieve a combustion process with low NOx emissions;

[0143] 3) A micro-mixing channel with a petal-shaped structure in the main combustion stage premixing pipe is proposed, which helps to increase the flow velocity of the boundary layer, effectively suppress backfire and enhance the efficiency of mixed combustion.

[0144] 4) By adopting a non-equally spaced array of main combustion stage premixed tubes and a ramp boss structure inside the premixed tubes, thermoacoustic oscillations can be effectively suppressed.

[0145] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0146] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more, unless explicitly defined otherwise.

[0147] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0148] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," and "bottom" are used interchangeably.

[0149] The orientation or positional relationship indicated by terms such as "inner", "clockwise", and "counterclockwise" is based on the orientation or positional relationship shown in the accompanying drawings and is only for the purpose of facilitating the description of the present invention and simplifying the description. It is not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0150] The above embodiments are provided for those skilled in the art to implement or use the present invention. Those skilled in the art can make various modifications or changes to the above embodiments without departing from the inventive concept of the present invention. Therefore, the protection scope of the present invention is not limited to the above embodiments, but should be the maximum scope that conforms to the innovative features mentioned in the claims.

Claims

1. A combined multi-nozzle hydrogen burner, characterized by, The structure adopts a centrally graded design, including a pre-combustion stage area and a main combustion stage area: The pre-combustion stage zone is located at the center of the burner, forming a pre-combustion stage flame; The main combustion stage region is located outside the pre-combustion stage, forming the main combustion stage flame; Selectively open the pre-combustion zone and / or the main combustion zone according to the operating conditions.

2. The combined multi-jet hydrogen burner of claim 1, wherein, The pre-combustion stage area includes annularly arranged micro-jet nozzles; The main combustion stage region includes multiple premixed nozzles arranged in an array, each equipped with a premixing tube.

3. The combined multi-jet hydrogen burner of claim 2, wherein, The main combustion stage region includes at least a main combustion stage hydrogen pipe, a main combustion stage hydrogen chamber, and a main combustion stage premixing pipe: The main combustion stage hydrogen pipe is connected to the main combustion stage hydrogen chamber and provides main combustion stage hydrogen fuel to the main combustion stage flame. The main combustion stage premixing pipe passes through the main combustion stage hydrogen chamber, and its upstream end is used to introduce main combustion stage air. The main combustion stage premixing pipe has a main combustion stage hydrogen injection hole on its side wall for introducing main combustion stage hydrogen. The main combustion stage hydrogen chamber is connected to the main combustion stage hydrogen pipe and the main combustion stage hydrogen nozzle, and stores and distributes the main combustion stage hydrogen to the main combustion stage hydrogen nozzle. The main combustion stage premixing tube serves as a premixing nozzle, mixing the main combustion stage hydrogen with the main combustion stage air.

4. The combined multi-jet hydrogen burner of claim 3, wherein, The main combustion stage region also includes a main combustion stage ramp boss: The main combustion stage ramp protrusion is located on the side wall of the internal air flow channel of the main combustion stage premixing pipe, upstream of the hydrogen injection hole of the main combustion stage.

5. The combined multi-jet hydrogen burner of claim 3, wherein, The number of the main combustion stage premixed tubes is multiple: The spatial arrangement of the premixed tubes in the main combustion stage is an asymmetric, non-periodic distribution of a spatial array.

6. The combined multi-jet hydrogen burner according to claim 3 or 5, characterized in that The spatial arrangement of the main combustion stage premixed tubes includes a spiral arrangement and a radial arrangement.

7. The modular multi-jet hydrogen burner of claim 3, wherein, The internal airflow channel of the main combustion stage premixed pipe is a gradually expanding rotating channel or a gradually contracting rotating channel, and the cross-sectional shape of the channel is petal-shaped.

8. The combined multi-jet hydrogen burner of claim 7, wherein, The internal airflow channel length of the main combustion stage premixed pipe is 2mm-20mm, and the diameter of the main combustion stage hydrogen nozzle is 0.3mm-1mm.

9. The combined multi-nozzle hydrogen burner according to claim 7, characterized in that, The number of premixed tube arrays in the main combustion stage is 3-12.

10. The combined multi-nozzle hydrogen burner according to claim 3, characterized in that, The internal airflow channel of the main combustion stage premixed pipe is a straight circular pipe channel.

11. The combined multi-nozzle hydrogen burner according to claim 1, characterized in that, The pre-combustion stage region includes at least a pre-combustion stage hydrogen pipe, a pre-combustion stage hydrogen nozzle, a pre-combustion stage throat flow channel, and a pre-combustion stage blunt body: The pre-combustion stage hydrogen pipe is connected to the pre-combustion stage hydrogen nozzle to provide pre-combustion stage hydrogen to the pre-combustion stage flame; The pre-combustion stage hydrogen nozzle is located at the end of the pre-combustion stage hydrogen pipe and surrounds the pre-combustion stage blunt body in an annular shape. The pre-combustion stage throat channel is located outside the pre-combustion stage hydrogen nozzle and the pre-combustion stage blunt body, and is used to introduce pre-combustion stage air and mix it with pre-combustion stage hydrogen. The pre-combustion stage blunt body is located at the center of the pre-combustion stage flame combustion zone; The pre-combustion stage hydrogen nozzle is combined with the pre-combustion stage throat channel to form a micro-jet nozzle.

12. A hydrogen combustion chamber, characterized in that, It includes at least the fuel supply line, nozzle assembly, combustion chamber flame tube, and combustion chamber shell: The fuel supply line is connected to the nozzle assembly and is used to supply hydrogen fuel to the nozzle assembly; The nozzle assembly is connected upstream to the fuel supply line and downstream to the inlet of the combustion chamber flame tube, where it injects hydrogen fuel and mixes it with air to form a mixture. The combustion chamber flame tube, which is integral with the combustion chamber shell, serves as the combustion zone to contain the mixture for combustion. The nozzle assembly is a combined multi-nozzle hydrogen burner as described in any one of claims 1 to 11.

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