A burner for pure hydrogen and hydrogen-rich gas turbines and a method of using the same

Abstract

The application discloses a pure hydrogen and hydrogen-rich gas turbine burner and a use method thereof, and relates to the field of gas turbines, in particular to a pure hydrogen and hydrogen-rich gas turbine burner and a use method thereof.The burner comprises a nozzle, a nozzle integrated plate and a flame tube. The flame tube is provided with the nozzle integrated plate at one end. The nozzle integrated plate is provided with mounting holes matched with fuel nozzles. The mounting holes can be arranged in a ring shape, a sector shape, a circular shape and the like according to design requirements to realize flexible control of a target of the burner in stages and in zones. The nozzle is arranged in the mounting hole and used for spraying a fuel and air mixture into the flame tube. The burner has the advantages that: by reasonably arranging the nozzles and matching the flame tube, a target flame shape, an anchoring position, a flame temperature and a flame residence time are realized, stable combustion with low NOx emission, no tempering and no thermal acoustic oscillation is effectively realized, and the like. x

Description

Technical Field

[0001] This invention relates to the field of gas turbines, and more specifically to a burner for pure hydrogen and hydrogen-rich gas turbines and its usage method. Background Technology

[0002] Hydrogen fuel is the best intermediate material in the development of gas turbines towards low-carbon and even zero-carbon processes, as its complete combustion produces only water. However, compared to traditional gas turbine fuels such as natural gas, hydrogen has characteristics such as low density, fast flame propagation speed, short extinguishing distance, high adiabatic flame temperature, and high flammability and explosiveness.

[0003] The following technical obstacles exist in the application of hydrogen fuel in conventional combustion systems of gas turbines:

[0004] (1) At high intake temperatures, the high reactivity of hydrogen greatly increases the risk of backfire in the premixed combustion system, which in turn causes serious damage to upstream components and affects the operation of the entire combustion system.

[0005] (2) Because hydrogen flames have high adiabatic flame temperatures, and NOx increases exponentially with flame temperature, NOx emissions will increase. In addition, the introduction of hydrogen will increase the concentration of activated molecules in the NOx generation chemical reaction, thereby exacerbating NOx generation. This makes it significantly more difficult to control hydrogen NOx emissions.

[0006] (3) Hydrogen flames have a fast propagation speed and a more compact heat-releasing structure. They are more likely to be strongly coupled with acoustic modes during changes in operating conditions. In addition, the flame transfer function of hydrogen fuel has a large gain over a fairly wide frequency range. Therefore, hydrogen fuel is more prone to thermoacoustic oscillations, which poses a huge challenge to burner design and operation. Summary of the Invention

[0007] The purpose of this invention is to provide a burner for pure hydrogen and hydrogen-rich gas turbines and its usage method, addressing the aforementioned problems.

[0008] The technical solution adopted in this invention is as follows:

[0009] A burner for pure hydrogen and hydrogen-rich gas turbines includes:

[0010] The device includes a fuel nozzle, a nozzle integration plate, and a flame tube. The flame tube has a nozzle integration plate at one end, and the nozzle integration plate has a connection hole that matches the fuel nozzle. The fuel nozzle is installed in the connection hole and is used to inject fuel into the flame tube. The nozzle integration plate is divided into multiple sections, and the connection holes in each section can be opened or closed uniformly.

[0011] Furthermore, the fuel nozzles and connection holes include multiple ones, arranged in an array on the nozzle integration plate.

[0012] Furthermore, the nozzle integration plate is configured as a plate-like structure with a certain thickness.

[0013] Furthermore, the nozzle integration plate is composed of several hollow circular rings tightly fitted together.

[0014] Furthermore, the annulus has a connection hole on the side near the fuel nozzle and an injection hole on the side near the flame tube.

[0015] Furthermore, the injection orifice is equipped with a valve that can control its opening and closing.

[0016] Furthermore, a central blunt body is provided at the connection between the fuel nozzle and the connection hole to stabilize the fuel flow.

[0017] Furthermore, the central blunt body is configured with a blade structure that matches the connecting hole. The blade includes an impact side and a guide side, with the impact side being narrower than the guide side. The guide side is used for fuel diversion.

[0018] Furthermore, the nozzle integration plate is provided with cooling holes for introducing cold air.

[0019] Furthermore, a method for using a burner for a pure hydrogen and hydrogen-rich gas turbine includes the following steps:

[0020] S1: Determine the number, arrangement, and spacing of the connection holes and injection holes on the nozzle integration plate according to the power required by the gas turbine;

[0021] S2: After ignition and combustion, observe whether the flame forms a stable, discrete small flame, and whether the flame temperature, flame dwell time, and anchoring position are in a stable state.

[0022] S3: If the flame state is unstable, it can be stabilized by adjusting the valve of the connection hole or the injection hole.

[0023] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0024] (1) Set a central blunt body to stabilize the fuel-air mixture that is ejected, so that the fuel is ignited and then forms a stable, anchored flame to ensure the combustion efficiency in the flame tube;

[0025] (2) The fuel nozzles are arranged in a square array, which can make the fuel evenly injected into the flame tube. Fuel is sprayed out at all parts of the nozzle integration plate, ensuring the fuel utilization rate.

[0026] (3) The hollow ring can make the flame more dispersed and achieve better combustion effect. The hollow ring structure makes the fuel in one ring interconnected, reducing the cost of fuel nozzles and improving the combustion efficiency of the flame.

[0027] (4) Ensure fuel utilization, flame temperature, flame residence time and anchoring position to effectively achieve low NO x Stable combustion with no emissions, no backfire, and no thermoacoustic oscillations. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of the present invention;

[0029] Figure 2 This is a schematic diagram of the nozzle integration plate of the present invention;

[0030] Figure 3 This is a schematic diagram of the integrated structure of the central control annular nozzle of the present invention;

[0031] Figure 4 This is a schematic diagram of the fuel nozzle structure of the present invention.

[0032] The markings in the diagram are: 1 - fuel nozzle, 2 - nozzle integration plate, 3 - flame tube, 4 - connection hole, 5 - central blunt body, 6 - hollow ring, 7 - injection hole, 8 - valve, 9 - air impact side, 10 - air guide side.

[0033] Specific examples

[0034] The present invention will now be described in detail with reference to the accompanying drawings.

[0035] 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 merely illustrative and not intended to limit the invention.

[0036] Example 1

[0037] In this embodiment, as Figure 1 and Figure 2As shown, a burner for pure hydrogen and hydrogen-rich gas turbines includes: a fuel nozzle 1, a nozzle integration plate 2, and a flame tube 3. The nozzle integration plate 2 is located at one end of the flame tube 3. The nozzle integration plate 2 has a connection hole 4 that matches the fuel nozzle 1. The fuel nozzle 1 is located at the connection hole 4 for injecting fuel into the flame tube 3. A central blunt body 5 is provided at the connection point between the fuel nozzle 1 and the connection hole 4 to stabilize the fuel flow. The nozzle integration plate 2 is located at one end of the flame tube 3, sealing one end of the flame tube 3 to ensure a relatively closed environment during combustion, preventing interference from the external environment or other airflows that could affect flame combustion. Unstable; the nozzle integration plate 2 is provided with a connection hole 4 that matches the fuel spraying end of the fuel nozzle 1. In this embodiment, a threaded connection is adopted. The outer side of the fuel spraying end of the fuel nozzle 1 is provided with threads, and correspondingly, the inner sidewall of the connection hole 4 is also provided with threads. When installing the fuel nozzle 1, it is only necessary to rotate the fuel nozzle 1 into the corresponding connection hole 4. Furthermore, a rubber gasket can be provided at the threaded end of the fuel nozzle 1. In this way, it can be ensured that after installation, when the fuel nozzle 1 sprays fuel, a seal is formed around it and at the connection point of the connection hole 4 to prevent fuel leakage, which could lead to insufficient fuel and the generation of NO. x This can lead to incomplete combustion or other safety hazards. A central blunt body 5 is provided at the connection between the fuel nozzle 1 and the connecting hole 4 to stabilize the fuel flow. Since the fuel injected into the fuel nozzle 1 is a mixture of hydrogen fuel and air,

[0038] Furthermore, the fuel nozzles 1 and connecting holes 4 are multiple and arranged in an array on the nozzle integration plate 2. In order to fully utilize space and ensure complete combustion of fuel during the operation of the flame tube 3, multiple fuel nozzles 1 and connecting holes 4 are provided in this embodiment. This arrangement ensures that the fuel supply reaches the specified value. Furthermore, the fuel nozzles 1 and connecting holes 4 are arranged in an array on the nozzle integration plate 2. In this embodiment, the fuel nozzles 1 are arranged in a square array. The advantage of this arrangement is that it allows fuel to be evenly injected into the flame tube 3, ensuring fuel is ejected from all parts of the nozzle integration plate 2, guaranteeing fuel utilization, flame temperature, flame residence time, and anchoring position, effectively achieving low NO₂ levels. x Stable combustion with no emissions, no backfire, and no thermoacoustic oscillations.

[0039] Furthermore, the nozzle integration plate 2 is configured as a plate-like structure with a certain thickness. In this embodiment, the nozzle integration plate 2 is made of a high-temperature resistant metal plate with a certain thickness. The advantages of this configuration are: it can provide heat insulation and flame retardancy, effectively preventing heat leakage during combustion in the flame tube 3, and facilitating the installation of threads to make the connection with the fuel nozzle 1 tighter and more secure. This configuration also allows the unstable airflow ejected from the fuel nozzle 1 to remain stable when passing through the nozzle integration plate 2, ensuring fuel utilization, flame temperature, flame residence time, and anchoring position, effectively achieving low NOx emissions. x Stable combustion with no emissions, no backfire, and no thermoacoustic oscillations.

[0040] Furthermore, typically, since the fuel nozzle 1 adopts a regular columnar structure, the fuel may not mix evenly with the air. Therefore, a central blunt body 5 is provided at the connection between the fuel nozzle 1 and the connecting hole 4 to stabilize the ejected fuel-air mixture, so that the fuel is ignited and forms a stable, anchored flame to ensure the combustion efficiency in the flame tube 3. The central blunt body 5 is set as a blade structure that matches the connecting hole 4. In this embodiment, in order to fully stabilize the fuel-air mixture in the fuel nozzle 1 before it enters the flame tube 3, the central blunt body 5 is set as a three-blade structure, with all three blades abutting against the fuel nozzle 1. In this way, the fuel-air mixture in the entire cross-section of the fuel nozzle 1 can be fully ballasted. The three-blade structure can ensure the effect of stabilizing the airflow without causing excessive obstruction to the airflow.

[0041] Furthermore, the blade includes an impact side 9 and a guide side 10, with the impact side 9 being narrower than the guide side 10. The guide side 10 is used for fuel guidance. In this embodiment, as shown... Figure 4 As shown, to prevent the fuel-air mixture from being excessively obstructed and rebounding when passing through the central blunt body 5, thus avoiding interference with the main airflow and achieving the opposite effect, the blade's impact side 9 is made as narrow as possible to reduce the impact surface. The guide side 10 is the blade side with the same airflow direction. In this way, the central blunt body 5 can effectively guide and stabilize the fuel-air mixture, ensuring its fuel utilization rate, flame temperature, flame residence time, and anchoring position, effectively achieving low NO. x Stable combustion with no emissions, no backfire, and no thermoacoustic oscillations; furthermore, the air guide side 10 can also be set with a certain curvature to rotate it when the fuel-air mixture passes through, increasing the flow rate and further mixing the hydrogen-containing fuel and air.

[0042] Furthermore, a method for using a burner for a pure hydrogen and hydrogen-rich gas turbine includes the following steps:

[0043] S1: Determine the number, arrangement and spacing of the connecting holes 4 and injection holes 7 on the nozzle integration plate 2 according to the power required by the gas turbine;

[0044] S2: After ignition and combustion, observe whether the flame forms a stable, discrete small flame, and whether the flame temperature, flame dwell time, and anchoring position are in a stable state.

[0045] S3: If the flame state is unstable, it can be stabilized by adjusting the valve 8 of the connection hole 4 or the injection hole 7.

[0046] Example 2

[0047] Based on Embodiment 1, the nozzle integration plate 2 is composed of several hollow circular rings 6 tightly fitted together, such as... Figure 3 As shown, several hollow rings 6 are nested together, and the gaps at their joints can be welded to keep them sealed and relatively fixed. Due to the special hollow structure of the rings, the fuel nozzles 1 connected in the same ring can spray into one ring and then into the flame tube 3 from the other end. In this way, the difference in the amount of fuel spray that may occur between the fuel nozzles 1 can be balanced. The fuel nozzle 1 that sprays more fuel can supplement the fuel nozzle 1 that sprays less fuel, all thanks to the interconnected hollow rings 6.

[0048] Furthermore, the annulus has a connecting hole 4 on the side near the fuel nozzle 1 and an injection hole 7 on the side near the flame tube 3. In this embodiment, the number of connecting holes 4 and the number of injection holes 7 may not be the same. For example, 10 connecting holes 4 are arranged in a circumferential array on one side of the same annulus to connect 10 fuel nozzles 1, and 20 injection holes 7 are set on the other side. In this way, the flame can be generated more dispersed when using fewer fuel nozzles 1, achieving a better combustion effect. The advantage of this arrangement is that the structure of the hollow annulus 6 allows the fuel in one annulus to be interconnected, reducing the cost of the fuel nozzles 1 and improving the combustion efficiency of the flame.

[0049] Furthermore, the injection orifice 7 is equipped with a valve 8 that can control its opening and closing. The valve can control the opening degree and flow rate of each injection orifice, or achieve the function of zoned control when required.

[0050] Furthermore, the addition of cooling vents allows cool air to enter the flame tube, preventing overheating, backfire, thermoacoustic oscillations, and other abnormal phenomena. This reduces the machine's workload, ensures fuel efficiency, and optimizes flame temperature, residence time, and anchoring position, effectively achieving low NOx emissions. x Emissions.

[0051] Example 3

[0052] The nozzle integration plate 2 is divided into multiple sections, and the connection holes 4 in each section can be opened or closed uniformly. In order to simplify the working procedure, each connection hole 4 can be connected to the fuel nozzle 1. When different flame combustion compositions are required, the opening or closing can be controlled by the valve 8 of the connection hole 4.

[0053] When the valve 8 structure is applied in Embodiment 1, it can be divided into several sector areas according to combustion needs, for example, by dividing the array arrangement and the connection holes 4 on the nozzle integration plate 2 into several sector areas. During ignition, by controlling the valve 8, each sector area can work in turn, reducing the machine load, ensuring its fuel utilization rate, as well as flame temperature, flame residence time and anchoring position, effectively achieving low NO x Stable combustion with no emissions, no backfire, and no thermoacoustic oscillations.

[0054] When the valve 8 structure is applied in Embodiment 2, the valves 8 of the connecting holes 4 and the injection holes 7 within the same ring can be opened, while the others are closed. This allows for alternating ignition of different rings, reducing the machine's workload, ensuring fuel utilization, and controlling flame temperature, flame residence time, and anchoring position, effectively achieving low NO₂ levels. x Stable combustion with no emissions, no backfire, and no thermoacoustic oscillations.

[0055] Example 3

[0056] When the flame tube is annular, the nozzle integration plate is correspondingly set as a ring, with the connecting holes on the nozzle integration plate arranged in a circular array. Preferably, the nozzle integration plate adopts a hollow ring structure, with the connecting holes and injection holes arranged in a circular array. The advantage of this setting is that it allows the nozzle integration plate to better fit the shape of the flame tube, reducing the machine load, ensuring fuel utilization, and effectively achieving low NOx emissions by controlling flame temperature, flame residence time, and anchoring position. x Stable combustion with no emissions, no backfire, and no thermoacoustic oscillations.

[0057] The above description is merely a preferred embodiment of the invention and is not intended to limit the invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the invention should be included within the scope of protection of the invention.

Claims

1. A burner for pure hydrogen and hydrogen-rich gas turbines, characterized in that: include: The assembly includes a fuel nozzle (1), a nozzle integration plate (2), and a flame tube (3). The flame tube (3) has a nozzle integration plate (2) at one end. The nozzle integration plate (2) has a connection hole (4) that matches the fuel nozzle (1). The fuel nozzle (1) is located in the connection hole (4) and is used to inject fuel into the flame tube (3). The nozzle integration plate (2) is divided into multiple sections, and the connection holes (4) in each section can be opened or closed uniformly. The fuel nozzle (1) and the connecting hole (4) include multiple parts, which are arranged in an array on the nozzle integration plate (2); The nozzle integration plate (2) is composed of several hollow circular rings (6) tightly fitted together; The ring has a connecting hole (4) on the side near the fuel nozzle (1) and an injection hole (7) on the side near the flame tube (3).

2. The burner for pure hydrogen and hydrogen-rich gas turbines according to claim 1, characterized in that: The injection hole (7) is equipped with a valve (8) that can control its opening and closing.

3. The burner for pure hydrogen and hydrogen-rich gas turbines according to claim 1, characterized in that: A central blunt body (5) for stabilizing fuel flow is provided at the connection between the fuel nozzle (1) and the connection hole (4).

4. The burner for pure hydrogen and hydrogen-rich gas turbines according to claim 3, characterized in that: The central blunt body (5) is configured as a blade structure that matches the connecting hole (4). The blade includes an impact side (9) and a guide side (10). The impact side (9) is narrower than the guide side (10). The guide side (10) is used for fuel flow.

5. A burner for pure hydrogen and hydrogen-rich gas turbines according to claim 1, characterized in that: The nozzle integration plate (2) is provided with cooling holes for introducing cold air.

6. A method of using a burner for pure hydrogen and hydrogen-rich gas turbines, applied to the burner for pure hydrogen and hydrogen-rich gas turbines as described in any one of claims 1-5, characterized in that: Includes the following steps: S1: Determine the number, arrangement and spacing of the connecting holes (4) and injection holes (7) on the nozzle integration plate (2) according to the power required by the gas turbine; S2: After ignition and combustion, observe whether the flame forms a stable, discrete small flame, and whether the flame temperature, flame dwell time, and anchoring position are in a stable state. S3: If the flame state is unstable, it can be stabilized by adjusting the valve (8) of the connection hole (4) or the injection hole (7).

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