Combustion chamber flame tube and flame tube manufacturing method suitable for pure hydrogen gas turbine

Abstract

The embodiment of the present disclosure discloses a combustion chamber flame tube and a flame tube manufacturing method suitable for a pure hydrogen gas turbine. A specific implementation of the combustion chamber flame tube includes: the flame tube body includes a head cooling section, a heat exchange rib segment and a tail cooling section, the head cooling section is provided with at least one head cooling groove, the tail cooling section is provided with at least one tail cooling groove, the outer side of the heat exchange rib segment is provided with at least one heat exchange rib, the head cooling section includes a connecting assembly, the connecting assembly is used to connect the head cooling section with the combustion chamber main nozzle; the flame tube guide bushing includes a bushing body and a fixing assembly, the bushing body and the fixing assembly are fixedly connected, and the fixing assembly is used to detachably connect the bushing body with the combustion chamber casing; the flame tube body is arranged inside the bushing body, and a preset annular cavity spacing is arranged between the flame tube body and the bushing body; at least one mixing hole is opened on the flame tube body. This implementation can reduce the emission of nitrogen oxides in the combustion chamber.

Description

Technical Field

[0001] The embodiments of the present disclosure relate to the technical field of gas turbines, and in particular to a combustion chamber flame tube and a flame tube manufacturing method applicable to a pure hydrogen gas turbine. Background Art

[0002] The flame tube of the combustion chamber of a pure hydrogen gas turbine is used to prevent the high-temperature combustion products from affecting the combustion chamber casing and shaft. The cooling of the flame tube wall temperature is of great significance to the combustion stability of the combustion chamber. At present, when designing the cooling structure of the flame tube of the combustion chamber, the commonly used method is: designing slots on the flame tube and cooling the flame tube wall by slot air film cooling.

[0003] However, the inventors have discovered that when the cooling structure of the flame tube of the combustion chamber is designed in the above manner, the following technical problems often occur: the flame tube uses slot air film cooling to cool the wall, and the required cooling air accounts for a high proportion of the total gas volume, resulting in a low proportion of air entering from the head to participate in the combustion, and the equivalent of the main combustion zone of the combustion chamber is relatively high, resulting in a higher combustion temperature, which causes more nitrogen oxides to be emitted from the combustion chamber.

[0004] When adopting a technical solution to solve the technical problem 1 in the background technology, the following problem often arises: how to determine the position of the mixing hole to improve the uniformity of the combustion chamber temperature. In response to these problems, the conventional solution is generally to manually set the position and shape of the mixing hole based on experience. However, the above solution has the following technical problem 2: the hydrogen content of the fuel in the pure hydrogen gas turbine is relatively high, and hydrogen is relatively active. The position of the mixing hole is set based on the experience of hydrogen-blended fuel, resulting in a longer residence time of the fuel in the pure hydrogen gas turbine in the combustion chamber, resulting in lower stability of the combustion gas.

[0005] The above information disclosed in this Background section is only for enhancement of understanding of the background of the inventive concept and therefore it may contain information that does not form the prior art that is already known in this country to a person of ordinary skill in the art. Summary of the invention

[0006] The content of this disclosure is used to introduce concepts in a brief form, which will be described in detail in the detailed implementation section below. The content of this disclosure is not intended to identify the key features or essential features of the technical solution claimed for protection, nor is it intended to limit the scope of the technical solution claimed for protection.

[0007] Some embodiments of the present disclosure propose a combustion chamber flame tube and a combustion chamber flame tube manufacturing method suitable for a pure hydrogen gas turbine to solve the technical problems mentioned in the above background technology section.

[0008] In a first aspect, some embodiments of the present disclosure provide a combustion chamber flame tube suitable for a pure hydrogen gas turbine, the combustion chamber flame tube comprising: the flame tube body comprises a head cooling section, a heat exchange rib segment and a tail cooling section, the inner side surface of the head cooling section is provided with at least one head cooling groove, the outer side surface of the tail cooling section is provided with at least one tail cooling groove, the outer side surface of the heat exchange rib segment is provided with at least one heat exchange rib, the head cooling section comprises a connecting assembly, the connecting assembly is used to connect the head cooling section with the combustion chamber main nozzle; the flame tube guide sleeve comprises a sleeve body and a fixing assembly, the sleeve body and the fixing assembly are fixedly connected, the fixing assembly is used to detachably connect the sleeve body with the combustion chamber casing; the flame tube body is arranged inside the sleeve body, a preset annular cavity spacing is provided between the flame tube body and the sleeve body; at least one mixing hole is opened on the flame tube body.

[0009] Optionally, the preset annular cavity spacing ranges from 30 to 40 mm, the fin height of each heat exchange fin included in the at least one heat exchange fin ranges from 2 to 4 mm, and the fin spacing between each heat exchange fin is 18 to 22 mm.

[0010] Optionally, the opening angle of each heat exchange fin on the outer side surface of the heat exchange fin segment is 90 degrees.

[0011] Optionally, each heat exchange fin is provided with a chamfer.

[0012] Optionally, the center points of the mixing holes included in the at least one mixing hole are located on the same horizontal plane, and the distance between the center point of the mixing hole and the center point of the head is in the range of 250 to 260 mm, and the ratio of the total area of ​​the mixing holes of each mixing hole to the total area of ​​the micro-mixing tube of the combustion chamber is a preset first area ratio.

[0013] Optionally, the ratio of the head flow area, the tail flow area and the total area of ​​the combustion chamber micro-mixing tube is a preset second area ratio, the above-mentioned head flow area is the sum of the areas of each head cooling groove of each head cooling groove, and the above-mentioned tail flow area is the sum of the areas of each tail cooling groove of each tail cooling groove.

[0014] In a second aspect, some embodiments of the present disclosure provide a method for manufacturing a combustion chamber flame tube, which is applied to a combustion chamber flame tube suitable for a pure hydrogen gas turbine described in any implementation of the first aspect, the method comprising: determining initial heat exchange fin parameter information, and performing the following simulation steps: constructing a first initial flame tube three-dimensional model according to the initial heat exchange fin parameter information and preset flame tube size information; simulating the first initial flame tube three-dimensional model according to a preset first fluid simulation model set to obtain first simulation information, wherein the first simulation information includes a flow field distribution diagram and a simulated gas average velocity; performing a trapped vortex test on the flow field distribution diagram. The method comprises the steps of: performing measurement processing to obtain a trapped vortex detection result; generating a simulated Reynolds number, a simulated heat transfer roughness and a simulated roughness according to the simulated gas average velocity and the initial heat exchange fin parameter information; in response to determining that the above-mentioned trapped vortex detection result, the above-mentioned simulated Reynolds number, the above-mentioned simulated heat transfer roughness and the above-mentioned simulated roughness meet the preset verification conditions, determining the initial heat exchange fin parameter information as the heat exchange fin parameter information; determining the flame tube head and tail area ratio information; determining the flame tube mixing hole information; and controlling the associated flame tube manufacturing device to perform the flame tube manufacturing operation according to the above-mentioned heat exchange fin parameter information, the above-mentioned flame tube mixing hole information and the above-mentioned flame tube head and tail area ratio information.

[0015] Optionally, the above-mentioned simulation step also includes: in response to determining that the above-mentioned trapped vortex detection results, the above-mentioned simulated gas average velocity, the above-mentioned simulated heat transfer roughness and the above-mentioned simulated roughness do not meet the above-mentioned preset verification conditions, adjusting the initial heat exchange fin parameter information to obtain updated heat exchange fin parameter information, and using the updated heat exchange fin parameter information as the initial heat exchange fin parameter information, and continuing to execute the above-mentioned simulation step.

[0016] Optionally, the above-mentioned determination of the flame tube head and tail area ratio information includes: determining the preset flame tube head and tail area ratio information as the initial flame tube head and tail area ratio information, and performing the following simulation steps: constructing a second initial flame tube three-dimensional model according to the initial flame tube head and tail area ratio information and the above-mentioned heat exchange fin parameter information; simulating the above-mentioned second initial flame tube three-dimensional model according to a preset second fluid simulation model set to obtain second simulation information, wherein the above-mentioned second simulation information includes a simulated flame tube wall temperature; in response to determining that the above-mentioned simulated flame tube wall temperature meets the preset temperature verification condition, determining the initial flame tube head and tail area ratio information as the flame tube head and tail area ratio information.

[0017] Optionally, in response to determining that the simulated flame tube wall temperature does not meet the preset temperature verification condition, the initial flame tube head and tail area ratio information is adjusted to obtain updated flame tube head and tail area ratio information, and the updated flame tube head and tail area ratio information is used as the initial flame tube head and tail area ratio information to continue executing the above simulation steps.

[0018] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: through the combustion chamber flame tube applicable to the pure hydrogen gas turbine of some embodiments of the present disclosure, the emission of nitrogen oxides in the combustion chamber can be reduced. Specifically, the reason for the high emission of nitrogen oxides in the combustion chamber is that the flame tube adopts slot air film cooling for wall cooling, and the required cooling air accounts for a high proportion of the total gas volume, resulting in a low proportion of air entering from the head to participate in combustion, and the equivalent of the main combustion zone of the combustion chamber is relatively high, resulting in a high combustion temperature, thereby causing more nitrogen oxides to be emitted from the combustion chamber. Based on this, some embodiments of the present disclosure are suitable for a combustion chamber flame tube of a pure hydrogen gas turbine, which combustion chamber flame tube includes: the above-mentioned flame tube main body includes a head cooling section, a heat exchange rib segment and a tail cooling section, the inner side surface of the above-mentioned head cooling section is provided with at least one head cooling groove, the outer side surface of the above-mentioned tail cooling section is provided with at least one tail cooling groove, the outer side surface of the above-mentioned heat exchange rib segment is provided with at least one heat exchange rib, the above-mentioned head cooling section includes a connecting assembly, and the above-mentioned connecting assembly is used to connect the above-mentioned head cooling section with the combustion chamber main nozzle; the above-mentioned flame tube guide sleeve includes a sleeve main body and a fixing assembly, the above-mentioned sleeve main body and the above-mentioned fixing assembly are fixedly connected, and the above-mentioned fixing assembly is used to detachably connect the above-mentioned sleeve main body with the combustion chamber casing; the above-mentioned flame tube main body is arranged inside the above-mentioned sleeve main body, and a preset annular cavity spacing is arranged between the above-mentioned flame tube main body and the above-mentioned sleeve main body; at least one mixing hole is opened on the above-mentioned flame tube main body. Because the combustion chamber flame tube can improve the convective heat transfer effect of the flame tube wall through the heat exchange rib segments, and at the same time, the head cooling slots and the tail cooling slots are combined to achieve air film cooling at both ends, so that the flame tube wall temperature can be cooled. Also, because the convective heat transfer through the heat exchange rib segments replaces the traditional wall air film cooling method, the amount of air used for cooling can be reduced, and then the combustion temperature can be reduced, thereby reducing the emission of nitrogen oxides in the combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and other features, advantages and aspects of the embodiments of the present disclosure will become more apparent with reference to the following detailed description in conjunction with the accompanying drawings. Throughout the accompanying drawings, the same or similar reference numerals represent the same or similar elements. It should be understood that the drawings are schematic and that components and elements are not necessarily drawn to scale.

[0020] Figure 1It is a schematic structural diagram of some embodiments of a combustion chamber flame tube applicable to a pure hydrogen gas turbine according to the present disclosure.

[0021] Figure 2 It is a schematic cross-sectional structure diagram of some embodiments of a combustion chamber flame tube applicable to a pure hydrogen gas turbine according to the present disclosure.

[0022] Figure 3 is a flow chart of some embodiments of a method for manufacturing a combustor flame sleeve according to the present disclosure. DETAILED DESCRIPTION

[0023] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments set forth herein. On the contrary, these embodiments are provided to provide a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0024] It should also be noted that, for ease of description, only the parts related to the invention are shown in the drawings. In the absence of conflict, the embodiments and features in the embodiments of the present disclosure can be combined with each other.

[0025] It should be noted that the concepts such as "first" and "second" mentioned in the present disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0026] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0027] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0028] The present disclosure will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0029] Figure 1 It is a schematic structural diagram of some embodiments of a combustion chamber flame tube applicable to a pure hydrogen gas turbine according to the present disclosure. Figure 1 It includes a flame tube body 1, a tail cooling section 13, a tail cooling groove 131, a mixing hole 14, a bushing body 21 and a fixing assembly 22.

[0030] Figure 2It is a schematic cross-sectional structure diagram of some embodiments of a combustion chamber flame tube applicable to a pure hydrogen gas turbine according to the present disclosure. Figure 2 It includes a flame tube body 1, a flame tube guide sleeve 2, a head cooling section 11, a heat exchange rib segment 12, a tail cooling section 13, a mixing hole 14, a heat exchange rib 121, a head cooling groove 111 and a tail cooling groove 131.

[0031] In some embodiments, the combustion chamber flame tube includes: a flame tube body 1 and a flame tube guide bushing 2. The combustion chamber flame tube may be a flame tube in a combustion chamber of a pure hydrogen gas turbine. The pure hydrogen gas turbine may be a gas turbine whose fuel has a 100% hydrogen content. The flame tube body 1 may be a cylinder of a thin-walled part for fuel combustion. The material of the flame tube body 1 may be a nickel-based high-temperature alloy. The flame tube body 1 may include a head cooling section 11, a heat exchange rib segment 12 and a tail cooling section 13. The head cooling section 11 and the tail cooling section 13 may be cylindrical cylinders. The heat exchange rib segment 12 may be a truncated cone-shaped cylinder. At least one head cooling groove 111 may be provided on the inner side of the head cooling section 11. The head cooling groove 111 may be a groove for forming a cooling gas film on the inner side of the head of the flame tube body 1. The head of the flame tube body 1 may be a portion of the flame tube connected to the main nozzle of the combustion chamber. The shape and number of the head cooling groove 111 are not limited. For example, the shape of the head cooling groove 111 can be rectangular or waist-shaped. The outer side surface of the above-mentioned tail cooling section 13 can be provided with at least one tail cooling groove 131. The tail cooling groove 131 can be a groove for forming a cooling gas film on the outer side surface of the tail of the flame tube body 1. The tail of the flame tube body 1 can be a part of the flame tube connected to the transition section of the combustion chamber. There is no limitation on the shape and number of the tail cooling groove 131. For example, the shape of the tail cooling groove 131 can be rectangular or waist-shaped. It should be noted that the shape of the head cooling groove 111 can be the same as or different from the shape of the tail cooling groove 131. At least one heat exchange fin 121 is provided on the outer side surface of the above-mentioned heat exchange fin segment 12. The heat exchange fin 121 can be a fin for increasing the convective heat exchange on the side of the flame tube body 1. There is no limitation on the shape and number of the heat exchange fin 121. For example, the shape of the heat exchange fin 121 can be rectangular or trapezoidal. The above-mentioned head cooling section 11 can include a connecting component. The above-mentioned connecting assembly can be used to connect the above-mentioned head cooling section 11 with the main nozzle of the combustion chamber. The above-mentioned main nozzle of the combustion chamber can be a fuel nozzle included in the combustion chamber of a pure hydrogen gas turbine. As an example, the above-mentioned connecting assembly can include a slot and an elastic sealing ring. The above-mentioned slot can be opened on the inner side of the above-mentioned head cooling section 11. The above-mentioned elastic sealing ring can be arranged in the above-mentioned slot. A sealing ring groove can be arranged on the above-mentioned combustion chamber main nozzle. The above-mentioned sealing ring groove can be a groove for nesting the sealing ring. The above-mentioned elastic sealing ring can be engaged in the above-mentioned sealing ring groove. Thus, the flame tube body can be connected to the main nozzle of the combustion chamber through the connecting assembly, and can be cooled by the cooling air film formed at the head and tail of the flame tube, and the heat exchange fins of the middle section.

[0032] In some embodiments, the flame tube guide bushing 2 may include a bushing body 21 and a fixing assembly 22. The bushing body 21 may be a bushing for guiding the flow direction of gas. The bushing body 21 may be made of stainless steel. For example, the bushing body 21 may be made of 316L stainless steel. The fixing assembly 22 may be a component for fixing the flame tube guide bushing 2. The bushing body 21 and the fixing assembly 22 may be fixedly connected. The fixing assembly 22 may be used to detachably connect the bushing body 21 to the combustion chamber casing. As an example, the fixing assembly 22 may include a screw hole. The flame tube guide bushing 2 may detachably connect the bushing body 21 to the combustion chamber casing by screws. Thus, the flame tube guide bushing may be fixedly arranged in the combustion chamber.

[0033] In some embodiments, the flame tube body 1 may be disposed inside the bushing body 21. A preset annular cavity spacing is provided between the flame tube body 1 and the bushing body 21. The preset annular cavity spacing may be a pre-set annular cavity spacing. The annular cavity spacing may be a vertical distance between any point on the outer side surface of the flame tube body 1 and the inner side surface of the bushing body 21. Thus, convection heat exchange may be performed on each heat exchange fin through the annular cavity formed between the bushing body and each heat exchange fin.

[0034] In some embodiments, at least one mixing hole 14 may be provided on the flame tube body 1. The mixing hole 14 may be a hole for air to flow in. The shape and number of the mixing hole 14 are not limited.

[0035] Therefore, when the combustion chamber of the pure hydrogen gas turbine is in working state, the air flow can enter the annular cavity formed between the liner body and each heat exchange fin, forming three air flows. Among them, the first air flow can enter the flame tube from each mixing hole, so as to cool the gas in the flame tube; the second air flow can enter the flame tube from the head cooling section, so as to form a cooling air film on the inner side of the flame tube head through the head cooling groove, thereby reducing the temperature of the inner side of the flame tube; the third air flow can enter the flame tube from the tail cooling section, so as to adjust the temperature distribution at the combustion chamber outlet.

[0036] Optionally, the preset annular cavity spacing may range from 30 to 40 mm. The fin height of each heat exchange fin 121 included in the at least one heat exchange fin 121 may range from 2 to 4 mm. The fin height range may be a range of fin heights. The fin height may be the height of the fin in a direction perpendicular to the outer side surface of the flame tube body 1. The fin spacing between each heat exchange fin 121 is 18 to 22 mm. The fin spacing may be the spacing between every two heat exchange fins 121. As a result, the airflow entering the annular cavity is in a vigorous turbulent zone, thereby improving the heat exchange effect of the heat exchange fins.

[0037] Optionally, the opening angle of each heat exchange fin 121 on the outer side surface of the heat exchange fin segment 12 may be 90 degrees, thereby facilitating processing.

[0038] Optionally, each heat exchange fin 121 may be provided with a chamfer, thereby suppressing the flow separation of the air flow on each heat exchange fin 121, thereby reducing the pressure loss.

[0039] Optionally, the center points of the mixing holes 14 included in the at least one mixing hole 14 are located on the same horizontal plane, and the distance between the center point of the mixing hole and the center point of the head is in the range of 250 to 260 mm. Among them, the center point of the mixing hole can be the center point of the mixing hole 14. The center point of the head can be the center point of the upper surface of the head cooling section 11. The upper surface of the head cooling section 11 can be the surface of the head cooling section 11 located on one side of the main nozzle of the combustion chamber. The ratio of the total area of ​​the mixing holes of each mixing hole 14 to the total area of ​​the micro-mixing tube of the combustion chamber is a preset first area ratio. The total area of ​​the mixing holes can be the sum of the areas of the individual mixing holes. The area of ​​the mixing holes can be the area of ​​the mixing hole 14. The total area of ​​the micro-mixing tube of the combustion chamber can be the sum of the outlet areas of each micro-mixing tube of each micro-mixing tube included in the combustion chamber. The outlet area of ​​the micro-mixing tube can be the area of ​​the outlet of the micro-mixing tube. The micro-mixing tube can be a tube body for pre-mixing fuel and air. The preset first area ratio may be a preset area ratio, so as to adjust the flow distribution of the gas in the annular cavity and reduce the pressure loss. For example, the preset first area ratio may be 1:4.8.

[0040] Optionally, the ratio of the head flow area, the tail flow area and the total area of ​​the micro-mixing tube of the combustion chamber can be a preset second area ratio. The preset second area ratio can be a pre-set ratio. The head flow area can be the sum of the areas of each head cooling groove of each head cooling groove 111. The head cooling groove area can be the surface area of ​​the head cooling groove 111. The tail flow area can be the sum of the areas of each tail cooling groove of each tail cooling groove 131. The tail cooling groove area can be the surface area of ​​the tail cooling groove 131. Thereby, the rationality of the distribution of the gas flow in the flame tube can be improved and the pressure loss can be reduced.

[0041] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: through the combustion chamber flame tube applicable to the pure hydrogen gas turbine of some embodiments of the present disclosure, the emission of nitrogen oxides emitted from the combustion chamber can be reduced. Specifically, the reason for the high emission of nitrogen oxides from the combustion chamber is that the flame tube adopts slot air film cooling for wall cooling, and the required cooling air accounts for a high proportion of the total gas volume, resulting in a low proportion of air entering from the head to participate in combustion, and the equivalent of the main combustion zone of the combustion chamber is relatively high, resulting in a high combustion temperature, thereby causing more nitrogen oxides to be emitted from the combustion chamber. Based on this, some embodiments of the present disclosure are suitable for a combustion chamber flame tube of a pure hydrogen gas turbine, which combustion chamber flame tube includes: the above-mentioned flame tube main body includes a head cooling section, a heat exchange rib segment and a tail cooling section, the inner side surface of the above-mentioned head cooling section is provided with at least one head cooling groove, the outer side surface of the above-mentioned tail cooling section is provided with at least one tail cooling groove, the outer side surface of the above-mentioned heat exchange rib segment is provided with at least one heat exchange rib, the above-mentioned head cooling section includes a connecting assembly, and the above-mentioned connecting assembly is used to connect the above-mentioned head cooling section with the combustion chamber main nozzle; the above-mentioned flame tube guide sleeve includes a sleeve main body and a fixing assembly, the above-mentioned sleeve main body and the above-mentioned fixing assembly are fixedly connected, and the above-mentioned fixing assembly is used to detachably connect the above-mentioned sleeve main body with the combustion chamber casing; the above-mentioned flame tube main body is arranged inside the above-mentioned sleeve main body, and a preset annular cavity spacing is arranged between the above-mentioned flame tube main body and the above-mentioned sleeve main body; at least one mixing hole is opened on the above-mentioned flame tube main body. Because the combustion chamber flame tube can improve the convective heat transfer effect of the flame tube wall through the heat exchange rib segments, and at the same time, the head cooling slots and the tail cooling slots are combined to achieve air film cooling at both ends, so that the flame tube wall temperature can be cooled. Also, because the convective heat transfer through the heat exchange rib segments replaces the traditional wall air film cooling method, the amount of air used for cooling can be reduced, and then the combustion temperature can be reduced, thereby reducing the emission of nitrogen oxides emitted by the combustion chamber.

[0042] Continue to refer Figure 3 , shows a process 300 of some embodiments of the combustion chamber flame tube manufacturing method according to the present disclosure. The combustion chamber flame tube manufacturing method is applied to Figure 1 The combustion chamber flame sleeve suitable for a pure hydrogen gas turbine shown includes the following steps:

[0043] Step 301, determine the initial heat exchange fin parameter information, and perform the following simulation steps:

[0044] Step 3011, constructing a first initial flame tube three-dimensional model according to the initial heat exchange fin parameter information and the preset flame tube size information.

[0045] In some embodiments, the execution body (e.g., a computing device) of the combustion chamber flame tube manufacturing method can construct a first initial flame tube three-dimensional model according to the initial heat exchange fin parameter information and the preset flame tube size information. The initial heat exchange fin parameter information can be the initial heat exchange fin parameter information. The heat exchange fin parameter information can characterize the heat exchange fin size. The initial heat exchange fin parameter information can include but is not limited to the ring cavity spacing, fin height, and fin spacing. The preset flame tube size information can be information of the preset flame tube size. The preset flame tube size information can include but is not limited to the head cooling section height, the heat exchange fin segment height, the tail cooling section height, the heat exchange fin segment average diameter, the head cooling section diameter, the tail cooling section diameter, the flame tube body wall thickness, and the mixing hole information. The head cooling section height can be the height of the cylinder corresponding to the head cooling section. The heat exchange fin segment height can be the height of the cylinder corresponding to the heat exchange fin segment. The tail cooling section height can be the height of the cylinder corresponding to the tail cooling section. The head cooling section diameter can be the diameter of the cylinder corresponding to the head cooling section. The diameter of the tail cooling section may be the diameter of the cylinder corresponding to the tail cooling section. The average diameter of the heat exchange fin segment may be the average value of the diameter of the truncated cone corresponding to the heat exchange fin segment. The wall thickness of the flame tube body may be the thickness of the wall of the flame tube body. The mixing hole information may include but is not limited to the shape of the mixing hole, the area of ​​the mixing hole, and the height of the mixing hole. The shape of the mixing hole may be the shape of the mixing hole. The shape of the mixing hole may be but is not limited to one of the following: rectangular, circular, and waist-shaped. The area of ​​the mixing hole may be the area of ​​a single mixing hole. The height of the mixing hole may be the distance between the center point of the mixing hole and the center point of the head. In practice, the execution subject may determine the preset heat exchange fin parameter information as the initial heat exchange fin parameter information, and construct the first initial flame tube three-dimensional model through the preset three-dimensional modeling software according to the initial heat exchange fin parameter information and the preset flame tube size information. Among them, the preset heat exchange fin parameter information may be the preset heat exchange fin parameter information. The preset three-dimensional modeling software may be the preset software for establishing a three-dimensional model. For example, the above-mentioned preset 3D modeling software may be UG (Unigraphics) software.

[0046] Step 3012: simulate the first initial flame tube three-dimensional model according to the preset first fluid simulation model set to obtain first simulation information.

[0047] In some embodiments, the execution subject may simulate the first initial flame tube three-dimensional model according to the preset first fluid simulation model set to obtain the first simulation information. The preset first fluid simulation model in the preset first fluid simulation model set may be a preset fluid simulation model. For example, the preset first fluid simulation model set may include a Realizable k-ε turbulence model and a Species Transport model. The first simulation information may include but is not limited to a flow field distribution diagram and a simulated gas average velocity. The simulated gas average velocity may be the average velocity of the gas flow in the annular cavity. In practice, first, the execution subject may import the first initial flame tube three-dimensional model into the preset simulation software. The preset simulation software may be a preset simulation software. For example, the preset simulation software may be a CFD (Computational Fluid Dynamics) simulation software. Then, in the preset simulation software, each preset first fluid simulation model included in the preset first fluid simulation model set is run to obtain a flow field distribution diagram and a simulated gas average velocity.

[0048] Step 3013, performing trapped vortex detection processing on the flow field distribution diagram to obtain a trapped vortex detection result.

[0049] In some embodiments, the above-mentioned execution subject may perform vortex trapped detection processing on the above-mentioned flow field distribution diagram to obtain a vortex trapped detection result. In practice, the above-mentioned execution subject may input the above-mentioned flow field distribution diagram into a pre-trained vortex trapped detection result generation model to obtain a vortex trapped detection result. Among them, the above-mentioned vortex trapped detection result generation model may be a classification model that takes the flow field distribution diagram as input and the vortex trapped detection result as output. The above-mentioned vortex trapped detection result may characterize whether there is a vortex trapped on the wall surface between each heat exchange fin in the flow distribution diagram. The vortex trapped detection result may be, but is not limited to, one of the following: the presence of a vortex trapped, the absence of a vortex trapped.

[0050] Step 3014, generating a simulated Reynolds number, a simulated heat transfer roughness and a simulated roughness according to the simulated gas average velocity and the initial heat exchange fin parameter information.

[0051] In some embodiments, the execution subject may generate a simulated Reynolds number, a simulated heat transfer roughness and a simulated roughness according to the simulated gas average velocity and the initial heat exchange fin parameter information. Among them, the simulated Reynolds number may be a simulated Reynolds number. The simulated heat transfer roughness may be a simulated heat transfer roughness of the heat exchange fin under the initial heat exchange fin parameter information and the Prandtl constant. The heat transfer roughness may be the degree of unevenness on the surface or interface of the material during the heat transfer process. The simulated roughness may be the roughness of the heat exchange fin obtained by simulation. In practice, first, the execution subject may input the simulated gas average velocity, the annular cavity spacing included in the initial heat exchange fin parameter information and the preset gas viscosity into the Reynolds number formula to obtain the simulated Reynolds number. Among them, the preset gas viscosity may be a preset viscosity of the air in the annular cavity. Secondly, the average diameter of the heat exchange fin segment included in the initial heat exchange fin parameter information is input into the circumference formula to obtain the average circumference of the heat exchange fin segment. Then, the average circumference of the heat exchange fin segment and the initial heat exchange fin parameter information including the ring cavity spacing, fin height, and fin spacing are input into the preset roughness generation model to obtain the simulated roughness. The preset roughness generation model can be expressed by the following formula:

[0052]

[0053] Wherein, R can represent the simulated roughness. f can represent the friction factor. e can represent the fin height. D can represent the ring cavity spacing. W can represent the average circumference of the heat exchange fin segment. H can represent the fin spacing. The above f can be generated by the following formula:

[0054]

[0055] in, It can represent the average friction factor of the opposite sides of two preset opposite heat exchange fins. s It can represent the friction factor of a preset smooth heat exchange fin channel.

[0056] Finally, the simulated roughness is input into the preset heat transfer roughness formula to obtain the heat transfer roughness.

[0057] Among them, the above preset heat transfer roughness formula can be expressed by the following formula:

[0058]

[0059] Wherein, G may represent the simulated heat transfer roughness, and S may represent a preset Stanton number.

[0060] Step 3015, in response to determining that the trapped vortex detection result, the simulated Reynolds number, the simulated heat transfer roughness and the simulated roughness meet the preset verification conditions, the initial heat exchange fin parameter information is determined as the heat exchange fin parameter information.

[0061] In some embodiments, the execution subject may determine the initial heat exchange fin parameter information as the heat exchange fin parameter information in response to determining that the trapped vortex detection result, the simulated Reynolds number, the simulated heat transfer roughness, and the simulated roughness meet preset verification conditions. Among them, the preset verification conditions may be that the trapped vortex detection result represents the presence of trapped vortices on the wall between each heat exchange fin in the flow distribution diagram, the simulated Reynolds number is greater than the preset Reynolds number, the simulated heat transfer roughness is less than the preset heat transfer roughness, and the simulated roughness is greater than the preset roughness. The preset Reynolds number may be a preset Reynolds number that represents that the airflow may be in a strong turbulent area. For example, the preset Reynolds number may be 10 4 The preset heat transfer roughness may be a preset heat transfer roughness. The preset roughness may be a preset roughness.

[0062] Optionally, the above execution subject may also perform the following simulation steps:

[0063] In response to determining that the above-mentioned trapped vortex detection result, the above-mentioned simulated gas average velocity, the above-mentioned simulated heat transfer roughness, and the above-mentioned simulated roughness do not meet the above-mentioned preset verification conditions, the initial heat exchange fin parameter information is adjusted to obtain updated heat exchange fin parameter information, and the updated heat exchange fin parameter information is used as the initial heat exchange fin parameter information to continue to perform the above-mentioned simulation steps. As an example, the above-mentioned execution subject can adjust the initial heat exchange fin parameter information by using a grid search parameter adjustment method to obtain updated heat exchange fin parameter information.

[0064] Step 302, determining the area ratio information of the flame tube head and tail.

[0065] In some embodiments, the execution subject may determine the flame tube head-to-tail area ratio information. The flame tube head-to-tail area ratio information may characterize the flame tube head-to-tail area ratio. The flame tube head-to-tail area ratio may be a ratio of the head flow area to the tail flow area. In practice, the execution subject may determine the preset flame tube head-to-tail area ratio as the flame tube head-to-tail area ratio information. The preset flame tube head-to-tail area ratio may be a preset flame tube head-to-tail area ratio.

[0066] In some optional implementations of some embodiments, the execution subject may determine the area ratio information of the flame tube head and tail through the following steps:

[0067] In the first step, the preset flame tube head and tail area ratio information is determined as the initial flame tube head and tail area ratio information, and the following simulation steps are performed:

[0068] Step 1: construct a second initial flame tube three-dimensional model according to the initial flame tube head and tail area ratio information and the above-mentioned heat exchange fin parameter information. In practice, the above-mentioned execution subject can construct the second initial flame tube three-dimensional model according to the initial flame tube head and tail area ratio information, the above-mentioned preset flame tube size information and the above-mentioned heat exchange fin parameter information through the above-mentioned preset three-dimensional modeling software.

[0069] Step 2, according to the preset second fluid simulation model set, simulate the above-mentioned second initial flame tube three-dimensional model to obtain the second simulation information. Among them, the preset second fluid simulation model in the preset second fluid simulation model set can be a preset fluid simulation model. For example, the preset second fluid simulation model set can include a Realizable k-ε turbulence model and a small flame generating flow (FGM, Flame Generated Manifold) model. The above-mentioned second simulation information may include but is not limited to the simulated flame tube wall temperature. The above-mentioned simulated flame tube wall temperature can be the temperature of the side of the combustion chamber flame tube obtained by simulation. In practice, the above-mentioned execution entity can import the second initial flame tube three-dimensional model into the above-mentioned preset simulation software. Then, in the above-mentioned preset simulation software, run each preset second fluid simulation model included in the preset second fluid simulation model set to obtain the simulated flame tube wall temperature.

[0070] Step 3, in response to determining that the simulated flame tube wall temperature meets the preset temperature verification condition, the initial flame tube head and tail area ratio information is determined as the flame tube head and tail area ratio information. The preset temperature verification condition may be that the simulated flame tube wall temperature is less than the preset flame tube wall temperature. The preset flame tube wall temperature may be the maximum value of the flame tube wall temperature that is preset within a safe range.

[0071] Optionally, the above execution subject may also perform the following simulation steps:

[0072] Step 4: In response to determining that the simulated flame tube wall temperature does not meet the preset temperature verification condition, the initial flame tube head and tail area ratio information is adjusted to obtain updated flame tube head and tail area ratio information, and the updated flame tube head and tail area ratio information is used as the initial flame tube head and tail area ratio information to continue to perform the above simulation steps. As an example, the above execution subject can adjust the width of the head cooling groove and the width of the tail cooling groove through a grid search parameter adjustment method to adjust the initial flame tube head and tail area ratio information.

[0073] Step 303, determining the flame tube mixing hole information.

[0074] In some embodiments, the execution entity may determine the flame tube mixing hole information. The flame tube mixing hole information may be the information of the mixing hole in the flame tube of the combustion chamber. In practice, the execution entity may determine the preset flame tube mixing hole information as the flame tube mixing hole information. The preset flame tube mixing hole information may be the preset flame tube mixing hole information. The preset flame tube mixing hole information may include but is not limited to the mixing hole shape, mixing hole area, and mixing hole height.

[0075] For the second technical problem in the background technology, the following solution can be adopted:

[0076] In some optional implementations of some embodiments, the execution subject may determine the flame tube mixing hole information through the following steps:

[0077] The first step is to obtain the flame tube combustion gas flow rate. The flame tube combustion gas flow rate may be the volume flow rate of the gas used for combustion in the flame tube. In practice, the execution subject may obtain the flame tube combustion gas flow rate from the database through a wired connection or a wireless connection.

[0078] The second step is to generate a mixing hole height threshold according to the flame tube combustion gas flow rate and the preset gas retention time threshold. The preset gas retention time range may be the maximum value of the preset gas retention time. The gas retention time may be the time that the mixed gas ejected from the main nozzle of the combustion chamber can be retained in the flame tube. The mixing hole height threshold may be the maximum value of the mixing hole height. In practice, the execution subject may determine the product of the flame tube combustion gas flow rate and the preset gas retention time threshold as the flame tube combustion gas volume threshold. The flame tube combustion gas volume threshold may be the maximum value of the flame tube combustion gas volume. The flame tube combustion gas volume may be the volume of the flame tube from the flame tube head to the center point of the mixing hole position. Then, the flame tube combustion gas volume threshold, the head cooling section diameter and the tail cooling section diameter included in the preset flame tube size information are input into the truncated cone volume formula to obtain the truncated cone height threshold as the mixing hole height threshold. The flame tube combustion gas volume threshold may be the volume in the truncated cone volume formula. The head cooling section diameter included in the preset flame tube size information may be the diameter of the upper bottom surface of the truncated cone in the truncated cone volume formula. The tail cooling section diameter included in the preset flame tube size information may be the diameter of the lower bottom surface of the truncated cone in the truncated cone volume formula.

[0079] The third step is to determine the initial flame tube mixing hole information according to the above mixing hole height range, and perform the following mixing hole information determination steps:

[0080] Step 1: construct a third initial flame tube three-dimensional model based on the flame tube head and tail area ratio information, the heat exchange fin parameter information and the initial flame tube mixing hole information. In practice, first, the execution subject can determine the mixing hole information included in the preset flame tube size information as the initial flame tube mixing hole information. Then, based on the flame tube head and tail area ratio information, the heat exchange fin parameter information, the preset flame tube size information and the initial flame tube mixing hole information, construct the third initial flame tube three-dimensional model through the preset three-dimensional modeling software.

[0081] Step 2, according to the preset second fluid simulation model set, simulate the above-mentioned third initial flame tube three-dimensional model to obtain the third simulation information. Wherein, the above-mentioned third simulation information includes the maximum value of the simulated combustion chamber outlet temperature, the average value of the simulated combustion chamber outlet temperature and the average value of the simulated combustion chamber inlet temperature. The above-mentioned maximum value of the simulated combustion chamber outlet temperature can be the maximum value of the temperature at the combustion chamber outlet obtained by simulation. The above-mentioned average value of the simulated combustion chamber outlet temperature can be the average value of the temperature at the combustion chamber outlet obtained by simulation. The above-mentioned average value of the simulated combustion chamber inlet temperature can be the average value of the temperature at the combustion chamber inlet obtained by simulation. In practice, first, the above-mentioned execution entity can import the above-mentioned third initial flame tube three-dimensional model into the above-mentioned preset simulation software. Then, in the above-mentioned preset simulation software, run each preset second fluid simulation model included in the preset second fluid simulation model set to obtain the third simulation information.

[0082] Step three, determining the difference between the maximum value of the simulated combustion chamber outlet temperature and the average value of the simulated combustion chamber outlet temperature as the first temperature difference.

[0083] Step 4: Determine the difference between the average value of the simulated combustion chamber outlet temperature and the average value of the simulated combustion chamber inlet temperature as the second temperature difference.

[0084] Step 5: Determine the ratio of the first temperature difference to the second temperature difference as the temperature non-uniformity coefficient.

[0085] Step 6: In response to determining that the temperature non-uniformity coefficient satisfies the preset temperature non-uniformity condition, the initial flame tube mixing hole information is determined as the flame tube mixing hole information. The preset temperature non-uniformity condition may be that the temperature non-uniformity coefficient is less than or equal to the preset temperature non-uniformity coefficient. The preset temperature non-uniformity coefficient may be a pre-set temperature non-uniformity coefficient. For example, the preset temperature non-uniformity coefficient may be 0.15.

[0086] Step seven, in response to determining that the temperature non-uniformity coefficient does not meet the preset temperature non-uniformity condition, the initial flame tube mixing hole information is adjusted according to the mixing hole height range to obtain updated flame tube mixing hole information, and the updated flame tube mixing hole information is used as the initial flame tube mixing hole information to continue to perform the mixing hole information determination step. As an example, the execution subject can adjust the mixing hole height, mixing hole shape and mixing hole area by using a grid search parameter adjustment method to obtain updated heat exchange fin parameter information. It should be noted that the adjusted mixing hole height is within the mixing hole height range.

[0087] The above technical solution and its related contents, as an inventive point of the embodiment of the present disclosure, solve the technical problem 2 mentioned in the background technology, "the hydrogen content of the fuel in the pure hydrogen gas turbine is high, and the hydrogen is relatively active. The position of the mixing hole is set according to the experience of hydrogen-mixed fuel, which leads to a longer residence time of the fuel in the combustion chamber of the pure hydrogen gas turbine, thereby causing the stability of the combustion gas to be low. If the above factors are solved, the effect of improving the stability of the combustion gas can be achieved. In order to achieve this effect, the combustion chamber flame tube manufacturing method disclosed in the present invention, when determining the height of the mixing hole, first determines the maximum height of the mixing hole according to the maximum value of the residence time of the pure hydrogen fuel in the flame tube, and then simulates through simulation software to obtain the non-uniformity coefficient of the combustion chamber temperature, thereby obtaining the position information and size information of the mixing hole. Also, because when determining the position and size of the mixing hole, the residence time of hydrogen is first considered, and then the position and size information of the mixing hole are obtained through simulation calculation, thereby improving the stability of the combustion gas in the combustion chamber.

[0088] Step 304, according to the heat exchange fin parameter information, the flame tube mixing hole information and the flame tube head and tail area ratio information, control the associated flame tube manufacturing device to perform the flame tube manufacturing operation.

[0089] In some embodiments, the execution subject may control the associated flame tube manufacturing device to perform the flame tube manufacturing operation according to the heat exchange fin parameter information, the flame tube mixing hole information and the flame tube head and tail area ratio information. The flame tube manufacturing device may be a device for manufacturing a combustion chamber flame tube. The flame tube manufacturing device may be a three-dimensional printing device. The flame tube manufacturing operation may be an operation for manufacturing a combustion chamber flame tube.

[0090] The above-mentioned embodiments of the present disclosure have the following beneficial effects: through the combustion chamber flame tube manufacturing method of some embodiments of the present disclosure, the emission of nitrogen oxides emitted by the combustion chamber can be reduced. Specifically, the reason for the high nitrogen oxide emission from the combustion chamber is that the flame tube adopts the slot air film cooling method for wall cooling, and the required cooling air accounts for a high proportion of the total gas volume, resulting in a low proportion of air entering the head to participate in the combustion, and the equivalent ratio of the main combustion zone of the combustion chamber is relatively high, resulting in a high combustion temperature, thereby causing more nitrogen oxides to be emitted from the combustion chamber. Based on this, the combustion chamber flame tube manufacturing method of some embodiments of the present disclosure, first, determines the initial heat exchange fin parameter information, and performs the following simulation steps: the first step is to construct a first initial flame tube three-dimensional model according to the initial heat exchange fin parameter information and the preset flame tube size information. Thus, an initial three-dimensional model of the flame tube can be obtained, which can be used for simulation. The second step is to simulate the above-mentioned first initial flame tube three-dimensional model according to the preset first fluid simulation model set to obtain the first simulation information, wherein the above-mentioned first simulation information includes a flow field distribution diagram and a simulated gas average velocity. Thus, the flow field distribution diagram of the gas and the average velocity in the flame tube under the flame tube structure of the corresponding size can be obtained, which can be used to judge the convective heat transfer effect of the flame tube. The third step is to perform vortex detection processing on the above flow field distribution diagram to obtain the vortex detection result. Thus, it can be determined whether there is a vortex between the wall surfaces corresponding to the flame tube heat exchange fins, which can be used to judge the convective heat transfer effect of the flame tube. The fourth step is to generate the simulated Reynolds number, the simulated heat transfer roughness and the simulated roughness according to the simulated gas average velocity and the initial heat exchange fin parameter information; the fifth step is to determine the initial heat exchange fin parameter information as the heat exchange fin parameter information in response to determining that the above vortex detection result, the above simulated Reynolds number, the above simulated heat transfer roughness and the above simulated roughness meet the preset verification conditions. Thus, the parameter information of the heat exchange fin with better convective heat transfer effect can be obtained, so as to improve the convective heat transfer effect of the flame tube. Secondly, the area ratio information of the head and tail of the flame tube is determined. Thus, the size ratio of each head cooling groove and tail cooling groove of the flame tube can be obtained. Then, the flame tube mixing hole information is determined. Thus, the position and size information of the mixing hole can be obtained. Finally, according to the above heat exchange fin parameter information, the above flame tube mixing hole information and the above flame tube head and tail area ratio information, the associated flame tube manufacturing device is controlled to perform the flame tube manufacturing operation, thereby, a combustion chamber flame tube with better convective heat transfer effect can be obtained, thereby reducing the emission of nitrogen oxides.Also, when manufacturing the combustion chamber flame tube, the flow field distribution of the gas in the flame tube can be simulated, and the influence of separation, reattachment and backflow caused by periodically arranged fins on the gas flow field distribution can be considered to obtain the size information of the heat exchange fin segments with better convective heat transfer effect, thereby improving the convective heat transfer effect of the combustion chamber flame tube, thereby reducing the emission of nitrogen oxides.

[0091] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present disclosure. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0092] The above descriptions are only some preferred embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the embodiments of the present disclosure is not limited to the technical solutions formed by a specific combination of the above-mentioned technical features, but should also cover other technical solutions formed by any combination of the above-mentioned technical features or their equivalent features without departing from the above-mentioned inventive concept. For example, the above-mentioned features are replaced with the technical features with similar functions disclosed in the embodiments of the present disclosure (but not limited to) and the technical solutions formed.

Claims

1. A combustion chamber flame tube suitable for a pure hydrogen gas turbine, the combustion chamber flame tube comprising: The flame tube body and the flame tube guide bushing, wherein: The flame tube body includes a head cooling section, a heat exchange rib segment and a tail cooling section, the inner side surface of the head cooling section is provided with at least one head cooling groove, the outer side surface of the tail cooling section is provided with at least one tail cooling groove, the outer side surface of the heat exchange rib segment is provided with at least one heat exchange rib, and the head cooling section includes a connecting assembly, which is used to connect the head cooling section with the main nozzle of the combustion chamber; The flame tube guide bushing comprises a bushing body and a fixing assembly, wherein the bushing body and the fixing assembly are fixedly connected, and the fixing assembly is used to detachably connect the bushing body to the combustion chamber casing; The flame tube body is arranged inside the bushing body, and a preset annular cavity spacing is arranged between the flame tube body and the bushing body; At least one mixing hole is provided on the flame tube body.

2. The combustion chamber flame liner suitable for a pure hydrogen gas turbine according to claim 1, wherein: The preset annular cavity spacing ranges from 30 to 40 mm, the fin height of each heat exchange fin included in the at least one heat exchange fin ranges from 2 to 4 mm, and the fin spacing between the heat exchange fins is from 18 to 22 mm.

3. The combustion chamber flame liner suitable for a pure hydrogen gas turbine according to claim 1, wherein: The opening angle of each heat exchange fin on the outer side of the heat exchange fin segment is 90 degrees.

4. The combustion chamber flame liner suitable for a pure hydrogen gas turbine according to claim 1, wherein: Each heat exchange fin is provided with a chamfer.

5. The combustion chamber flame liner suitable for a pure hydrogen gas turbine according to claim 1, wherein: The center points of the mixing holes of the at least one mixing hole are located on the same horizontal plane, and the distance between the center point of the mixing hole and the center point of the head is in the range of 250 to 260 mm, and the ratio of the total area of ​​the mixing holes of the mixing holes to the total area of ​​the micro-mixing tube of the combustion chamber is a preset first area ratio.

6. The combustion chamber flame liner suitable for a pure hydrogen gas turbine according to claim 1, wherein: The ratio of the head flow area, the tail flow area and the total area of ​​the combustion chamber micro-mixing tube is a preset second area ratio, the head flow area is the sum of the areas of each head cooling groove of each head cooling groove, and the tail flow area is the sum of the areas of each tail cooling groove of each tail cooling groove.

7. A method for manufacturing a combustion chamber flame tube, applied to the combustion chamber flame tube suitable for a pure hydrogen gas turbine as claimed in any one of claims 1 to 6, the method comprising: Determine the initial heat transfer fin parameter information and perform the following simulation steps: Constructing a first initial flame tube three-dimensional model according to initial heat exchange fin parameter information and preset flame tube size information; According to a preset first fluid simulation model set, the first initial flame tube three-dimensional model is simulated to obtain first simulation information, wherein the first simulation information includes a flow field distribution diagram and a simulated gas average velocity; Performing a trapped vortex detection process on the flow field distribution diagram to obtain a trapped vortex detection result; Generate the simulated Reynolds number, simulated heat transfer roughness and simulated roughness according to the simulated gas average velocity and the initial heat exchange fin parameter information; In response to determining that the trapped vortex detection result, the simulated Reynolds number, the simulated heat transfer roughness, and the simulated roughness meet a preset verification condition, determining the initial heat exchange fin parameter information as the heat exchange fin parameter information; Determine the ratio of the area between the head and tail of the flame tube; Determine the flame tube mixing hole information; According to the heat exchange fin parameter information, the flame tube mixing hole information and the flame tube head and tail area ratio information, the associated flame tube manufacturing device is controlled to perform the flame tube manufacturing operation.

8. The method according to claim 7, wherein: The simulation step also includes: In response to determining that the trapped vortex detection result, the simulated gas average velocity, the simulated heat transfer roughness and the simulated roughness do not meet the preset verification conditions, the initial heat exchange fin parameter information is adjusted to obtain updated heat exchange fin parameter information, and the updated heat exchange fin parameter information is used as the initial heat exchange fin parameter information to continue executing the simulation step.

9. The method according to claim 7, wherein: Determining the area ratio information of the flame tube head and tail includes: The preset flame tube head and tail area ratio information is determined as the initial flame tube head and tail area ratio information, and the following simulation steps are performed: Constructing a three-dimensional model of a second initial flame tube according to the area ratio information of the head and tail of the initial flame tube and the parameter information of the heat exchange fins; According to a preset second fluid simulation model set, the second initial flame tube three-dimensional model is simulated to obtain second simulation information, wherein the second simulation information includes a simulated flame tube wall temperature; In response to determining that the simulated flame tube wall temperature satisfies a preset temperature verification condition, the initial flame tube head-to-tail area ratio information is determined as the flame tube head-to-tail area ratio information.

10. The method according to claim 9, wherein: The simulation step also includes: In response to determining that the simulated flame tube wall temperature does not meet the preset temperature verification condition, the initial flame tube head and tail area ratio information is adjusted to obtain updated flame tube head and tail area ratio information, and the updated flame tube head and tail area ratio information is used as the initial flame tube head and tail area ratio information to continue executing the simulation step.

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