Combustion chamber air intake structure and manufacturing method suitable for pure hydrogen gas turbine

Abstract

The embodiment of the present disclosure discloses a combustion chamber air intake structure and manufacturing method suitable for a pure hydrogen gas turbine. A specific implementation of the combustion chamber air intake structure includes: a primary panel, a secondary panel, at least one partition and at least one fuel hole, wherein the secondary panel includes five sectors, each of the five sectors includes at least one micro-mixing tube and a fuel hole, and the diameter of each micro-mixing tube is 3 to 5 mm. The primary panel is located at the center of the secondary panel, and an ignition hole is opened in the center of the primary panel, and an igniter and a fuel nozzle are installed in the ignition hole; each partition of at least one partition is located between two adjacent sectors, and each partition is used to separate two adjacent sectors; each fuel hole of at least one fuel hole is opened in the center of the corresponding sector, and one end of the fuel pipe is connected to the corresponding fuel hole. This implementation improves the combustion stability of the combustion chamber and the safety of the turbine.

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 air intake structure and a manufacturing method suitable for a pure hydrogen gas turbine. Background Art

[0002] The combustion chamber of a pure hydrogen gas turbine is a device where fuel or propellant burns to generate high-temperature combustion gas. It is a combustion device made of high-temperature resistant alloy materials and is an important component of a pure hydrogen gas turbine. The usual method is to transport hydrogen fuel to the main nozzle through a structure of three fuel holes and mix it with air for combustion.

[0003] However, it is found in practice that when the above method is used to manufacture the air intake structure, the following technical problems often occur:

[0004] First, when the fuel hole structure delivers fuel, the mixing uniformity of air and hydrogen is low, resulting in a higher risk of flashback of the nozzle installed in the middle of the intake structure, which in turn causes lower combustion stability in the combustion chamber and lower safety in the combustion chamber.

[0005] Second, when determining the hydrogen flow rate of the micro-mixing tube, the air intake temperature was not taken into account, resulting in the determined hydrogen flow rate being inconsistent with the actual hydrogen flow rate, which in turn resulted in a low mixing uniformity of air and hydrogen, resulting in a high temperature distribution coefficient at the combustion chamber outlet, which in turn damaged the turbine and resulted in a low safety of the turbine.

[0006] 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

[0007] 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.

[0008] Some embodiments of the present disclosure propose a combustion chamber air intake structure and a method for manufacturing the combustion chamber air intake structure suitable for a pure hydrogen gas turbine to solve one or more of the technical problems mentioned in the above background technology section.

[0009] In a first aspect, some embodiments of the present disclosure provide a combustion chamber air intake structure suitable for a pure hydrogen gas turbine, the combustion chamber air intake structure comprising: a primary panel, a secondary panel, at least one partition and at least one fuel hole, wherein the secondary panel comprises five fan-shaped segments, each of the five fan-shaped segments comprises at least one micro-mixing tube and a fuel hole, the micro-mixing tube diameter corresponding to each micro-mixing tube in the at least one micro-mixing tube is 3 to 5 mm, one end of each micro-mixing tube is located in the micro-mixing tube arrangement area of ​​the corresponding fan-shaped segment, the primary panel is located at the center of the secondary panel, an ignition hole is opened in the center of the primary panel, an igniter and a fuel nozzle are installed in the ignition hole; each of the at least one partition is located between two adjacent fan-shaped segments, each partition is used to separate two adjacent fan-shaped segments; each of the at least one fuel hole is opened in the center of the corresponding fan-shaped segment, each fuel hole is used to install a fuel pipe, and one end of the fuel pipe is connected to the corresponding fuel hole.

[0010] Optionally, the central angle of each sector is 72 degrees.

[0011] Optionally, the diameter of the fuel hole is 22-26 mm; the length of the fuel pipe installed in each fuel hole is 260 mm.

[0012] Optionally, each micro-mixing tube further includes a micro-mixing tube fuel hole, and the positions of the micro-mixing tube fuel holes included in each micro-mixing tube are the same; the micro-mixing tube fuel holes are arranged on the side of the corresponding micro-mixing tube, and the diameter of each micro-mixing tube fuel hole is 0.4 to 0.7 mm.

[0013] In a second aspect, some embodiments of the present disclosure provide a method for manufacturing a combustion chamber intake structure suitable for a pure hydrogen gas turbine, the method comprising: obtaining an initial sector partition value corresponding to a target pure hydrogen gas turbine; based on the initial sector partition value, performing the following parameter confirmation steps: creating an initial intake structure model according to the initial sector partition value, wherein the central angle of each sector segment in the initial intake structure model is the ratio of the circumferential angle to the initial sector partition value; determining the air intake volume of the sector segment according to the initial sector partition value and the secondary panel ratio; determining the hydrogen intake volume of the sector segment according to the air intake volume of the sector segment and a preset equivalence ratio; intake volume; determining the fuel hole pressure corresponding to the micro-mixing tube according to the hydrogen intake volume of the above-mentioned sector segment and the air intake volume of the above-mentioned sector segment; in response to the micro-mixing tube fuel hole pressure satisfying the preset pressure condition, determining the above-mentioned initial intake structure model as the combustion chamber intake structure, wherein the above-mentioned preset pressure condition is that the micro-mixing tube fuel hole pressure is less than or equal to the preset pressure threshold; determining the micro-mixing tube diameter and the fuel hole diameter corresponding to the combustion chamber intake structure; using the determined initial sector partition value, the micro-mixing tube diameter and the fuel hole diameter as printing parameters, controlling the associated 3D printer to perform the combustion chamber intake structure 3D printing manufacturing operation.

[0014] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: through the combustion chamber air intake structure applicable to the pure hydrogen gas turbine of some embodiments of the present disclosure, the combustion stability of the combustion chamber and the safety of the turbine are improved. Specifically, the reasons for the low combustion stability of the combustion chamber and the low safety of the combustion chamber are: when the fuel hole structure transports the fuel, the mixing uniformity of air and hydrogen is low, resulting in a high risk of flashback of the nozzle installed in the middle of the air intake structure, resulting in uneven distribution of the combustion chamber outlet temperature, thereby resulting in low combustion stability of the combustion chamber and low safety of the turbine. Based on this, some embodiments of the present disclosure are applicable to the combustion chamber air intake structure of the pure hydrogen gas turbine, the combustion chamber air intake structure includes: a primary panel, a secondary panel, at least one partition and at least one fuel hole, wherein the secondary panel includes five sectors, each of the five sectors includes at least one micro-mixing tube and a fuel hole, the micro-mixing tube diameter corresponding to each micro-mixing tube in the at least one micro-mixing tube is 3 to 5 mm, one end of each micro-mixing tube is located in the micro-mixing tube arrangement area of ​​the corresponding sector, the primary panel is located at the center of the secondary panel, an ignition hole is opened in the center of the primary panel, and an igniter and a fuel nozzle are installed in the ignition hole; each partition in the at least one partition is located between two adjacent sectors, and each partition is used to separate two adjacent sectors; each fuel hole in the at least one fuel hole is opened in the center of the corresponding sector, each fuel hole is used to install a fuel pipe, and one end of the fuel pipe is connected to the corresponding fuel hole. Because the entire secondary panel is divided into five sectors, the hydrogen fuel is input into the main nozzle through the fuel hole set in each sector. Then, the air and hydrogen are evenly mixed in multiple micro-mixing tubes arranged in the hydrogen and air secondary panels, thereby improving the mixing uniformity of the mixed gas, thereby reducing the risk of flashback, improving the combustion stability of the combustion chamber, and thus improving the safety of the turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] 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.

[0016] Figure 1 is a schematic structural diagram of some embodiments of a combustion chamber air intake structure applicable to a pure hydrogen gas turbine according to the present disclosure;

[0017] Figure 2 It is a schematic diagram of a sector structure of some embodiments of a combustion chamber air intake structure applicable to a pure hydrogen gas turbine according to the present disclosure;

[0018] Figure 3The flowcharts are some embodiments of the method for manufacturing a combustion chamber air intake structure applicable to a pure hydrogen gas turbine according to the present disclosure. DETAILED DESCRIPTION

[0019] 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.

[0020] 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.

[0021] 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.

[0022] 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".

[0023] 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.

[0024] The present disclosure will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0025] Figure 1 It is a schematic structural diagram of some embodiments of the combustion chamber air intake structure applicable to a pure hydrogen gas turbine disclosed in the present invention. Figure 1 It includes a primary panel 1, a secondary panel 2, a partition 3 and a fuel hole 4.

[0026] Figure 2 It is a schematic diagram of the fan-shaped segment structure of some embodiments of the combustion chamber air intake structure applicable to a pure hydrogen gas turbine disclosed in the present invention. Figure 2 It includes fuel holes 4 and sector blank areas 5.

[0027] In some embodiments, Figure 1As mentioned above, the combustion chamber air intake structure includes: a primary panel 1, a secondary panel 2, at least one partition 3 and at least one fuel hole 4. Among them, the primary panel 1 is located at the center of the secondary panel 2, and an ignition hole is provided in the center of the primary panel, and an igniter and a fuel nozzle are installed in the ignition hole. There is no limitation on the shapes of the first panel 1 and the second panel 2. For example, the shapes of the first panel 1 and the second panel 2 are circular. The fuel pipe may be a pipe for the circulation of fuel. The fuel may be hydrogen fuel. The fuel hole may be located at the center of the corresponding sector. Each fuel hole is used to install a fuel pipe, and one end of the fuel pipe is connected to the corresponding fuel hole.

[0028] In some embodiments, Figure 2 As shown, the secondary panel 2 includes five fan-shaped segments, each of the five fan-shaped segments includes at least one micro-mixing tube and a fuel hole 4, the micro-mixing tube diameter of each micro-mixing tube in the at least one micro-mixing tube is 3 to 5 mm, and one end of each micro-mixing tube is located in the micro-mixing tube arrangement area of ​​the corresponding fan-shaped segment. The shape of the fan-shaped segment can be the shape obtained by dividing the second panel into five equal parts. The fuel hole can be an opening for installing a fuel pipe.

[0029] In some embodiments, Figure 1 As shown, each of the at least one partition is located between two adjacent sectors, and each partition is used to separate two adjacent sectors. The number of partitions included in the at least one partition is determined by the number of sectors divided by the secondary panel. Specifically, the number of partitions included in the at least one partition is the same as the number of sectors divided by the secondary panel.

[0030] Optionally, the central angle of each sector is 72 degrees.

[0031] Optionally, the diameter of the fuel hole is 22-26 mm. The length of the fuel pipe installed in each fuel hole is 260 mm.

[0032] Optionally, each micro-mixing tube further comprises a micro-mixing tube fuel hole, and the micro-mixing tube fuel holes of each micro-mixing tube are located at the same position. The micro-mixing tube fuel holes are arranged on the side of the corresponding micro-mixing tube, and the diameter of each micro-mixing tube fuel hole is 0.4-0.7 mm.

[0033] The above-mentioned various embodiments of the present disclosure have the following beneficial effects: through the combustion chamber air intake structure applicable to the pure hydrogen gas turbine of some embodiments of the present disclosure, the combustion stability of the combustion chamber and the safety of the turbine are improved. Specifically, the reasons for the low combustion stability of the combustion chamber and the low safety of the combustion chamber are: when the fuel hole structure transports the fuel, the mixing uniformity of air and hydrogen is low, resulting in a high risk of flashback of the nozzle installed in the middle of the air intake structure, resulting in uneven distribution of the combustion chamber outlet temperature, thereby resulting in low combustion stability of the combustion chamber and low safety of the turbine. Based on this, some embodiments of the present disclosure are applicable to the combustion chamber air intake structure of the pure hydrogen gas turbine, the combustion chamber air intake structure includes: a primary panel, a secondary panel, at least one partition and at least one fuel hole, wherein the secondary panel includes five sectors, each of the five sectors includes at least one micro-mixing tube and a fuel hole, the micro-mixing tube diameter corresponding to each micro-mixing tube in the at least one micro-mixing tube is 3 to 5 mm, one end of each micro-mixing tube is located in the micro-mixing tube arrangement area of ​​the corresponding sector, the primary panel is located at the center of the secondary panel, an ignition hole is opened in the center of the primary panel, and an igniter and a fuel nozzle are installed in the ignition hole; each partition in the at least one partition is located between two adjacent sectors, and each partition is used to separate two adjacent sectors; each fuel hole in the at least one fuel hole is opened in the center of the corresponding sector, each fuel hole is used to install a fuel pipe, and one end of the fuel pipe is connected to the corresponding fuel hole. Because the entire secondary panel is divided into five sectors, the hydrogen fuel is input into the main nozzle through the fuel hole set in each sector. Then, the air and hydrogen are evenly mixed in multiple micro-mixing tubes arranged in the hydrogen and air secondary panels, thereby improving the mixing uniformity of the mixed gas, thereby reducing the risk of flashback, improving the combustion stability of the combustion chamber, and thus improving the safety of the turbine.

[0034] Continue to refer Figure 3 , shows a process 300 of some embodiments of a method for manufacturing a combustion chamber air intake structure suitable for a pure hydrogen gas turbine according to the present disclosure. The method for manufacturing a combustion chamber air intake structure suitable for a pure hydrogen gas turbine is applied to Figure 1 The combustion chamber intake structure shown includes the following steps:

[0035] Step 301, obtaining an initial sector partition value corresponding to a target pure hydrogen gas turbine.

[0036] In some embodiments, an execution subject (e.g., a computing device) of a method for manufacturing a combustion chamber air intake structure for a pure hydrogen gas turbine may obtain an initial sector partition value corresponding to a target pure hydrogen gas turbine. The initial sector partition value may be a pre-set number of partitions for the secondary panel. As an example, the initial sector partition value may be 1, indicating that the second panel is not partitioned, and the number of fuel holes included in the secondary panel is 1.

[0037] Step 302: Based on the initial sector partition value, perform the following parameter confirmation steps:

[0038] Step 3021, creating an initial intake structure model according to the initial sector partition value.

[0039] In some embodiments, the execution entity may create an initial air intake structure model according to the initial sector partition value. The central angle of each sector in the initial air intake structure model is the ratio of the circumferential angle to the initial sector partition value. The initial air intake structure model may be a 3D model of the air intake structure.

[0040] Step 3022, determine the air intake volume of the sector segment according to the initial sector partition value and the secondary panel ratio value.

[0041] In some embodiments, the execution subject may determine the air intake volume of the sector segment according to the initial sector partition value and the secondary panel ratio value. In practice, the air intake volume of the sector segment may be determined by the following formula:

[0042]

[0043] Among them, m air Indicates the air intake volume of the fan-shaped segment. τ indicates the secondary panel ratio. Here, the secondary panel ratio is a preset value. For example, the secondary panel ratio can be 0.75. m t It represents the total air mass flow rate of the first and second panels. N represents the initial sector partition value.

[0044] Step 3023, determining the hydrogen intake amount of the sector segment according to the air intake amount of the sector segment and the preset equivalence ratio.

[0045] In some embodiments, the execution subject may determine the hydrogen intake amount of the sector according to the air intake amount of the sector and the preset equivalence ratio. The preset equivalence ratio may be an equivalence ratio at a predetermined combustion temperature. In practice, the hydrogen intake amount of the sector may be determined by the following formula:

[0046]

[0047] Among them, mair Indicates the air intake volume of the fan segment. θ indicates the preset equivalence ratio. m H2 Indicates the hydrogen intake amount of the sector.

[0048] Step 3024: Determine the micro-mixing tube fuel hole pressure corresponding to the micro-mixing tube according to the hydrogen intake amount and the air intake amount of the sector segment.

[0049] In some embodiments, the execution entity may determine the micro-mixing tube fuel hole pressure corresponding to the micro-mixing tube according to the hydrogen intake amount of the sector segment and the air intake amount of the sector segment.

[0050] Step 3025: In response to the micro-mixing tube fuel hole pressure satisfying a preset pressure condition, the initial intake structure model is determined as the combustion chamber intake structure.

[0051] In some embodiments, the execution subject may determine the initial intake structure model as the combustion chamber intake structure in response to the micro-mixing tube fuel hole pressure satisfying a preset pressure condition, wherein the preset pressure condition may be that the micro-mixing tube fuel hole pressure is less than or equal to a preset pressure threshold.

[0052] Step 3026, determining the diameter of the micro-mixing tube and the diameter of the fuel hole corresponding to the combustion chamber intake structure.

[0053] In some embodiments, the execution subject may obtain the micro-mixing tube diameter and the fuel hole diameter corresponding to the combustion chamber intake structure from a target database, wherein the target database may be a pre-set database for storing the micro-mixing tube diameter and the fuel hole diameter.

[0054] Step 303: Using the determined initial sector partition value, micro-mixing tube diameter, and fuel hole diameter as printing parameters, the associated 3D printer is controlled to perform a 3D printing manufacturing operation of the combustion chamber intake structure.

[0055] In some embodiments, the above-mentioned execution subject can use the determined initial sector partition value, the diameter of the micro-mixing tube and the diameter of the fuel hole as printing parameters to control the associated 3D printer to perform the combustion chamber intake structure 3D printing manufacturing operation. Among them, the above-mentioned associated 3D printer can be a 3D printer connected to the above-mentioned execution subject by wire or wireless connection. Here, the above-mentioned 3D printer can be a powder hot melt 3D printer. In practice, first, the above-mentioned initial intake structure model is sliced. Among them, the above-mentioned slicing process can be to adjust the parameters such as the printing layer thickness, filling density, and support structure. Second, according to the above-mentioned initial sector partition value, the diameter of the micro-mixing tube and the diameter of the fuel hole, the sliced ​​initial intake structure model is adjusted. Third, the adjusted model file is exported as a model file in a preset format. Among them, the above-mentioned preset format can be STL (STereoLithography, stereolithography) or OBJ format. Fourth, the model file in the preset format is imported into the above-mentioned 3D printer, and the metal powder is melted and deposited by the above-mentioned powder hot melt 3D printer, and the combustion chamber intake structure 3D printing manufacturing operation is performed on the initial intake structure model. The metal powder may be a powder material of metal GH3536. Fifth, in response to the completion of the three-dimensional printing manufacturing operation of the combustion chamber intake structure, the support structure of the printed initial intake structure model is removed. Sixth, the printed initial intake structure model is heat treated.

[0056] Optionally, the preset pressure threshold may be obtained through the following steps:

[0057] The first step is to obtain the preset combustion temperature threshold.

[0058] In some embodiments, the execution subject may obtain a preset combustion temperature threshold, wherein the preset combustion temperature threshold may be a preset combustion temperature threshold of the combustion chamber.

[0059] In practice, the preset combustion temperature threshold can be determined through the following sub-steps:

[0060] The first sub-step is to obtain the machine information corresponding to the target pure hydrogen gas turbine, wherein the machine information includes the combustion zone temperature distribution uniformity standard value, air intake temperature and combustion temperature.

[0061] In the second sub-step, the combustion zone temperature distribution uniformity standard value, the air intake temperature and the combustion temperature are substituted into the combustion zone temperature distribution uniformity standard value formula to obtain the maximum temperature of the combustion zone as the preset combustion temperature threshold. In practice, the combustion zone temperature distribution uniformity standard value formula is as follows:

[0062]

[0063] Among them, OTDF represents the standard value of temperature distribution uniformity in the combustion zone. max Indicates the preset combustion temperature threshold. T aver Indicates the combustion temperature (average temperature of the combustion zone). T2 indicates the air intake temperature.

[0064] The second step is to determine the maximum mass flow rate of hydrogen corresponding to the micro-mixing tube according to the above-mentioned preset combustion temperature threshold, and to determine the preset pressure threshold according to the above-mentioned maximum mass flow rate of hydrogen.

[0065] In some embodiments, the execution entity may determine the maximum mass flow rate of hydrogen corresponding to the micro-mixing tube according to the preset combustion temperature threshold, and determine the preset pressure threshold according to the maximum mass flow rate of hydrogen.

[0066] In practice, the preset pressure threshold can be determined through the following sub-steps:

[0067] In the first sub-step, the preset combustion temperature threshold is input into the pre-trained equivalence ratio determination model to obtain the equivalence ratio threshold. In practice, the equivalence ratio determination model may include a correspondence table of preset combustion temperature thresholds. The correspondence table may be a correspondence table based on the correspondence between a large number of preset combustion temperature thresholds and equivalence ratio thresholds by a person skilled in the art. In this way, the preset combustion temperature threshold is sequentially compared with a plurality of preset combustion temperature thresholds in the correspondence table. If a preset combustion temperature threshold in the correspondence table is the same as or similar to the preset combustion temperature threshold, the equivalence ratio threshold corresponding to the preset combustion temperature threshold in the correspondence table is used as the equivalence ratio threshold indicated by the preset combustion temperature threshold.

[0068] The second sub-step is to determine the air density value of the micro-mixing tube according to the air intake pressure, the air molecular weight and the air intake temperature. In practice, the air density value of the micro-mixing tube can be determined by the following formula:

[0069]

[0070] Among them, ρ air Indicates the air density value of the micro-mixing tube. P indicates the air intake pressure. M indicates the air molecular mass. T2 indicates the air intake temperature.

[0071] The third sub-step is to obtain the micro-mixing tube air flow rate value and the micro-mixing tube diameter. The micro-mixing tube air flow rate value may be the flow rate of air in a single micro-mixing tube. Here, the micro-mixing tube air flow rate value may be determined by the tempering boundary.

[0072] The fourth sub-step is to determine the air mass flow rate according to the air velocity value of the micro-mixing tube, the diameter of the micro-mixing tube and the air density value of the micro-mixing tube. In practice, the air mass flow rate can be determined by the following formula:

[0073]

[0074] Among them, m air Indicates the air mass flow rate. V indicates the air velocity value of the micro-mixing tube. D indicates the diameter of the micro-mixing tube.

[0075] The fifth sub-step is to determine the maximum mass flow rate of hydrogen according to the equivalence ratio threshold and the air mass flow rate. In practice, the maximum mass flow rate of hydrogen can be determined by the following formula:

[0076]

[0077] Among them, m H2，max Indicates the maximum mass flow rate of hydrogen. θ max Indicates the equivalence ratio threshold.

[0078] The sixth sub-step is to determine the number of micro-mixing tubes included in the sector segment as the number of micro-mixing tubes.

[0079] The seventh sub-step is to determine the total area of ​​hydrogen holes in the micro-mixing tubes according to the number of micro-mixing tubes and the diameter of the fuel holes in the micro-mixing tubes. In practice, first, the hydrogen hole area of ​​a single micro-mixing tube can be determined according to the diameter of the fuel holes in the micro-mixing tubes. Second, the total area of ​​hydrogen holes in the micro-mixing tubes is determined by multiplying the hydrogen hole area by the number of micro-mixing tubes.

[0080] The eighth sub-step is to obtain the micro-mixing tube air pressure value and the hydrogen density value. The micro-mixing tube air pressure value can be obtained by the diffuser intake pressure included in the combustion chamber. The micro-mixing tube air pressure value is approximately equal to the diffuser intake pressure.

[0081] The ninth sub-step is to determine a preset pressure threshold value according to the maximum mass flow rate of hydrogen, the air pressure value of the micro-mixing tube, the hydrogen density value and the total area of ​​hydrogen holes in the micro-mixing tube. In practice, the preset pressure threshold value can be determined by the following formula:

[0082] m H2，max =A = ρ H2 ×u.

[0083]

[0084] Where A represents the total area of ​​hydrogen holes in the micro-mixing tube. u represents the hydrogen inlet velocity in the micro-mixing tube. ρ H2 Represents the density of hydrogen. air Indicates the air pressure value of the micro-mixing tube. H2 Indicates the preset pressure threshold.

[0085] The above-mentioned first sub-step to the ninth sub-step and their related contents are an inventive point of the embodiment of the present disclosure. Combined with the above step "Step 3026", the second technical problem "When determining the hydrogen flow rate of the micro-mixing tube, the intake temperature of the air is not taken into account, resulting in the determined hydrogen flow rate not matching the actual hydrogen flow rate, which in turn results in a low mixing uniformity of air and hydrogen, a high risk of flashback of the nozzle installed in the middle of the intake structure, and an uneven distribution of the temperature at the outlet of the combustion chamber, resulting in low combustion stability of the combustion chamber and low safety of the turbine". The factors that lead to low combustion stability of the combustion chamber and low safety of the turbine are often as follows: When determining the hydrogen flow rate of the micro-mixing tube, the intake temperature of the air is not taken into account, resulting in the determined hydrogen flow rate not matching the actual hydrogen flow rate, which in turn results in a low mixing uniformity of air and hydrogen, a high risk of flashback of the nozzle installed in the middle of the intake structure, and an uneven distribution of the temperature at the outlet of the combustion chamber, resulting in low combustion stability of the combustion chamber and low safety of the turbine. If the above-mentioned factors are solved, the effect of improving the combustion stability of the combustion chamber and the safety of the turbine can be achieved. In order to achieve this effect, first, the above-mentioned preset combustion temperature threshold is input into the pre-trained equivalence ratio determination model to obtain the equivalence ratio threshold. Thus, the equivalence ratio value at the temperature of the preset combustion temperature threshold can be determined. Second, the micro-mixing tube air density value is determined according to the air intake pressure, the air molecular weight and the above-mentioned air intake temperature. Thus, the air density in the micro-mixing tube can be determined. Third, the micro-mixing tube air flow rate value and the micro-mixing tube diameter are obtained; the air mass flow rate is determined according to the above-mentioned micro-mixing tube air flow rate value, the micro-mixing tube diameter and the above-mentioned micro-mixing tube air density value. Thus, the air mass flow rate in the micro-mixing tube can be determined by the air density. Fourth, the maximum mass flow rate of hydrogen is determined according to the above-mentioned equivalence ratio threshold and the above-mentioned air mass flow rate. Thus, the maximum mass flow rate of hydrogen can be determined. Furthermore, the preset pressure threshold can be accurately determined. Fifth, the number of micro-mixing tubes included in the fan-shaped segment is determined as the number of micro-mixing tubes. Thus, the number of micro-mixing tubes on the secondary panel can be determined. Sixth, according to the number of micro-mixing tubes and the diameter of the fuel holes of the micro-mixing tubes, the total area of ​​the hydrogen holes of the micro-mixing tubes is determined; and the air pressure value and the hydrogen density value of the micro-mixing tubes are obtained. Thus, the relevant parameters of the micro-mixing tubes can be determined. Seventh, according to the maximum mass flow rate of hydrogen, the air pressure value of the micro-mixing tubes, the hydrogen density value and the total area of ​​the hydrogen holes of the micro-mixing tubes, the preset pressure threshold is determined. Thus, the pressure threshold can be determined. Combined with the step "step 3026" above, the diameter of the micro-mixing tube and the diameter of the fuel hole corresponding to the intake structure of the combustion chamber are determined, and according to the initial sector partition value, the diameter of the micro-mixing tube and the diameter of the fuel hole, the associated three-dimensional printing device is controlled to perform the intake structure manufacturing operation. Thus, the low mixing uniformity of air and hydrogen in the manufactured intake structure of the combustion chamber is avoided, the uniformity of the temperature distribution at the outlet of the combustion chamber is ensured, and the combustion stability of the combustion chamber and the safety of the turbine are improved.

[0086] Optionally, after step 302, in response to the micro-mixing tube fuel hole pressure not satisfying the preset pressure condition, the sum of the initial sector partition value and the preset value is determined as the sector partition value, and the sector partition value is used as the initial sector partition value to perform the parameter confirmation step again.

[0087] In some embodiments, the execution entity may determine the sum of the initial sector partition value and the preset value as the sector partition value in response to the micro-mixing tube fuel hole pressure not satisfying the preset pressure condition, and use the sector partition value as the initial sector partition value to execute the above steps again.

[0088] The above-mentioned embodiments of the present disclosure have the following beneficial effects: through the combustion chamber intake structure applicable to pure hydrogen gas turbines of some embodiments of the present disclosure, the combustion stability of the combustion chamber and the safety of the turbine are improved. Specifically, the reason for the low combustion stability of the combustion chamber and the low safety of the turbine is that when the fuel hole structure delivers fuel, the mixing uniformity of air and hydrogen is low, resulting in a high risk of flashback of the nozzle installed in the middle of the intake structure, resulting in uneven distribution of the combustion chamber outlet temperature, thereby causing low combustion stability of the combustion chamber and low safety of the turbine. Based on this, the manufacturing method of the combustion chamber intake structure applicable to pure hydrogen gas turbines of some embodiments of the present disclosure, first, obtain the initial sector partition value corresponding to the target pure hydrogen gas turbine. Thus, the initial partition of the intake structure can be determined. Second, based on the initial sector partition value, the following parameter confirmation step is performed: First, according to the above initial sector partition value, an initial intake structure model is created. Thus, the initial model can be established according to the initial sector partition value. Secondly, according to the above initial sector partition value and the secondary panel proportion value, the air intake amount of the sector segment is determined. Thus, the amount of air entering a single sector segment can be determined. Then, according to the air intake amount of the above-mentioned sector segment and the preset equivalence ratio, the hydrogen intake amount of the sector segment is determined. Thus, the intake amount of hydrogen fuel entering a single sector tube can be determined. Afterwards, according to the hydrogen intake amount of the above-mentioned sector segment and the air intake amount of the above-mentioned sector segment, the micro-mixing tube fuel hole pressure corresponding to the micro-mixing tube is determined. Thus, the intake pressure can be determined. Then, in response to the micro-mixing tube fuel hole pressure meeting the preset pressure condition, the initial intake structure model is determined as the intake structure of the combustion chamber. Thus, when the manufacturing of the initial model meets the pressure requirements, the initial model can be determined as the intake structure of the combustion chamber. Then, the micro-mixing tube diameter and the diameter of the fuel hole corresponding to the intake structure of the combustion chamber are determined. Thus, the diameter of the micro-mixing tube and the diameter of the fuel hole of the printed initial intake structure model can be determined. Finally, the determined initial sector partition value, the micro-mixing tube diameter and the diameter of the fuel hole are used as printing parameters to control the associated 3D printer to perform the 3D printing manufacturing operation of the intake structure of the combustion chamber. Thus, the intake structure of the combustion chamber is manufactured. Also, because the pressure requirements are met through the intake structure of the combustion chamber, the air and hydrogen can be evenly mixed, which improves the mixing uniformity, reduces the risk of flashback of the nozzle installed in the middle of the intake structure, ensures the uniformity of the combustion chamber outlet temperature distribution, and thereby improves the combustion stability of the combustion chamber and the safety of the turbine.

[0089] 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 air intake structure suitable for a pure hydrogen gas turbine, wherein: The combustion chamber intake structure includes: a primary panel, a secondary panel, at least one partition and at least one fuel hole, wherein the secondary panel includes five fan-shaped segments, each of the five fan-shaped segments includes at least one micro-mixing tube and a fuel hole, the micro-mixing tube diameter of each micro-mixing tube in the at least one micro-mixing tube is 3 to 5 mm, and one end of each micro-mixing tube is located in the micro-mixing tube arrangement area of ​​the corresponding fan-shaped segment, The primary panel is located at the center of the secondary panel, an ignition hole is provided at the center of the primary panel, an igniter and a fuel nozzle are installed in the ignition hole; Each of the at least one partition is located between two adjacent sectors, and each partition is used to separate two adjacent sectors; Each of the fuel holes is opened at the center of the corresponding sector segment, and each fuel hole is used to install a fuel pipe, and one end of the fuel pipe is connected to the corresponding fuel hole.

2. The combustion chamber air intake structure suitable for a pure hydrogen gas turbine according to claim 1, wherein: The central angle of each sector is 72 degrees.

3. The combustion chamber air intake structure suitable for a pure hydrogen gas turbine according to claim 1, wherein: The diameter of the fuel hole is 22 to 26 mm; The length of the fuel pipe installed at each fuel hole is 260 mm.

4. The combustion chamber air intake structure suitable for a pure hydrogen gas turbine according to claim 1, wherein: Each micro-mixing tube further includes a micro-mixing tube fuel hole, and the positions of the micro-mixing tube fuel holes included in each micro-mixing tube are the same; The micro-mixing tube fuel holes are arranged on the side of the corresponding micro-mixing tube, and the diameter of each micro-mixing tube fuel hole is 0.4-0.7 mm.

5. A method for manufacturing a combustion chamber air intake structure suitable for a pure hydrogen gas turbine according to any one of claims 1 to 4, the manufacturing method comprising: Obtaining an initial sector partition value corresponding to a target pure hydrogen gas turbine; Based on the initial sector partition value, perform the following parameter confirmation steps: Creating an initial air intake structure model according to the initial sector partition value, wherein the central angle of each sector segment in the initial air intake structure model is the ratio of the circumferential angle to the initial sector partition value; Determine the air intake volume of the sector segment according to the initial sector partition value and the secondary panel proportion value; Determining the hydrogen intake amount of the sector according to the air intake amount of the sector and a preset equivalence ratio; Determining the micro-mixing tube fuel hole pressure corresponding to the micro-mixing tube according to the hydrogen intake amount of the sector segment and the air intake amount of the sector segment; In response to the micro-mixing tube fuel hole pressure satisfying a preset pressure condition, determining the initial intake structure model as a combustion chamber intake structure, wherein the preset pressure condition is that the micro-mixing tube fuel hole pressure is less than or equal to a preset pressure threshold; Determining the diameter of the micro-mixing tube and the diameter of the fuel hole corresponding to the combustion chamber intake structure; The determined initial sector partition value, the micro-mixing tube diameter and the fuel hole diameter are used as printing parameters to control the associated three-dimensional printer to perform a three-dimensional printing manufacturing operation of the combustion chamber intake structure.

6. The manufacturing method according to claim 5, wherein: The method further comprises: In response to the micro-mixing tube fuel hole pressure not satisfying the preset pressure condition, the sum of the initial sector partition value and the preset value is determined as the sector partition value, and the sector partition value is used as the initial sector partition value to perform the parameter confirmation step again.

7. The manufacturing method according to claim 5, wherein: The preset pressure threshold is obtained by the following steps: Obtaining a preset combustion temperature threshold; According to the preset combustion temperature threshold, a maximum mass flow rate of hydrogen corresponding to the micro-mixing tube is determined, and according to the maximum mass flow rate of hydrogen, a preset pressure threshold is determined.

8. The manufacturing method according to claim 7, wherein: The preset combustion temperature threshold is determined by the following steps: Acquiring machine information corresponding to the target pure hydrogen gas turbine, wherein the machine information includes a combustion zone temperature distribution uniformity standard value, an air intake temperature, and a combustion temperature; The combustion zone temperature distribution uniformity standard value, the air intake temperature and the combustion temperature are substituted into the combustion zone temperature distribution uniformity standard value formula to obtain the combustion zone maximum temperature as the preset combustion temperature threshold.

Images