Head modeling method applied to integrated pneumatic design of combustion chamber turbine of ground heavy-duty gas turbine

Abstract

The invention discloses a head modeling method applied to integrated pneumatic design of a combustion chamber turbine of a ground heavy-duty gas turbine, which comprises the following steps of: analyzing the characteristics of a micro-mixing combustion chamber in the ground heavy-duty gas turbine to obtain the downstream flow field characteristics of the micro-mixing combustion chamber, namely a heat transfer combustion calculation result; the pure pneumatic calculation result is compared with the heat transfer combustion calculation result, the pure pneumatic calculation is used for replacing the heat transfer combustion calculation, flow characteristics are simulated through the pure pneumatic calculation, and the flow characteristics comprise pressure and speed; based on a pure pneumatic state, comparing the difference of flow fields at the outlets of the annular pipe type and the circular pipe type; and simulating the characteristics of the micro-mixing head by adopting a source item jet modeling method. The method can be applied to the aerodynamic design process of the ground heavy-duty gas turbine combustion and spraying combination, and the design time cost is reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of ground heavy-duty gas turbines, and particularly relates to a head modeling method applied to the integrated aerodynamic design of a combustor turbine of a ground heavy-duty gas turbine. Background Technique

[0002] For ground heavy-duty gas turbines, aiming at the integration of the combustor and guide vanes, a design strategy of "reducing the number of guide vanes and extending the partition forward integrally" is proposed, which can effectively reduce the cooling air consumption, but may reduce the working efficiency to a certain extent and has certain reference significance. On the contrary, in the industrial field, many companies at home and abroad have developed heavy-duty gas turbines with different power levels, and have developed mature heavy-duty gas turbines and put them into use in large quantities. These companies have made corresponding attempts and breakthroughs in the integrated design of the combustor turbine. With the support of the US Department of Energy, GE Company in the United States took the lead in starting the coupled design of the combustor turbine guide vanes (combustion injection consortium), and set the cycle efficiency of the next-generation heavy-duty gas turbine at 65%, taking this as the goal to drive the advancement of the combustor turbine coupling scheme.

[0003] In the early design and development process of the combustion injection consortium, as an advanced combustion technology, micro-mixing combustion has become an indispensable part of the design system of the combustion injection consortium. After the micro-mixing head adopts multiple ring-shaped micro-mixing fuel nozzles for array, it is arranged in the head area of the combustion injection consortium. The micro-mixing combustion scheme greatly improves the combustion uniformity and combustion stability. The short combustion distance combined with the dense micro-mixing arrangement makes the non-uniformity of the temperature field disappear due to the mixing effect between the micro-mixing pipes within an extremely short length. At the same time, the array arrangement can help the adjacent nozzles for re-ignition. For micro-mixing combustion, during the early aerodynamic optimization design, a large number of calculation cases need to be iterated. Considering the micro-mixing hole combustion greatly limits the speed of aerodynamic optimization design. One is that due to the small size of the micro-mixing pipes in the head, the number of grids surges during the overall calculation; the other is that the calculation efficiency decreases after adding the combustion reaction for calculation, which indicates that considering the micro-mixing combustion head is not conducive to the design process during the early aerodynamic optimization design.

[0004] In summary, how to consider the influence of micro-mixing head combustion in the early stage of aerodynamic design and reduce the aerodynamic design optimization time requires in-depth research and discussion to obtain a compromise modeling scheme. Summary of the Invention

[0005] To solve the above technical problems, the present invention proposes a head modeling method applied to the integrated aerodynamic design of a combustor turbine of a ground heavy-duty gas turbine to solve the problems existing in the above prior art.

[0006] To achieve the above object, in a first aspect, the present invention provides a head modeling method applied to the integrated aerodynamic design of a ground heavy-duty gas turbine combustor turbine, including:

[0007] Analyze the characteristics of the micro-mixing combustor in the ground heavy-duty gas turbine to obtain the flow field characteristics downstream of the micro-mixing combustor, that is, the heat transfer combustion calculation results;

[0008] Compare the pure aerodynamic calculation with the heat transfer combustion calculation results, and replace the heat transfer combustion calculation with the pure aerodynamic calculation. Simulate the flow characteristics through the pure aerodynamic calculation, and the flow characteristics include pressure and velocity;

[0009] Based on the pure aerodynamic state, compare the differences in the flow fields at the exits of the annular tube type and the circular tube type;

[0010] Adopt the source term method jet modeling method to simulate the characteristics of the micro-mixing head.

[0011] Preferably, the micro-mixing combustor includes the upper wall surface of the fuel injection combination body, the partition wall surface of the fuel injection combination body, the first periodic surface of the fuel injection combination body, the lower wall surface of the fuel injection combination body, the micro-mixing annular tube channel of the fuel injection combination body, the second periodic surface of the fuel injection combination body, the circular tube channel of the fuel injection combination body, and the point source center of the fuel injection combination body.

[0012] Preferably, the upper wall surface of the fuel injection combination body, the partition wall surface of the fuel injection combination body, and the lower wall surface of the fuel injection combination body together form a flow passage for the mainstream gas.

[0013] Preferably, the first periodic surface of the fuel injection combination body, the second periodic surface of the fuel injection combination body, the upper wall surface of the fuel injection combination body, the partition wall surface of the fuel injection combination body, and the lower wall surface of the fuel injection combination body form a fluid domain, and the mainstream gas flows through the middle.

[0014] Preferably, the first periodic surface of the fuel injection combination body and the second periodic surface of the fuel injection combination body are used as rotating periodic surfaces. After the rotating periodic surfaces rotate and array around the rotating array center and overlap, they generate the original annular combustor structure.

[0015] Preferably, comparing the differences in the flow fields at the exits of the annular tube type and the circular tube type includes:

[0016] Calculate the annular tube area of the original annular combustor structure;

[0017] According to the annular tube area, simplify the annular tube type nozzle into a circular tube type micro-mixing nozzle according to the equal area law to ensure that the flow velocity and flow momentum before and after modeling are consistent.

[0018] Preferably, the annular tube area of the annular tube type nozzle is:

[0019]

[0020] The annular area of the circular tube type micro-mixing nozzle is:

[0021]

[0022] d is the inner diameter of the annular tube, D is the outer diameter of the annular tube, and De is the diameter of the circular tube type structure.

[0023] Preferably, the simulation of the micro-mixing head characteristics by using the source term method jet modeling method includes:

[0024] Defining the hole center by using a point source, and further modeling the circular tube type micro-mixing head;

[0025] For each hole center, setting the jet radius;

[0026] Setting the flow rate at each point source position.

[0027] Preferably, the jet radius is:

[0028] r = 1 / 2De

[0029] Wherein, the point source center is the center of the circular tube, and De is the diameter of the circular tube type structure.

[0030] The present invention also provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the steps of the method are implemented.

[0031] Compared with the prior art, the present invention has the following advantages and technical effects:

[0032] The present invention provides a head modeling method applied to the integrated aerodynamic design of the combustor turbine of a ground heavy-duty gas turbine. First, analyze the characteristics of the micro-mixing combustor in the ground heavy-duty gas turbine to obtain the downstream flow field characteristics of the micro-mixing combustor, that is, the heat transfer combustion calculation results; secondly, compare the pure aerodynamic calculation with the heat transfer combustion calculation results, and replace the heat transfer combustion calculation with the pure aerodynamic calculation, and simulate the flow characteristics through the pure aerodynamic calculation, and the flow characteristics include pressure and velocity; then, based on the pure aerodynamic state, compare the differences in the flow fields at the outlets of the annular tube type and the circular tube type; finally, use the source term method jet modeling method to simulate the micro-mixing head characteristics.

[0033] The present invention innovatively proposes a modeling and simulation method based on the flow field characteristics of the micro-mixing head, which reduces the original large memory grid and long-cycle calculation process. This modeling method combines the complex head characteristics of the micro-mixing head and also greatly reduces the design and simulation cost, and can be applied to the aerodynamic design process of the combustor and injector combination of the ground heavy-duty gas turbine to reduce the design time cost. Description of the Drawings

[0034] The accompanying drawings, which form a part of this application, are used to provide a further understanding of this application. The schematic embodiments and descriptions thereof of this application are used to explain this application and do not constitute an improper limitation of this application. In the drawings:

[0035] Figure 1 Schematic diagram of the fuel injection and combustion combination scheme of the embodiment of the present invention;

[0036] Figure 2 Flow chart of the micro-hybrid modeling analysis of the embodiment of the present invention;

[0037] Figure 3 Schematic diagram of the micro-hybrid modeling analysis of the embodiment of the present invention;

[0038] Figure 4 Schematic diagram of the flow field analysis of the embodiment of the present invention;

[0039] Figure 5 Schematic diagram of the flow analysis of the annular nozzle and circular nozzle in a pure pneumatic environment of the embodiment of the present invention;

[0040] Figure 6 Schematic diagram of the flow analysis of the circular nozzle and point source modeling in a pure pneumatic environment of the embodiment of the present invention. Detailed implementation manners

[0041] It should be noted that, without conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The following will refer to the accompanying drawings and combine with the embodiments to detail this application.

[0042] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0043] Embodiment 1

[0044] In this embodiment, a head modeling method applied to the integrated pneumatic design of the combustor and turbine of a ground heavy-duty gas turbine is provided, including:

[0045] S1. Analyze the characteristics of the micro-hybrid combustor in the ground heavy-duty gas turbine to obtain the flow field characteristics downstream of the micro-hybrid combustor, that is, the heat transfer and combustion calculation results;

[0046] The head mentioned in this embodiment is a micro-hybrid combustion head, and its combustion mainly occurs through the micro-hybrid pipes of the head. The fuel and air are mixed inside the annular pipe, and the mixing uniformity continuously improves along the way. After being ejected at the outlet position, isobaric combustion occurs.

[0047] In order to demonstrate the overall solution and elaborate in detail on the implementation structure of the specific solution, when presenting, after dividing the geometric region of the model using rotational periodic boundaries, one structural unit is selected for display. For the combustion and injection combined structure, the overall structure mainly includes a micro-mixing combustion chamber, an axial staging combustion scheme, and an integrated design of the combustion chamber guide vanes. After the combustion chamber and the guide vanes are connected as a whole, they are connected to the downstream moving blades.

[0048] The structure described in this embodiment and the structure shown in the drawing represent a periodic model unit. After the upper and lower wall surfaces rotate around a rotation axis, the left and right end faces can completely coincide. In reality, it should be an annular combustion chamber. Using a periodic unit to describe it is for one purpose of simplifying the modeling and for another to better describe the concept and structure of the integrated solution. The modular solution specifically analyzes the flow field characteristics with combustion. During the downstream migration of the micro-mixing combustion velocity field and temperature field, the non-uniformity gradually weakens, and its mixing distance is relatively short. On this basis, combined with the combustion simulation characteristics, a pure aerodynamic CFD calculation solution is adopted, and the mainstream high-temperature gas is directly ejected from the annular tube channel. The high-temperature gas still maintains the outflow characteristics under the original combustion conditions, and its non-uniformity gradually attenuates during the downstream migration process, similar to the flow field distribution presented under the original combustion conditions.

[0049] The micro-mixing combustion chamber described herein mainly consists of the following structures: the upper wall surface 1 of the combustion and injection combined body, the partition wall surface 2 of the combustion and injection combined body, the first periodic surface 3 of the combustion and injection combined body, the lower wall surface 4 of the combustion and injection combined body, the micro-mixing annular tube channel 5 of the combustion and injection combined body, the second periodic surface 6 of the combustion and injection combined body, the circular tube channel 7 of the combustion and injection combined body, and the point source center 8 of the combustion and injection combined body. Among them, the upper wall surface 1 of the combustion and injection combined body, the partition wall surface 2 of the combustion and injection combined body, and the lower wall surface 4 of the combustion and injection combined body together form the flow passage for the mainstream gas.

[0050] The structural dimensions of the entire combustion chamber stage conform to the structural design of an actual heavy-duty gas turbine. Among them, the upper wall surface 1 of the combustion and injection combined body and the lower wall surface 4 of the combustion chamber stage together form the flow passage for the mainstream gas, which flows from a high radius to a low radius. The number of units arrayed in the circumferential range of the partition wall surface 2 of the combustion and injection combined body can be selected from 18 to 24. In this embodiment, the number of units used is 20. The derivative design of the aerodynamic parameters involved will not be elaborated here.

[0051] The micro-mixing combustion chamber is located at the uppermost upstream of the overall structural scheme diagram. The mainstream gas from the compressor passes through this place and mixes with the fuel. At the same time, a part of the cooling gas in the front cavity also flows through here. After mixing, combustion occurs. At this time, due to the relatively small fuel component, it is lean combustion, resulting in relatively few pollutant emissions.

[0052] S2. Compare the pure pneumatic calculation with the heat transfer combustion calculation results, and replace the heat transfer combustion calculation with the pure pneumatic calculation. Simulate the flow characteristics through the pure pneumatic calculation, where the flow characteristics include pressure and velocity.

[0053] Figure 1 Shows the overall scheme of a new type of first-stage high-pressure turbine with a combustion and injection combined structure, including the combustion and injection combined structure. As Figure 1 shown, the micro-mixing combustion chambers are densely arranged upstream and evenly distributed in the entire inlet position area. As Figure 4 shown, for the combustion characteristics of the micro-mixing combustion chamber, corresponding combustion simulations are carried out. The overall simulation uses commercial software. After the mesh is drawn with polyhedral meshes, the K-w SST turbulence model is adopted, the combustion component reaction model is turned on, and CFD simulation calculations are performed. For the mass fraction contour map, the hydrogen component gradually diffuses downstream of the micro-mixing nozzle. At the position D, which is 5 times the outer ring diameter of the nozzle downstream, the hydrogen component is uniform and the value is zero, indicating that the combustion reaction is completed; for the temperature contour map, the temperature at the nozzle outlet rises rapidly, and the temperature in the outflow area continues to diffuse. At the position D, which is 6 times the outer ring diameter of the nozzle downstream, the temperature contour map is uniform; while for the velocity contour map, it shows a distribution characteristic similar to that of the temperature and mass fraction contour maps.

[0054] In summary, for the flow field characteristics downstream of the micro-mixing combustion chamber, the combustion process expands at the downstream outlet, rapidly mixes within a short distance, and the jet characteristics only remain within the range of 5D - 6D lengths and tend to be uniform at the downstream position. The head of this combustion unit is an array of 9 micro-mixing pipes. After being drawn with polyhedral meshes, there are 6 million meshes in total. If it is mapped to the inlet section, the number of meshes will soar to 70 million. For this micro-mixing combustion characteristic, a micro-mixing inlet modeling study is carried out.

[0055] S3. Based on the pure pneumatic state, compare the differences in the flow fields at the outlets of the annular pipe type and the circular pipe type.

[0056] S4. Use the source term method jet modeling method to simulate the characteristics of the micro-mixing head.

[0057] As Figure 2 and Figure 3 shown, based on the characteristics of the micro-mixing combustion holes, first conduct an annular pipe pneumatic modeling study. The annular pipe structure 5 is shown in Figure 3 , and then simplify the annular pipe structure into a circular pipe structure 7. Compare the modeling schemes under different structures, and finally simplify the circular pipe structure 7 into a point source simplified model 8. The final modeling uses the point source simplified model.

[0058] The micro-mixing annular pipe channel 5 of the combustion and injection combined body consists of inner and outer rings. The inner ring diameter is defined as d, and the outer ring diameter is defined as D. According to the area calculation formula, the area of the annular pipe can be obtained Design it according to the high-level 300MW size of the ground heavy-duty gas turbine. The inner ring diameter d is generally selected in the range of 20 - 30mm, and it is selected in combination with the micro-mixing hole arrangement scheme. The outer ring diameter D has a certain quantitative relationship with the inner ring diameter d. The outer ring diameter D is generally selected as 1.4 - 1.6 times the inner ring diameter d, which is determined according to the final value of the inner ring diameter.

[0059] The circular tube structure 7 has a single diameter definition. Define the diameter of the circular tube structure 7 as De, which can be calculated according to the formula. From the multiple relationship between the outer ring diameter D and the inner ring diameter d of the annular tube, the circular tube diameter is generally 0.98 - 1.24 times the inner ring diameter d of the annular tube.

[0060] The point source simplified model is further optimized on the basis of the circular tube type. The center of the point source is the center of the circular tube, which represents the center position of the micro-mixing combustion nozzle. Define the radius as r, and this radius r = 1 / 2De. Given the flow boundary at each micro-mixing hole position, the above-mentioned modeling is simulated by the meshless method. The concentrator is embedded in the solver. Since the mesh at the inlet position does not have a regular geometric shape after discretization, it is difficult to complete the flow convergence by giving the inlet velocity distribution by conventional interpolation. For this, the meshless method takes the flow numerical value as the constraint and solves the convergence by itself, and appropriately scales the convergence problem of conventional interpolation to complete the calculation.

[0061] To specifically show the structural dimensions and verify the feasibility of the modeling method, a specific embodiment is used for illustration. In this embodiment, the selected inner diameter of the annular tube is 20mm, the outer diameter is 30mm, the corresponding selected circular tube diameter is 23mm, and a total of 240 micro-mixing heads are arranged at the head of the single channel, which are evenly arranged at the head position. The aerodynamic parameters set in the CFD calculation process will not be elaborated here.

[0062] The micro-mixing modeling scheme of the circular tube type structure can be designed as a point source simplified jet. The specific idea is to extract the original center of the circular tube as the center point of all micro-mixing point sources, and define the jet direction, jet flow rate and jet radius for each center point, and use the meshless method to give the boundary conditions.

[0063] The calculation scheme of the annular tube type micro-mixing tube under pure aerodynamics can be changed to the calculation scheme of the circular tube under pure aerodynamics. The above-mentioned scheme modeling is obtained based on the flow field analysis. Under pure aerodynamic CFD calculation, there is a low-speed region at the outlet position of the annular tube type, mainly due to the lack of jet at the center of the annular tube. However, at about 0.5D downstream, due to the diffusion of the jet, the low-speed region has been filled by the adjacent side airflow, forming a jet similar to a circular tube shape. The specific analysis of this modeling scheme is carried out by comparing after CFD aerodynamic calculation.

[0064] Such as Figure 5As shown in the figure, the downstream velocity contour distributions of the annular micro-mixing nozzle and the circular tube micro-mixing nozzle under pure pneumatic calculation conditions are presented. The velocity contour comparisons at different cross-section positions are carried out. As shown in the figure, at the downstream position of 5 mm, that is, the nozzle outflow position, a significant annular tube velocity distribution characteristic appears under the annular tube micro-mixing nozzle at this cross-section. Similarly, a significant circular tube jet characteristic appears under the circular tube micro-mixing nozzle, which is mainly due to the flow field differences caused by the geometric structure itself. During the further migration downstream, when the cross-section at 33 mm downstream is intercepted, there is similarity in the flow fields between the two. The original annular jet forms a circular tube jet as the low-speed area in the center is quickly filled by the fluid due to the uneven pressure distribution. Combining the analysis of the micro-mixing unit results, it can be obtained that this modeling scheme is feasible. When at the cross-section 51 mm downstream, the flow fields under the two calculation methods are both uniform. The modeling scheme from the annular tube jet to the equal-area circular tube jet is feasible.

[0065] As Figure 6 shown, for the circular tube jet, the point source modeling method is used for further simplification. The center position of the jet of the circular tube 7 is defined as the center 8 of the combustion-injection combined point source. After being defined by the meshless source term method, three-dimensional CFD simulation calculations are carried out. At the cross-section 5 mm downstream, the velocity field of the circular tube jet can be clearly observed. The point source method effectively reproduces the flow field of the circular tube jet, showing significant non-uniformity at the outlet position. During the further migration downstream, when reaching the cross-section position of 31 mm, the non-uniformity of the flow field weakens, but the core of the high-speed flow field is still retained. The point source modeling method well captures this diffusion and mixing process, presenting a similar high-speed flow field distribution. The flow field tends to be uniform after reaching the cross-section of 57 mm.

[0066] The beneficial effects of this embodiment:

[0067] In this embodiment, a head modeling scheme applied to the integrated aerodynamic design of the combustor turbine of a ground heavy-duty gas turbine is designed. First, the combustion characteristics and downstream aerodynamic characteristics of the micro-mixing combustion tube are analyzed. Based on the simulation calculation analysis, a pure pneumatic modeling design is carried out. During the preliminary aerodynamic design, an annular tube structure is used to simulate the micro-mixing head with combustion, and the similarity of the flow is verified. On this basis, on the premise of ensuring the outflow velocity and momentum conservation, the annular tube structure is modeled into a circular tube, further simplifying the calculation structure of the micro-mixing head. Then, the point source method is used to define the center hole position of the micro-mixing jet. The meshless method is used, and the flow rate and temperature are used as boundary condition constraints. Taking the micro-mixing jet position as the center and the circular tube diameter as the jet region for modeling calculations, the feasibility of the point source method is verified. Finally, the following micro-mixing modeling method is formed: Micro-mixing hole point sources are arranged in the head array of the combustion-injection combined body, and each point source corresponds to a diameter and a flow rate value. The solver uses the meshless matching convergence method for calculation.

[0068] This embodiment can effectively capture the aerodynamic characteristics downstream of the micro-mixing combustion head, and at the same time can significantly reduce the consumption of computing resources and computing time during the calculation process, taking into account both calculation accuracy and calculation cost. It can be used for the rapid design and optimization in the aerodynamic design stage of the fuel injection and combustion combination, and becomes a new type of head modeling scheme considering aerodynamic design. In other fields, such as when this method is adopted for the position of dense hole jets, the simulation time can be effectively shortened.

[0069] While considering the outflow characteristics of the micro-mixing combustion holes and their influence on the downstream, this embodiment reduces the number of meshes drawn, reduces the time of the simulation process, and finally reduces the time cost of aerodynamic design optimization.

[0070] Embodiment 2

[0071] This embodiment also discloses a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the steps of the method described in Embodiment 1 are implemented.

[0072] The above is only the preferred specific embodiment of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A head scaling method applied to the integrated aerodynamic design of the combustor and turbine of a ground heavy-duty gas turbine, characterized in that Including: Analyze the characteristics of the micro - mixing combustion chamber in a ground - based heavy - duty gas turbine to obtain the flow - field characteristics downstream of the micro - mixing combustion chamber, that is, the calculation results of heat transfer and combustion. Compare the pure aerodynamic calculation with the calculation results of heat transfer and combustion, and replace the heat - transfer combustion calculation with the pure aerodynamic calculation. Simulate the flow characteristics through the pure aerodynamic calculation, and the flow characteristics include pressure and velocity. Based on the pure aerodynamic state, compare the differences in the flow fields at the outlets of the annular - tube type and the circular - tube type. Use the source - term method jet - modeling method to simulate the characteristics of the micro - mixing head.

2. The method according to claim 1, wherein: The micro - mixing combustion chamber includes the upper wall surface (1) of the fuel - injection combination body, the partition wall surface (2) of the fuel - injection combination body, the first periodic surface (3) of the fuel - injection combination body, the lower wall surface (4) of the fuel - injection combination body, the micro - mixing annular - tube channel (5) of the fuel - injection combination body, the second periodic surface (6) of the fuel - injection combination body, the circular - tube channel (7) of the fuel - injection combination body, and the point - source center (8) of the fuel - injection combination body.

3. The method according to claim 2, wherein: The upper wall surface (1) of the fuel - injection combination body, the partition wall surface (2) of the fuel - injection combination body, and the lower wall surface (4) of the fuel - injection combination body together form the flow - through channel for the main - stream gas.

4. The method according to claim 2, wherein: The first periodic surface (3) of the fuel - injection combination body, the second periodic surface (6) of the fuel - injection combination body, the upper wall surface (1) of the fuel - injection combination body, the partition wall surface (2) of the fuel - injection combination body, and the lower wall surface (4) of the fuel - injection combination body form a fluid domain, and the main - stream gas flows through the middle.

5. The method according to claim 2, wherein: The first periodic surface (3) of the fuel - injection combination body and the second periodic surface (6) of the fuel - injection combination body are used as rotating periodic surfaces. After the rotating periodic surfaces rotate around the rotation - array center and overlap, they generate the original annular combustion - chamber structure.

6. The method according to claim 5, wherein: The differences in the flow fields at the outlets of the annular - tube type and the circular - tube type include: Calculate the annular - tube area of the original annular combustion - chamber structure. According to the annular - tube area, simplify the annular - tube type nozzle into a circular - tube type micro - mixing nozzle according to the equal - area rule to ensure that the flow velocity and flow momentum before and after modeling are consistent.

7. The method according to claim 1, wherein: The annular - tube area of the annular - tube type nozzle is: The annular - tube area of the circular - tube type micro - mixing nozzle is: d is the inner diameter of the annular tube, D is the outer diameter of the annular tube, and De is the diameter of the circular - tube type structure.

8. The method according to claim 1, wherein: Using the source - term method jet - modeling method to simulate the characteristics of the micro - mixing head includes: Use the point - source definition hole center to further model the circular - tube type micro - mixing head. For each hole center, set the jet radius. Set the flow rate at each point - source position.

9. The method according to claim 8, wherein: The jet radius is: r = 1 / 2De Wherein, the point - source center is the center of the circular tube, and De is the diameter of the circular - tube type structure.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it realizes the steps of the method according to any one of claims 1 - 9.

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