Accelerated calculation method, device and equipment for thermal spraying multi-component jet flow field and medium

Abstract

The invention provides an accelerated calculation method, device, equipment and medium for a thermal spraying multi-component jet flow field, and the method comprises the steps: carrying out the initialization of a global flow field according to a given initial condition, and enabling the initial condition to comprise an incoming flow parameter and a jet flow parameter; the temperature of the flow field is solved according to a full-computational-domain Newton iteration method, ten thousand steps of preliminary numerical calculation of the thermal spraying multi-component jet flow field are carried out, and the preliminary temperature of all grid blocks in the whole domain is obtained; recognizing a grid domain far away from the jet flow and the wall surface based on a flow field boundary condition, and applying a temperature criterion to the recognized grid domain; and according to the result of the temperature criterion, temperature updating is performed on the global grid domain, and flow field numerical calculation is continuously performed until the flow field converges, so that the problems of discrimination and correction of the temperature calculation method of the calculation domain and proper improvement of the calculation efficiency of the thermal spraying multi-component jet flow field are solved.

Description

Technical Field

[0001] This invention relates to the field of computational fluid dynamics (CFD) technology, and in particular to an accelerated calculation method, apparatus, equipment and medium for thermally sprayed multi-component jet flow fields. Background Technology

[0002] Reaction control systems (RCS) utilize the direct force generated by engine exhaust to achieve rapid changes in aircraft attitude and trajectory. They can serve as a powerful supplement to traditional aerodynamic control surfaces and have significant engineering application value.

[0003] In recent years, with the rapid development of new air defense, anti-missile, and anti-adventure weapons, simulations of multi-component thermal jet flow fields containing complex physicochemical effects—which more closely resemble real flight conditions—have become increasingly common to meet the demands for stable control, high maneuverability, and precision strikes. Compared to traditional cold-jet simulation techniques, these often significantly reduce the stability and computational efficiency of numerical methods.

[0004] Numerical simulations of cold-jet flow fields are typically based on the calorimetric assumption of a perfect gas, where internal energy and temperature remain linear, and temperature can be directly and explicitly solved for. In contrast, the internal energy and temperature of a thermally sprayed multi-component flow field are no longer linearly related, and temperature cannot be explicitly solved for. Therefore, temperature can only be solved by applying Newton's iteration method to the enthalpy polynomial given an initial temperature value.

[0005] Traditional numerical calculations of multi-component flow fields in thermal spraying always use the Newton-Raphson iteration method to solve for temperature within the global grid. However, for the external flow domain, which is not affected by the jet flow and is near the wall, the temperature is very close to the external flow temperature. Using the Newton-Raphson iteration method to solve for temperature increases the amount of redundant calculations, which reduces the computational efficiency of the numerical program.

[0006] Therefore, it is urgent to propose an accelerated calculation method for the flow field of thermally sprayed multi-component jets to solve the problem of judging and correcting the temperature calculation method in the computational domain and appropriately improve the calculation efficiency of the flow field of thermally sprayed multi-component jets. Summary of the Invention

[0007] To overcome the problems existing in related technologies, this disclosure provides an accelerated calculation method, apparatus, equipment, and medium for thermal spray multi-component jet flow fields, in order to solve the technical problem of judging and correcting the temperature calculation method of the computational domain in related technologies and appropriately improve the calculation efficiency of thermal spray multi-component jet flow fields.

[0008] This specification provides one or more embodiments of an accelerated calculation method for the flow field of a thermally sprayed multi-component jet, comprising the following steps: The global flow field is initialized based on given initial conditions, including incoming flow parameters and jet parameters; The flow field temperature was solved using the Newton-Raphson iteration method over the entire computational domain. A preliminary numerical calculation of the flow field of the thermal spray multi-component jet was performed with 10,000 steps to obtain the preliminary temperature of each grid block in the entire domain. Based on the flow field boundary conditions, grid domains far from the jet and the wall are identified, and temperature criteria are applied to the identified grid domains. Based on the temperature criterion, the temperature of the entire grid domain is updated, and the flow field numerical calculation continues until the flow field converges.

[0009] Preferably, the incoming flow parameters include incoming flow Mach number, incoming flow static pressure, incoming flow static temperature, and incoming flow composition, wherein the incoming flow composition is a mixture of oxygen and nitrogen. The jet parameters include the nozzle exit Mach number, exit static pressure, exit static temperature, and jet composition, wherein the jet composition is a mixture of carbon monoxide, carbon dioxide, nitrogen, and water vapor.

[0010] Preferably, the identification of grid domains far from the jet and wall based on flow field boundary conditions specifically includes the following steps: By using the boundary conditions of the CFD calculation program, mesh blocks whose boundary type does not belong to either the jet inlet / outlet boundary or the wall boundary are selected and defined as mesh domains far away from the jet and the wall.

[0011] Preferably, applying a temperature criterion to the identified grid region specifically includes the following steps: The difference between the initial temperature of the grid domain and the external flow temperature is calculated. If the difference is not greater than 5K, the initial temperature is taken as the fixed temperature value of the grid domain, and the temperature of the corresponding grid domain will not be solved by Newton iteration in subsequent flow field iterations. If the difference is greater than 5K, the initial temperature is used as the initial temperature value for subsequent flow field iterations, while maintaining the Newton iteration solution temperature for the corresponding grid domain.

[0012] Preferably, the criteria for judging the convergence of the flow field are that the change in the flow field parameters is lower than a preset convergence threshold, or that the preset maximum number of iterations is reached.

[0013] This specification provides one or more embodiments of an accelerated calculation device for the flow field of a thermally sprayed multi-component jet, including an initialization module, a preliminary temperature calculation module, a temperature criterion module, and a calculation update module; The initialization module is used to initialize the global flow field according to given initial conditions, including incoming flow parameters and jet parameters. The preliminary temperature calculation module is used to solve the flow field temperature according to the Newton iteration method of the whole computational domain, and to perform 10,000 steps of preliminary numerical calculation of the thermal spray multi-component jet flow field to obtain the preliminary temperature of each grid block in the whole domain. The temperature criterion module is used to identify grid domains far from the jet and the wall based on the flow field boundary conditions, and to apply temperature criteria to the identified grid domains. The calculation update module is used to update the temperature of the entire grid domain in real time based on the results of the temperature criterion, and continue to perform flow field numerical calculations until the flow field converges.

[0014] Preferably, the incoming flow parameters include incoming flow Mach number, incoming flow static pressure, incoming flow static temperature, and incoming flow composition, wherein the incoming flow composition is a mixture of oxygen and nitrogen. The jet parameters include the nozzle exit Mach number, exit static pressure, exit static temperature, and jet composition, wherein the jet composition is a mixture of carbon monoxide, carbon dioxide, nitrogen, and water vapor.

[0015] Preferably, the temperature criterion module is further configured as follows: By using the boundary conditions of the CFD calculation program, mesh blocks whose boundary type does not belong to either the jet inlet / outlet boundary or the wall boundary are selected and defined as mesh domains far away from the jet and the wall.

[0016] This specification provides one or more embodiments of a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the accelerated calculation method for the thermal spray multi-component jet flow field as described above.

[0017] This specification provides one or more embodiments of a computer-readable storage medium storing a computer program that, when executed by a processor, implements the steps of the accelerated calculation method for the thermal spray multi-component jet flow field described above.

[0018] This disclosure provides an accelerated calculation method, apparatus, equipment, and medium for the flow field of a thermally sprayed multi-component jet. Its advantages lie in the following: First, it initializes the entire flow field according to given initial conditions, including inflow and jet parameters, establishing a standardized data framework and defining the initial boundaries and component basis of the flow field. Second, it unifies the initial data benchmark, avoiding subsequent calculation divergence and providing consistent starting data for temperature calculation and grid domain analysis, reducing unnecessary computational losses. Third, it solves the flow field temperature using the Newton-Raphson iteration method across the entire computational domain, performing 10,000 steps of preliminary numerical calculations of the thermally sprayed multi-component jet flow field to obtain the preliminary temperature of each grid block across the entire domain. Leveraging the second-order convergence characteristic of Newton's iteration, it can quickly approximate the true temperature. The 10,000-step calculation establishes a stable temperature trend, while simultaneously providing a basis for subsequent grid domain identification and temperature criteria. Applying the core criteria provides a basis for avoiding initial local deviations and laying the foundation for acceleration. Based on the flow field boundary conditions, grid domains far from the jet and wall are identified. Temperature criteria are applied to the identified grid domains to achieve differentiated division of the computational domain, lock stable regions that do not require high-frequency iteration, reduce the frequency of parameter adjustments, break the indiscriminate iteration mode across the entire domain, focus on the core changing regions, and reduce computational complexity. This is the core optimization step for acceleration. According to the results of the temperature criteria, the temperature of the entire grid domain is updated, which can reduce the amount of iterative computation in stable regions, achieve accurate correction of dynamic regions such as jets and walls, avoid repeated calculations, and continue to perform numerical calculations of the flow field until the flow field converges, ensuring data reliability. By optimizing the region division in the early stage, the iteration cycle is shortened, and finally, both computational efficiency and accuracy are achieved. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in one or more embodiments of this specification or in the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments recorded in this specification. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A flowchart illustrating an accelerated calculation method for a thermally sprayed multi-component jet flow field provided in one or more embodiments of this specification; Figure 2 A flowchart illustrating the accelerated calculation method for the flow field of a multi-component thermal spray provided in one or more embodiments of this specification; Figure 3 A schematic diagram of the computational form and computational mesh of a swirling jet provided for one or more embodiments of this specification; Figure 4 A flow field comparison diagram between the accelerated numerical method provided in one or more embodiments of this specification and the conventional Newton iteration method; Figure 5Comparison chart of pneumatic parameters-computer time provided for one or more embodiments of this specification; Figure 6 A schematic diagram of the structure of an accelerated calculation device for a thermally sprayed multi-component jet flow field provided for one or more embodiments of this specification; Figure 7 This is a schematic diagram of the structure of a computer device provided for one or more embodiments of this specification. Detailed Implementation

[0021] To enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this specification, and not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this invention.

[0022] The present invention will now be described in detail with reference to specific embodiments and accompanying drawings.

[0023] Method Implementation Examples According to embodiments of the present invention, an accelerated calculation method for the flow field of a thermally sprayed multi-component jet is provided, such as... Figure 1 The diagram shown is a flowchart illustrating the accelerated calculation method for the flow field of a multi-component thermal spray provided in this embodiment. The accelerated calculation method for the flow field of a multi-component thermal spray according to this embodiment includes the following steps: S110. The program initialization module initializes the global flow field according to given initial conditions. These initial conditions include incoming flow parameters and jet parameters. The incoming flow parameters include the incoming Mach number, incoming static pressure, incoming static temperature, and incoming flow composition, where the incoming flow composition is a mixture of oxygen and nitrogen. The jet parameters include the nozzle exit Mach number, exit static pressure, exit static temperature, and jet composition, where the jet composition is a mixture of carbon monoxide, carbon dioxide, nitrogen, and water vapor.

[0024] S120. Solve the flow field temperature using the Newton-Raphson iteration method across the entire computational domain. Perform preliminary numerical calculations of the thermal spray multi-component jet flow field over 10,000 steps to obtain the preliminary temperatures of each grid block across the entire domain. T(n) ( n =1,2,…, N , N (Total number of grid blocks), outflow temperature is denoted as T 外流 .

[0025] S130. Identify grid domains far from the jet and wall based on flow field boundary conditions, and apply temperature criteria to the identified grid domains.

[0026] S140. Based on the temperature criterion, update the temperature of the entire grid domain and continue to perform flow field numerical calculations until the flow field converges. The criteria for judging flow field convergence are that the change in flow field parameters is lower than the preset convergence threshold or the preset maximum number of iterations is reached.

[0027] Specifically, the global flow field is judged according to grid block numbers from 1 to N, and the judgment conditions are as follows: ① The grid blocks do not contain wall or jet boundary conditions; ② .

[0028] If both conditions ① and ② are met, then T(n) As the temperature value output for this type of grid block, the temperature solution step for this type of grid block is skipped in subsequent numerical flow field calculations.

[0029] If conditions ① and ② are not simultaneously met, the Newton-Raphson iteration method for solving the temperature for this type of mesh block remains unchanged, and the iteration formula is as follows: , T(n) Using this as the initial value for iteration, the iteration ends when the convergence criterion is satisfied, and the temperature value after iteration is output and denoted as [value]. T(n') This is output as the temperature value of this type of grid block.

[0030] Replace the temperatures of the two types of mesh blocks obtained above with the temperatures at 10,000 steps, update the global temperature of the flow field, and continue running the program to complete the numerical calculations at the current time step.

[0031] like Figure 2 The diagram shows the flowchart of the accelerated calculation method for the multi-component thermal jet flow field provided in this embodiment. The method balances calculation accuracy and efficiency through a "boundary characteristic judgment + temperature difference grading strategy": The process begins with flow field initialization and preliminary temperature field acquisition. First, it determines whether the grid block contains walls or jet boundaries (the flow / thermal characteristics of these regions are more complex). If it does not contain such boundaries, it proceeds directly to subsequent calculations. If it does, it further compares the temperature difference between the grid block and the external flow. If the difference is >5K (strong nonlinear scenarios, such as the interaction between a high-temperature jet and a low-temperature environment), a global Newton iteration is used for fine-grained solution. If it is ≤5K (weak nonlinear scenarios, such as the boundary layer stabilization stage), the calculation is simplified by solving in separate regions. After obtaining the temperature using both methods, the flow field is updated, and finally, subsequent numerical simulations (such as momentum and continuity equation solving) are performed.

[0032] The method provided in this embodiment initializes the entire flow field according to given initial conditions, including inflow and jet parameters, establishing a standardized data framework and defining the initial boundaries and component basis of the flow field. It unifies the initial data benchmark, avoiding subsequent calculation divergence and providing consistent starting data for temperature calculation and grid domain analysis, reducing unnecessary computational losses. The flow field temperature is solved using the Newton-Raphson iteration method across the entire computational domain, performing 10,000 steps of preliminary numerical calculations of the thermal jet multi-component flow field to obtain the preliminary temperature of each grid block across the entire domain. Leveraging the second-order convergence characteristic of Newton's iteration, the true temperature can be quickly approximated. The 10,000-step calculation establishes a stable temperature trend, providing a core basis for subsequent grid domain identification and temperature criterion application, avoiding initial localization. This approach addresses biases and lays the foundation for acceleration. Based on flow field boundary conditions, grid domains far from the jet and wall are identified. Temperature criteria are applied to these identified grid domains to achieve differentiated computational domain partitioning, locking stable regions that do not require high-frequency iterations, reducing parameter adjustment frequency, breaking the indiscriminate iteration pattern across the entire domain, focusing on core changing regions, reducing computational complexity, and accelerating core optimization. Temperature updates are performed on the entire grid domain based on the temperature criteria results, reducing iterative computation in stable regions, enabling precise correction of dynamic regions such as the jet and wall, avoiding redundant calculations, and continuing flow field numerical calculations until convergence, ensuring data reliability. The optimization of the initial region partitioning shortens the iteration cycle, ultimately achieving both computational efficiency and accuracy targets.

[0033] In one embodiment, identifying mesh domains far from the jet and wall based on flow field boundary conditions specifically includes the following steps: By using the boundary conditions of the CFD calculation program, mesh blocks whose boundary type does not belong to either the jet inlet / outlet boundary or the wall boundary are selected and defined as mesh domains far away from the jet and the wall.

[0034] The method provided in this embodiment filters and excludes grid blocks at the jet inlet / outlet and wall boundaries and defines the target domain through CFD program boundary conditions. The technical effects are as follows: relying on standardized program judgment, it avoids human error and accurately locates stable grid areas without jet interaction and wall heat exchange; it identifies areas that do not require high-frequency calculations, providing a basis for simplifying iterations and saving resources, and directly supporting the acceleration of flow field calculations; based on a unified CFD data benchmark, it ensures the data consistency of subsequent temperature updates and convergence calculations, avoiding deviations.

[0035] In one embodiment, applying a temperature criterion to the identified grid region specifically includes the following steps: The difference between the initial temperature of the grid domain and the external flow temperature is calculated. If the difference is not greater than 5K, the initial temperature is taken as the fixed temperature value of the grid domain, and the temperature of the corresponding grid domain will not be solved by Newton iteration in subsequent flow field iterations.

[0036] If the difference is greater than 5K, the initial temperature will be used as the initial temperature value for subsequent flow field iterations, while maintaining the Newton iteration solution temperature for the corresponding grid domain.

[0037] The method provided in this embodiment accurately divides the temperature stable and dynamic mesh domains. The stable domain with a difference of ≤5K has a fixed temperature, eliminating the need for Newton iterations and directly reducing unnecessary computations. The dynamic domain with a difference of >5K uses the initial temperature as the initial value for iteration, avoiding the inefficiency of solving from scratch and accelerating iteration convergence. Overall, while reducing computational resource consumption, it ensures the accuracy of temperature solution in the dynamic region, achieving a balance between efficiency and accuracy.

[0038] The following specific implementation case further illustrates the solution: This invention conducts numerical acceleration calculations and tests on the flow field disturbed by a jet with a swirling body shape, such as... Figure 3 The diagram shown illustrates the computational model and mesh of the swirling jet calculation method provided in this embodiment. The incoming Mach number is 5, the incoming static pressure is 5529.31 Pa, the incoming static temperature is 216.65 K, and the incoming gas composition is a mixture of oxygen and nitrogen. The nozzle exit Mach number is 3.3, the exit static pressure is 149101 Pa, the exit static temperature is 1050 K, and the jet composition is a mixture of carbon monoxide, carbon dioxide, nitrogen, and water vapor. Figure 4 The diagram shows a comparison of the flow field between the accelerated numerical method provided in this embodiment and the conventional Newton-Raphson iteration method. The two methods are essentially identical, verifying the computational accuracy of this invention. Figure 5 As shown, this is a comparison of aerodynamic parameters and computation time provided in this embodiment. It shows the pitch moment-computation time curves of the two methods. The accelerated numerical method can reach 40,000 steps of convergence in about 55,300 s, while the traditional global Newton iteration method requires about 67,000 s to reach 40,000 steps of convergence. The overall computational efficiency is improved by about 17.5%. Compared with the traditional global Newton iteration method for solving temperature, the method of solving temperature by partitioning the computational domain can make the flow field of the thermal jet multi-component jet converge more quickly, which verifies the effectiveness of the present invention for accelerating the numerical calculation of the flow field of the thermal jet multi-component jet. Device Examples According to embodiments of the present invention, an accelerated calculation device for the flow field of a thermally sprayed multi-component jet is provided, such as... Figure 6 The diagram shown is a structural schematic of the accelerated calculation device for the thermal spray multi-component jet flow field provided in this embodiment. The accelerated calculation device for the thermal spray multi-component jet flow field according to this embodiment includes an initialization module 61, a preliminary temperature calculation module 62, a temperature criterion module 63, and a calculation update module 64.

[0040] Initialization module 61 is used to initialize the global flow field according to given initial conditions. The initial conditions include incoming flow parameters and jet parameters. The incoming flow parameters include incoming flow Mach number, incoming flow static pressure, incoming flow static temperature, and incoming flow composition. The incoming flow composition is a mixture of oxygen and nitrogen. The jet parameters include nozzle exit Mach number, exit static pressure, exit static temperature, and jet composition. The jet composition is a mixture of carbon monoxide, carbon dioxide, nitrogen, and water vapor.

[0041] The preliminary temperature calculation module 62 is used to solve the flow field temperature according to the Newton iteration method of the whole computational domain, and to perform 10,000 steps of preliminary numerical calculation of the thermal spray multi-component jet flow field to obtain the preliminary temperature of each grid block in the whole domain.

[0042] Temperature criterion module 63 is used to identify grid domains far from the jet and wall based on flow field boundary conditions, and apply temperature criteria to the identified grid domains.

[0043] The calculation update module 64 is used to update the temperature of the entire grid domain in real time based on the results of the temperature criterion, and continue to perform numerical calculations of the flow field until the flow field converges.

[0044] The apparatus provided in this embodiment includes an initialization module 61 that initializes the entire flow field according to given initial conditions, including inflow parameters and jet parameters. This establishes a standardized data framework, defining the initial boundaries and component basis of the flow field. It unifies the initial data benchmark, preventing subsequent calculation divergence and providing consistent starting data for temperature calculation and grid domain analysis, reducing unnecessary computational losses. The preliminary temperature calculation module 62 solves for the flow field temperature using the Newton-Raphson iteration method across the entire computational domain, performing 10,000 steps of preliminary numerical calculations of the thermal jet multi-component jet flow field. This yields the preliminary temperature of each grid block across the entire domain. Leveraging the second-order convergence characteristic of Newton-Raphson iteration, the actual temperature can be quickly approximated. The 10,000-step calculation establishes a stable temperature trend and provides a core basis for subsequent grid domain identification and temperature criterion application, avoiding initial localization. The temperature criterion module 63 identifies grid domains far from the jet and wall based on the flow field boundary conditions, applies temperature criteria to the identified grid domains, realizes differentiated division of the computational region, locks stable regions that do not require high-frequency iteration, reduces the frequency of parameter adjustment, breaks the whole-domain indiscriminate iteration mode, focuses on the core changing region, reduces computational complexity, and is the core optimization link for acceleration; the calculation update module 64 updates the temperature of the whole-domain grid domain according to the results of the temperature criterion, which can reduce the amount of iterative calculation in stable regions, realize accurate correction of dynamic regions such as jet and wall, avoid repeated calculations, continue to perform flow field numerical calculations until the flow field converges, ensure data reliability, shorten the iteration cycle with the help of the previous region division optimization, and finally achieve both computational efficiency and accuracy.

[0045] In one embodiment, the temperature criterion module 63 is further configured as follows: By using the boundary conditions of the CFD calculation program, mesh blocks whose boundary type does not belong to either the jet inlet / outlet boundary or the wall boundary are selected and defined as mesh domains far away from the jet and the wall.

[0046] The device provided in this embodiment filters and excludes grid blocks at the jet inlet / outlet and wall boundaries and defines the target domain through CFD program boundary conditions. The technical effects are as follows: relying on standardized program judgment, it avoids human error and accurately locks stable grid areas without jet interaction and wall heat exchange; it clarifies areas that do not require high-frequency calculations, providing a basis for simplifying iterations and saving resources, and directly supporting the acceleration of flow field calculations; based on the unified CFD data benchmark, it ensures the data consistency of subsequent temperature updates and convergence calculations, avoiding deviations.

[0047] The embodiments of the present invention are device embodiments corresponding to the above method embodiments. The specific operations of each module processing step can be understood with reference to the description of the method embodiments, and will not be repeated here.

[0048] like Figure 7 As shown, the present invention also provides a computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, it implements the accelerated calculation method for the thermal spray multi-component jet flow field in the above embodiments, or when the computer program is executed by a processor, it implements the accelerated calculation method for the thermal spray multi-component jet flow field in the above embodiments.

[0049] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0050] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, for apparatus or system embodiments, since they are basically similar to method embodiments, the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments. The apparatus and system embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without creative effort.

[0051] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and the contents not described in detail in the specification of the present invention are known to those skilled in the art.

Claims

1. A method for calculating the acceleration of a multi-component thermal jet flow field, characterized in that, Includes the following steps: The global flow field is initialized based on given initial conditions, including incoming flow parameters and jet parameters; The flow field temperature was solved using the Newton-Raphson iteration method over the entire computational domain. A preliminary numerical calculation of the flow field of the thermal spray multi-component jet was performed with 10,000 steps to obtain the preliminary temperature of each grid block in the entire domain. Based on the flow field boundary conditions, grid domains far from the jet and the wall are identified, and temperature criteria are applied to the identified grid domains. Based on the temperature criterion, the temperature of the entire grid domain is updated, and the flow field numerical calculation continues until the flow field converges.

2. The acceleration calculation method for the flow field of a multi-component thermal spray as described in claim 1, characterized in that, The incoming flow parameters include the incoming flow Mach number, incoming flow static pressure, incoming flow static temperature, and incoming flow composition. The jet parameters include the nozzle exit Mach number, exit static pressure, exit static temperature, and jet composition.

3. The method for accelerating the calculation of the flow field of a multi-component thermal jet as described in claim 1, characterized in that, The identification of grid domains far from the jet and wall based on flow field boundary conditions specifically includes the following steps: By using the boundary conditions of the CFD calculation program, mesh blocks whose boundary type does not belong to either the jet inlet / outlet boundary or the wall boundary are selected and defined as mesh domains far away from the jet and the wall.

4. The method for accelerating the calculation of the flow field of a multi-component thermal jet as described in claim 1, characterized in that, Applying a temperature criterion to the identified grid region specifically includes the following steps: The difference between the initial temperature of the grid domain and the external flow temperature is calculated. If the difference is not greater than 5K, the initial temperature is taken as the fixed temperature value of the grid domain, and the temperature of the corresponding grid domain will not be solved by Newton iteration in subsequent flow field iterations. If the difference is greater than 5K, the initial temperature is used as the initial temperature value for subsequent flow field iterations, while maintaining the Newton iteration solution temperature for the corresponding grid domain.

5. The method for accelerating the calculation of the flow field of a multi-component thermal jet as described in claim 1, characterized in that, The criteria for judging the convergence of the flow field are that the change in the flow field parameters is lower than the preset convergence threshold, or the preset maximum number of iterations is reached.

6. An acceleration calculation device for the flow field of a thermally sprayed multi-component jet, characterized in that, It includes an initialization module, a preliminary temperature calculation module, a temperature criterion module, and a calculation and update module; The initialization module is used to initialize the global flow field according to given initial conditions, including incoming flow parameters and jet parameters. The preliminary temperature calculation module is used to solve the flow field temperature according to the Newton iteration method of the whole computational domain, and to perform 10,000 steps of preliminary numerical calculation of the thermal spray multi-component jet flow field to obtain the preliminary temperature of each grid block in the whole domain. The temperature criterion module is used to identify grid domains far from the jet and the wall based on the flow field boundary conditions, and to apply temperature criteria to the identified grid domains. The calculation update module is used to update the temperature of the entire grid domain in real time based on the results of the temperature criterion, and continue to perform flow field numerical calculations until the flow field converges.

7. The accelerated calculation device for the thermal spray multi-component jet flow field as described in claim 6, characterized in that, The incoming flow parameters include incoming flow Mach number, incoming flow static pressure, incoming flow static temperature, and incoming flow composition, wherein the incoming flow composition is a mixture of oxygen and nitrogen. The jet parameters include the nozzle exit Mach number, exit static pressure, exit static temperature, and jet composition, wherein the jet composition is a mixture of carbon monoxide, carbon dioxide, nitrogen, and water vapor.

8. The accelerated calculation device for the thermal spray multi-component jet flow field as described in claim 6, characterized in that, The temperature criterion module is further configured as follows: By using the boundary conditions of the CFD calculation program, mesh blocks whose boundary type does not belong to either the jet inlet / outlet boundary or the wall boundary are selected and defined as mesh domains far away from the jet and the wall.

9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the accelerated calculation method for the thermal spray multi-component jet flow field as described in any one of claims 1 to 5.

10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the steps of the accelerated calculation method for the thermal spray multi-component jet flow field as described in any one of claims 1 to 5.

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