Method and system for identifying thermal-chemical non-equilibrium subzone of scramjet engine

Abstract

The application provides a scramjet thermal-chemical non-equilibrium partition identification method and system, and relates to the technical field of engine thermal-chemical non-equilibrium partition. The method comprises the following steps: obtaining flow field flow and component information through numerical simulation; based on the flow field flow and component information, calculating local flow characteristic time, chemical reaction characteristic time and vibration modal relaxation time in the scramjet; calculating thermal Damkohler number based on the local flow characteristic time and the vibration modal relaxation time, and calculating chemical Damkohler number based on the local flow characteristic time and the chemical reaction characteristic time; based on the calculated thermal Damkohler number and the chemical Damkohler number, realizing the identification and partition of the scramjet thermal-chemical non-equilibrium. The application establishes a calculation method of the local flow characteristic time and the chemical reaction time suitable for various orders of chemical reactions and various reaction components, and further realizes the partition identification of the high-Mach-number scramjet thermal-chemical non-equilibrium.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of engine thermo-chemical non-equilibrium partition, and particularly relates to a method and system for identifying thermo-chemical non-equilibrium partition of a scramjet engine. BACKGROUND

[0002] A scramjet engine is a key core power for realizing air-breathing hypersonic flight. A high-Mach-number scramjet engine is generally considered to be a scramjet engine under the condition that the flight Mach number is greater than 8. The scramjet engine adapted to high-Mach-number flight (Ma≥8) has a significant thermo-chemical non-equilibrium effect inside, which has a significant influence on jet combustion and engine performance. In the existing research on the influence of non-equilibrium effect on the scramjet engine, the local wave structure, ignition delay, flame propagation and heating / cooling effect inside the engine are usually targeted. However, the geometrical forms and flow characteristics of the engine forebody, inlet, isolation section, combustion chamber and tail nozzle are different, and each plays a function, and finally must be connected into an organic whole to realize effective propulsion. At present, there is still a lack of detailed characterization of the thermo-chemical non-equilibrium effect partition of the high-Mach-number scramjet engine on the basis of multi-time-scale analysis.

[0003] The identification of thermo-chemical non-equilibrium requires the calculation of flow characteristic time, vibration mode relaxation time and chemical reaction characteristic time. The inventors have found that:

[0004] (1) The flow characteristic time is defined as the ratio of the characteristic length (L) and the characteristic velocity (U), that is, L / U. In the past, the calculation of L / U mainly takes the full engine size as the characteristic length, and U takes the incoming flow velocity or the axis velocity in the flow field, but this calculation method has a full engine observation scale, which is not conducive to the analysis of the local thermo-chemical non-equilibrium mechanism in the scramjet engine.

[0005] (2) Generally, the calculation of the chemical reaction characteristic time needs to select different methods according to the reaction order and reaction components, which is not universal. SUMMARY

[0006] To overcome the shortcomings of the prior art, the present application provides a method and system for identifying thermo-chemical non-equilibrium partition of a scramjet engine, which is suitable for chemical reactions of all orders in the combustion mechanism and various reaction components in the flow field, and has universality. The calculation method of the defined flow characteristic time has a local perspective, and can effectively identify the thermo-chemical non-equilibrium characteristics of the scramjet engine.

[0007] To achieve the above-mentioned purpose, one or more embodiments of the present application provide the following technical solutions:

[0008] The present application provides a method for identifying thermo-chemical non-equilibrium partition of a scramjet engine in the first aspect.

[0009] A method for identifying thermochemical non-equilibrium partitions of a scramjet engine comprises the following steps:

[0010] Numerical simulation of hydrogen injection ignition and combustion in the scramjet engine flow passage considering thermochemical non-equilibrium flow was performed to obtain flow field and composition information;

[0011] Based on the flow field and component information, the local flow characteristic time, chemical reaction characteristic time and vibration mode relaxation time inside the scramjet engine are calculated;

[0012] The thermal Damköhler number is calculated based on the local flow characteristic time and the vibration mode relaxation time, and the chemical Damköhler number is calculated based on the local flow characteristic time and the chemical reaction characteristic time;

[0013] Based on the calculated thermal Damköhler number and chemical Damköhler number, the thermodynamic non-equilibrium characteristics and chemical non-equilibrium characteristics of the flow field inside the scramjet engine are characterized respectively, realizing the identification and zoning of the thermochemical non-equilibrium of the scramjet engine.

[0014] A second aspect of the present invention provides a scramjet engine thermochemical non-equilibrium partition identification system.

[0015] Thermochemical non-equilibrium partition identification system for scramjet engines includes:

[0016] The numerical simulation module is configured to: perform numerical simulation of hydrogen injection ignition and combustion in the flow channel of the scramjet engine considering thermochemical non-equilibrium flow, and obtain flow field flow and composition information;

[0017] a characteristic time calculation module configured to calculate the local flow characteristic time, chemical reaction characteristic time, and vibration mode relaxation time inside the scramjet engine based on flow field flow and component information;

[0018] The Damköhler number characterization module is configured to: calculate the thermal Damköhler number based on the local flow characteristic time and the vibration mode relaxation time, and calculate the chemical Damköhler number based on the local flow characteristic time and the chemical reaction characteristic time;

[0019] The identification and partitioning module is configured to characterize the thermodynamic non-equilibrium characteristics and chemical non-equilibrium characteristics of the flow field inside the scramjet engine based on the calculated thermal Damköhler number and chemical Damköhler number, respectively, to achieve the identification and partitioning of the thermochemical non-equilibrium of the scramjet engine.

[0020] A third aspect of the present invention provides a computer-readable storage medium having a program stored thereon, which, when executed by a processor, implements the steps of the method for identifying thermochemical non-equilibrium partitions of a scramjet engine as described in the first aspect of the present invention.

[0021] A fourth aspect of the present invention provides an electronic device comprising a memory, a processor, and a program stored in the memory and executable on the processor. When the processor executes the program, the steps of the method for identifying thermochemical non-equilibrium partitions of a scramjet engine as described in the first aspect of the present invention are implemented.

[0022] One or more of the above technical solutions have the following beneficial effects:

[0023] The present invention provides a method and system for identifying thermochemical nonequilibrium zoning within a scramjet engine. The defined flow characteristic time provides a local perspective, facilitating analysis of the localized thermochemical nonequilibrium characteristics of the entire scramjet engine. Furthermore, the chemical reaction characteristic time defined in the present invention is derived based on component continuity equations and is applicable to all-order chemical reactions and various reaction components. Based on the present definition, the complete thermochemical nonequilibrium zoning characteristics of the scramjet engine flow path can be identified based on multi-timescale analysis. This is of great significance for understanding the inherent characteristics of flow and combustion, overall engine performance, and fostering new design principles and concepts.

[0024] The present invention defines thermal Dam'Köhler numbers and chemical Dam'Köhler numbers, calculates the thermal Dam'Köhler number based on the local flow characteristic time and the vibration modal relaxation time, and calculates the chemical Dam'Köhler number based on the local flow characteristic time and the chemical reaction characteristic time, and characterizes the thermodynamic non-equilibrium characteristics and chemical non-equilibrium characteristics of the flow field inside the scramjet engine respectively, which can realize the identification and zoning of the thermochemical non-equilibrium of the scramjet engine very intuitively and conveniently.

[0025] Advantages of additional aspects of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The accompanying drawings, which constitute a part of the present invention, are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0027] Figure 1 This is an overall flow chart of Example 1 of the present invention.

[0028] Figure 2 Schematic diagram for calculating the local flow residence time in a scramjet engine.

[0029] Figure 3 This is the thermal non-equilibrium partition diagram of the flow channel in the scramjet engine targeted by the present invention.

[0030] Figure 4 This is the chemical non-equilibrium partition diagram of the flow channel in the scramjet engine targeted by the present invention. DETAILED DESCRIPTION

[0031] It should be noted that the following detailed descriptions are exemplary and intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which the present invention belongs.

[0032] It should be noted that the terms used herein are for describing particular embodiments only and are not intended to limit the exemplary embodiments according to the present invention.

[0033] In the absence of conflict, the embodiments of the present invention and the features thereof may be combined with each other.

[0034] Overall concept:

[0035] In response to the technical issues mentioned in the background art, previous studies on the calculation of flow characteristic time (L / U) primarily used the full engine dimensions as the characteristic length, with U representing the incoming flow velocity or the flow field's central axis velocity. This calculation method, focusing on the full engine, is not conducive to analyzing the local thermochemical nonequilibrium mechanisms within scramjet engines. Furthermore, the calculation of chemical reaction characteristic time typically requires different methods based on the reaction order and reaction components, making it not universally applicable. Therefore, it is necessary to develop a method for calculating local flow characteristic time and chemical reaction time applicable to chemical reactions of all orders and reaction components, thereby enabling the regional identification of thermochemical nonequilibrium within high-Mach number scramjet engines.

[0036] Based on this, the present invention proposes a method and system for identifying thermochemical non-equilibrium zones in scramjet engines, which can be applied to identify thermochemical non-equilibrium zones in high Mach number scramjet engines. The identification method includes the following steps:

[0037] Numerical simulation of the flow path of a target high Mach number scramjet engine considering thermochemical non-equilibrium was performed to obtain flow field and composition information;

[0038] Calculate local flow characteristic time, chemical reaction time and vibration mode relaxation time using flow and composition information;

[0039] The obtained characteristic time is used to calculate the Damköhler number, the thermal Damköhler number is used to judge the thermodynamic non-equilibrium, and the chemical Damköhler number is used to judge the chemical non-equilibrium, thereby realizing the identification and zoning of the thermochemical non-equilibrium of the scramjet engine.

[0040] The present invention is applicable to chemical reactions of all orders in the combustion mechanism and various reaction components in the flow field. The calculation method of the defined flow characteristic time has a local perspective and can identify the thermochemical non-equilibrium characteristics of the entire scramjet engine.

[0041] Example 1

[0042] This embodiment discloses a method for identifying thermochemical non-equilibrium partitions of a scramjet engine.

[0043] like Figure 1 As shown, the scramjet engine thermochemical non-equilibrium partition identification method includes the following steps:

[0044] Numerical simulation of hydrogen injection ignition and combustion in the scramjet engine flow path considering thermochemical non-equilibrium was performed to obtain flow field and composition information;

[0045] Based on the flow field and component information, the local flow characteristic time, chemical reaction characteristic time and vibration mode relaxation time inside the scramjet engine are calculated;

[0046] The thermal Damköhler number is calculated based on the local flow characteristic time and the vibration mode relaxation time, and the chemical Damköhler number is calculated based on the local flow characteristic time and the chemical reaction characteristic time;

[0047] Based on the calculated thermal Damköhler number and chemical Damköhler number, the thermodynamic non-equilibrium characteristics and chemical non-equilibrium characteristics of the flow field inside the scramjet engine are characterized respectively, realizing the identification and zoning of the thermochemical non-equilibrium of the scramjet engine.

[0048] As a more specific technical solution, the scramjet engine thermochemical non-equilibrium partition identification method mentioned in this embodiment may include:

[0049] Step 1: Numerical simulation of hydrogen injection ignition and combustion in the target high Mach number scramjet engine flow path, taking into account thermochemical non-equilibrium, to obtain flow field and composition information;

[0050] Step 2: Based on the flow field and component information obtained in step 1, calculate the local flow characteristic time τ inside the scramjet engine f , chemical reaction characteristic time τ che and vibration modal relaxation time τ V ;

[0051] Step 3: Based on the characteristic time in step 2, use the Damköhler number Determine the thermochemical non-equilibrium characteristics in the flow field. Use the thermal Damm-Kohler number Da v Characterizing thermodynamic nonequilibrium, chemical Damköhler number Da che characterize chemical nonequilibrium;

[0052] Step 4: Determine the thermodynamic non-equilibrium characteristics of the flow field inside the scramjet engine based on the thermal Damköhler number calculated in step 3:

[0053] When the thermal Damm-Kohler number approaches 0, the flow is in a thermodynamic frozen state; when the thermal Damm-Kohler number approaches 1, the flow is in a thermodynamic non-equilibrium state; when the thermal Damm-Kohler number approaches positive infinity, the flow is in a thermodynamic equilibrium state.

[0054] The chemical non-equilibrium characteristics of the flow field in the scramjet engine are determined based on the chemical Damköhler number calculated in step 3:

[0055] When the chemical Damköhler number approaches 0, the flow is in a chemically frozen state; when the chemical Damköhler number approaches 1, the flow is in a chemically non-equilibrium state; when the chemical Damköhler number approaches positive infinity, the flow is in a chemically equilibrium state.

[0056] Furthermore, the local flow characteristic time τ in step 2 f , chemical reaction characteristic time τ che and vibration modal relaxation time τ V The specific definitions are as follows:

[0057] Definition of local flow characteristic time:

[0058]

[0059] Where Δx and Δy represent the grid lengths in the x-direction and y-direction respectively, and u i and v i Represent the local speed in the x and y directions respectively, such as Figure 2 This definition is a grid-based method for calculating the local flow characteristic time, which can be used to calculate the local flow characteristic time in the flow channel of a scramjet engine.

[0060] This grid-based calculation method requires the entire engine to be gridded. This embodiment takes the two dimensions of a two-dimensional grid, x and y, as an example. Δx and Δy are the grid lengths in the two dimensions x and y spanned by each grid node i, and u i and v i is the speed of grid node i in the x and y directions. Divide the length of the grid Δx spanned by grid node i in the x direction by the local speed u i , get the flow characteristic time in the x direction; divide the grid length Δy spanned by the grid node i in the y direction by the local velocity v i , and the characteristic flow time in the y direction is obtained. Finally, the characteristic flow time τ at the grid node i is f Take the minimum of the x and y flow characteristic times.

[0061] The characteristic time of chemical reactions can be expressed by reaction or by component, with the following definitions:

[0062]

[0063] Where, τ che(reaction) is the chemical reaction time defined by the chemical reaction rate, ρ and M represent the density and molar mass of the mixture respectively, and Rr is the chemical reaction rate. che(species) is the chemical reaction time defined by the components, ρ s is the density of component s, ω s is the chemical reaction source term of component s.

[0064] These two methods of calculating the characteristic time of chemical reactions are derived based on the continuity equation and are applicable to all-order chemical reactions and various reaction components, and are universal.

[0065] Vibration modal relaxation time τ m-s,V-T Calculated by the Millikan-White relationship (Millikan RC, White DR. Systematics of vibrational relaxation[J]. The Journal of chemical physics, 1963, 39(12): 3209-3213. https: / / doi.org / 10.1063 / 1.1734182):

[0066]

[0067]

[0068] Where p is pressure (Pa), T tr is the translational-rotational temperature, μ ms is the reduced molecular mass, θ vs is the vibration characteristic temperature, τ V is the vibration mode relaxation time of component s, X s is the mole fraction of component s.

[0069] Furthermore, in step 3, the thermal Dam-Köhler number Da v and chemical Damköhler number Da che The specific definitions are as follows:

[0070]

[0071] Where, τ f is the flow characteristic time, τ che is the characteristic time of chemical reaction, τ V is the vibration mode relaxation time. che Including τ che(reaction) and τ che(species)Different calculation methods can be selected according to the problem of interest. The thermal Damköhler number and chemical Damköhler number are used to identify the thermochemical non-equilibrium characteristics of the engine flow path.

[0072] Next, this embodiment describes the technical solution by taking a two-dimensional Hyshot II scramjet engine using hydrogen as fuel as the target scramjet engine.

[0073] Step 1: Simulate the flow path of the target scramjet engine to obtain the translational-rotational temperature T under non-equilibrium conditions tr , pressure P, density of the mixture ρ, density of component s in the flow field ρ s and the chemical reaction source term ω of component s s This simulation uses a detailed reaction mechanism of hydrogen-air combustion, not a general reaction.

[0074] Step 2: Use the method in the technical solution to calculate the local flow characteristic time, chemical reaction characteristic time and translation-vibration relaxation time in the target engine, and calculate the flow characteristic time under five perspectives, namely 4 local perspectives and 1 global perspective. The smallest observation scale among the four local perspectives is Figure 2 Each grid node i is shown as spanning 2 grid lengths (2 grids), i.e., Δx = 2 grid lengths and Δy = 2 grid lengths. The minimum of the calculated flow characteristic times in the x and y directions is then taken as the flow characteristic time at grid node i. Similarly, the calculation method for three perspectives—Δx and Δy equal to 4 grid lengths (4 grids), Δx and Δy equal to 10 grid lengths (10 grids), and Δx and Δy equal to 20 grid lengths (20 grids)—is the same as for the 2-grid perspective. The flow characteristic time is also calculated from a global perspective, using the full engine scale as the characteristic length.

[0075] The global flow characteristic time τ calculated from the full engine size perspective is f(length) This is for comparison with the calculation results of the local perspective defined in the present invention, and its specific definition is as follows:

[0076]

[0077] Where L is the total engine size, u ∞ is the incoming flow velocity.

[0078] Step 3: Use the characteristic time obtained in step 2 to calculate the thermal Damköhler number and chemical Damköhler number of the flow path in the engine, and then identify the thermochemical non-equilibrium partitions in the entire engine.

[0079] Step 4: Take the logarithm of the Damköhler number and display it as a cloud chart.

[0080] The thermal non-equilibrium partition in the target engine is shown as Figure 3 The inflow component oxygen (O2), the jet component hydrogen (H2) and the product water (H2O) are taken as examples for demonstration.

[0081] The chemical non-equilibrium partition is shown as Figure 4 The positive reaction of H+O2=O+OH, O2 and H2 are taken as examples for demonstration.

[0082] The cloud chart in the figure shows that the calculation result under the full scale has no local characteristics and ignores the local non-equilibrium region in the engine, which is not conducive to the analysis of the local non-equilibrium mechanism. The calculation method of the local flow characteristic time and the calculation method of the chemical reaction characteristic time suitable for various reaction components of each order of chemical reaction are combined with the Millikan-White translational-vibrational relaxation time, and finally the thermal chemical non-equilibrium of the high Mach number scramjet engine is partitioned and recognized.

[0083] Embodiment two

[0084] The embodiment discloses a thermal chemical non-equilibrium partition recognition system of a scramjet engine.

[0085] The thermal chemical non-equilibrium partition recognition system of the scramjet engine comprises:

[0086] The numerical simulation module is configured to perform numerical simulation of hydrogen injection ignition and combustion considering thermal chemical non-equilibrium in the flow channel of the scramjet engine to obtain flow field flow and component information;

[0087] The characteristic time calculation module is configured to calculate the local flow characteristic time, the chemical reaction characteristic time and the vibration mode relaxation time inside the scramjet engine based on the flow field flow and component information;

[0088] The Damkohler number representation module is configured to calculate the thermal Damkohler number based on the local flow characteristic time and the vibration mode relaxation time, and calculate the chemical Damkohler number based on the local flow characteristic time and the chemical reaction characteristic time;

[0089] The recognition partition module is configured to represent the thermodynamic non-equilibrium characteristics and the chemical non-equilibrium characteristics of the flow field in the scramjet engine based on the calculated thermal Damkohler number and chemical Damkohler number, respectively, to realize the recognition and partition of the thermal chemical non-equilibrium of the scramjet engine.

[0090] Embodiment three

[0091] The purpose of the embodiment is to provide a computer readable storage medium.

[0092] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the method for identifying thermochemical non-equilibrium partitions of a scramjet engine as described in Example 1 of the present disclosure.

[0093] Example 4

[0094] The purpose of this embodiment is to provide an electronic device.

[0095] An electronic device includes a memory, a processor, and a program stored in the memory and executable on the processor, wherein when the processor executes the program, the steps of the method for identifying thermochemical non-equilibrium partitions of a scramjet engine as described in Example 1 of the present disclosure are implemented.

[0096] The steps involved in the apparatuses of Examples 2, 3, and 4 above correspond to those of Method Example 1. For detailed implementations, please refer to the relevant description of Example 1. The term "computer-readable storage medium" should be understood to mean a single medium or multiple media containing one or more instruction sets; it should also be understood to include any medium capable of storing, encoding, or carrying an instruction set for execution by a processor and causing the processor to perform any method of the present invention.

[0097] Those skilled in the art will appreciate that the modules or steps of the present invention described above can be implemented using a general-purpose computer device. Alternatively, they can be implemented using program code executable by a computing device, which can then be stored in a storage device and executed by the computing device. Alternatively, they can be fabricated into separate integrated circuit modules, or multiple modules or steps can be fabricated into a single integrated circuit module for implementation. The present invention is not limited to any specific combination of hardware and software.

[0098] Although the above describes the specific embodiments of the present invention in conjunction with the accompanying drawings, it is not intended to limit the scope of protection of the present invention. Those skilled in the art should understand that various modifications or variations that can be made by those skilled in the art on the basis of the technical solution of the present invention without any creative work are still within the scope of protection of the present invention.

Claims

1. A method for identifying thermochemical non-equilibrium partitions in a scramjet engine, characterized in that: The following steps are involved: Numerical simulation of hydrogen injection ignition and combustion in the scramjet engine flow path considering thermochemical non-equilibrium was performed to obtain flow field and composition information; Based on the flow field and component information, the local flow characteristic time, chemical reaction characteristic time and vibration mode relaxation time inside the scramjet engine are calculated; The local flow characteristic time τ f The calculation method is: Where, Δ x and Δ y Respectively x Direction and y The grid length in the direction, u i and v i Respectively x and y local speed in the direction; The characteristic time of chemical reactions can be expressed by reaction or by component, specifically: Where, τ che(reaction) is the chemical reaction time defined by the chemical reaction rate, ρ and M represent the density and molar mass of the mixture, Rr is the chemical reaction rate; τ che(species) is the chemical reaction time defined by the components, ρ s For components s The density, ω s For components s Chemical reaction source term; Based on the Millikan-White relationship, combined with the pressure obtained by numerical simulation P and translational-rotational temperature T tr , calculate the vibration mode relaxation time τ V ; The thermal Damköhler number is calculated based on the local flow characteristic time and the vibration mode relaxation time, and the chemical Damköhler number is calculated based on the local flow characteristic time and the chemical reaction characteristic time; The thermal Damköhler number and the chemical Damköhler number are specifically defined as follows: In the formula, Da v is the thermal Damköhler number, Da che is the chemical Damköhler number, τ f is the local flow characteristic time, τ V is the vibration mode relaxation time, τ che is the characteristic time of chemical reaction; Based on the calculated thermal Damköhler number and chemical Damköhler number, the thermodynamic non-equilibrium characteristics and chemical non-equilibrium characteristics of the flow field inside the scramjet engine are characterized respectively, realizing the identification and zoning of the thermochemical non-equilibrium of the scramjet engine.

2. The method for identifying thermochemical non-equilibrium partitions of a scramjet engine according to claim 1, wherein: The flow field and composition information obtained by the numerical simulation includes the translational-rotational temperature under non-equilibrium conditions. T tr ,pressure P , the density of the mixture ρ , components in the flow field s Density ρ s and components s Chemical reaction source term ω s .

3. The method for identifying thermochemical non-equilibrium zones in a scramjet engine according to claim 1, wherein: When the thermal Dam-Kohler number approaches 0, the flow is in a thermodynamically frozen state; When the thermal Dam-Kohler number approaches 1, the flow is in a thermodynamic non-equilibrium state; When the thermal Dam-Kohler number approaches positive infinity, the flow is in thermodynamic equilibrium.

4. The method for identifying thermochemical non-equilibrium zones in a scramjet engine according to claim 1, wherein: When the chemical Damköhler number approaches 0, the flow is in a chemically frozen state; When the chemical Damköhler number approaches 1, the flow is in a chemical non-equilibrium state; When the chemical Damköhler number approaches positive infinity, the flow is in chemical equilibrium.

5. The method for identifying thermochemical non-equilibrium partitions of a scramjet engine according to claim 1, wherein: Chemical reaction time defined by chemical reaction rate τ che(reaction) and chemical reaction times defined by components τ che(species) It is derived based on the continuity equation and is applicable to chemical reactions of all orders and various reaction components.

6. Scramjet engine thermochemical non-equilibrium partition identification system, characterized by: include: The numerical simulation module is configured to: perform numerical simulation of hydrogen injection ignition and combustion in the flow channel of the scramjet engine taking into account thermochemical non-equilibrium, and obtain flow field flow and composition information; a characteristic time calculation module configured to calculate the local flow characteristic time, chemical reaction characteristic time, and vibration mode relaxation time inside the scramjet engine based on flow field flow and component information; The local flow characteristic time τ f The calculation method is: Where, Δ x and Δ y Respectively x Direction and y The grid length in the direction, u i and v i Respectively x and y local speed in the direction; The characteristic time of chemical reactions can be expressed by reaction or by component, specifically: Where, τ che(reaction) is the chemical reaction time defined by the chemical reaction rate, ρ and M represent the density and molar mass of the mixture, Rr is the chemical reaction rate; τ che(species) is the chemical reaction time defined by the components, ρ s For components s The density, ω s For components s Chemical reaction source term; Based on the Millikan-White relationship, combined with the pressure obtained by numerical simulation P and translational-rotational temperature T tr , calculate the vibration mode relaxation time τ V ; The Damköhler number characterization module is configured to: calculate the thermal Damköhler number based on the local flow characteristic time and the vibration mode relaxation time, and calculate the chemical Damköhler number based on the local flow characteristic time and the chemical reaction characteristic time; The thermal Damköhler number and the chemical Damköhler number are specifically defined as follows: In the formula, Da v is the thermal Damköhler number, Da che is the chemical Damköhler number, τ f is the local flow characteristic time, τ V is the vibration mode relaxation time, τ che is the characteristic time of chemical reaction; The identification and partitioning module is configured to characterize the thermodynamic non-equilibrium characteristics and chemical non-equilibrium characteristics of the flow field inside the scramjet engine based on the calculated thermal Damköhler number and chemical Damköhler number, respectively, to achieve the identification and partitioning of the thermochemical non-equilibrium of the scramjet engine.

7. A computer-readable storage medium having a program stored thereon, characterized in that: When the program is executed by a processor, the steps of the method for identifying thermochemical non-equilibrium partitions of a scramjet engine according to any one of claims 1 to 5 are implemented.

8. An electronic device comprising a memory, a processor, and a program stored in the memory and executable on the processor, wherein: When the processor executes the program, the steps of the method for identifying thermochemical non-equilibrium partitions of a scramjet engine according to any one of claims 1 to 5 are implemented.

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