Construction method of fragmentation evolution mechanism model of aviation kerosene combustion soot particles

Abstract

The application relates to the field of aviation technology, in particular to a method for constructing a fragmentation evolution mechanism model of aviation kerosene combustion soot particles, which comprises the following steps: obtaining a kinetic mechanism of aviation kerosene fuel combustion chemical reaction; performing soot particle dynamics simulation according to a simplified mechanism and a particle group balance theory to obtain a soot particle balance mechanism model, then incorporating a particle fragmentation mechanism, and determining a soot particle balance equation by using a statistical mechanics method; coupling the soot particle balance equation and a Navier-Stokes (N-S) equation to simulate a soot generation process of aviation kerosene fuel in a combustion process, obtaining a space-time variation law of soot particle size distribution under different working conditions, and finally predicting an evolution process of the soot particles generated by aviation kerosene fuel combustion under different working conditions. Therefore, the method solves the problems in the prior art that the fragmentation mechanism of the soot particles is ignored, and the simulation and prediction accuracy of the aviation kerosene combustion generated soot particles is low.

Description

Technical Field

[0001] This application relates to the field of aviation technology, and in particular to a method for constructing a model of the fragmentation and evolution mechanism of carbon soot particles from aviation kerosene combustion. Background Technology

[0002] Over the past few decades, aviation, as the fastest and most efficient mode of transportation in human economic activity, has seen its emissions account for a continuously rising proportion of total air pollutant emissions. The industry, academia, and the general public are increasingly concerned about the impact and hazards of civil aviation emissions. In 2017, the International Civil Aviation Organization (ICAO) revised Annex 16 Volume 2, identifying particulate matter as a limited pollutant for emissions from next-generation civil aircraft engines. New emission standards for the mass and quantity of non-volatile particulate matter during the landing and takeoff cycles of aircraft engines replaced the emission smoke value standards implemented since the 1980s. Starting January 1, 2023, subsonic civil aircraft turbofan and turbojet engines with a rated thrust greater than 26.7 kN must meet the latest ICAO particulate matter emission standards during type certification. Aviation kerosene is the primary fuel for civil aircraft engines worldwide, and particulate matter is a significant pollutant generated during its combustion. With the advancements in the performance of next-generation civil aviation engines, particulate matter emissions are becoming increasingly smaller and more difficult to measure. However, their main component is carbon soot particles of varying sizes. Related research indicates that particulate matter emissions from aircraft engines during operation have a significant impact on airport air quality and human health. Furthermore, civil aviation emissions are a major source of atmospheric pollutants in the upper troposphere. Mainstream research suggests that particulate matter emissions can lead to enhanced radiative forcing, directly influencing climate change, and can also indirectly affect climate change by increasing contrails. Therefore, accurate measurement and prediction of particulate matter emissions from civil aviation engines are crucial.

[0003] For aircraft engines, the formation of soot reduces the combustion efficiency of the combustion chamber and increases the heat load on the combustion chamber walls. For human health, the scattering and absorption of sunlight and the absorption of infrared radiation by soot particles exacerbate temperature fluctuations. The precursors of particulate matter, such as polycyclic aromatic hydrocarbons, can also increase the risk of cancer in humans. The negative effects on the human respiratory system are also significant. The deposition rate of ultrafine particulate matter with a diameter of less than 100 nanometers (PM0.1) in the human respiratory tract is higher than 50%, and the smaller the particulate matter, the deeper it can penetrate into the respiratory tract, and it can even penetrate the alveoli and enter the bloodstream, causing asthma, lung cancer, and cardiovascular diseases.

[0004] Whether an aero-engine's particulate matter emission performance is up to standard has a significant impact on its airworthiness certification. The performance design of the next generation of civil aero-engines must meet the latest emission standards of the International Civil Aviation Organization (ICAO). Accurately predicting the distribution and evolution of carbon soot particles generated by the combustion of aviation kerosene under different operating conditions is of great engineering value for assessing its emission performance. Studies have explored the impact of fragmentation mechanisms on soil aggregate stability, droplet size, and particle size. For example, Sun Yiqiu et al. used three different fragmentation treatments on black soil aggregates to analyze the effects of freeze-thaw cycles and initial moisture content on the stability of soil aggregates with different initial particle sizes. Zhu Lingling et al. used numerical simulation to study the influence of different fragmentation mechanisms on metal droplet size. Zhang Cun et al. studied the fragmentation characteristics and their influencing mechanisms during the compaction process of coal samples with different particle sizes. Chi Changjiang conducted related research on the basic modes and intrinsic mechanisms of spherical particle layer crushing under pressure. All these studies indicate that fragmentation mechanisms play an important role in the formation of particles with different sizes. However, current research in China on the fragmentation mechanism of carbon soot particles during aviation kerosene combustion is lacking, resulting in an inability to effectively control aviation carbon emissions. Summary of the Invention

[0005] This application provides a method, apparatus, electronic device, and storage medium for constructing a model of the fragmentation and evolution mechanism of carbon soot particles generated by aviation kerosene combustion, in order to solve the problem that the fragmentation mechanism of carbon soot particles is ignored in related technologies, resulting in low accuracy in the simulation and prediction of carbon soot particles generated by aviation kerosene combustion.

[0006] The first aspect of this application provides a method for constructing a fragmentation evolution mechanism model of soot particles from aviation kerosene combustion, comprising the following steps: obtaining the kinetic mechanism of the chemical reaction of aviation kerosene fuel combustion; performing soot particle dynamics simulation based on the simplified mechanism of the kinetic mechanism and particle swarm equilibrium theory to obtain a soot particle equilibrium mechanism model; incorporating a particle fragmentation mechanism into the equilibrium mechanism model and determining the soot particle equilibrium equation of the soot particle equilibrium mechanism model using statistical mechanics methods; simulating the soot generation process of aviation kerosene fuel during combustion using the soot particle equilibrium equation to obtain the spatiotemporal variation law of soot particle size distribution under different operating conditions, thereby constructing the fragmentation evolution mechanism model of combustion soot particles; iteratively correcting the fragmentation evolution mechanism model that fails verification; obtaining the final fragmentation evolution mechanism model after successful verification; and using the final fragmentation evolution mechanism model to predict the evolution process of soot particles generated by aviation kerosene fuel combustion under different operating conditions.

[0007] Furthermore, the kinetic mechanism includes the reaction mechanisms of each component in aviation kerosene fuel. The simplification process includes: coupling the reaction mechanisms of each component to obtain a coupled model; using a direct relationship diagram to simplify the coupled model to obtain a skeleton kinetic mechanism; and extracting the target reaction path in the reaction path of the skeleton kinetic mechanism to construct the simplified mechanism.

[0008] Furthermore, the equation for the soot particle breakage mechanism is as follows:

[0009]

[0010] Where, N i and N j Let represent the number density of soot particles composed of i or j carbon atoms, where j > i; kfg(i) represents the breakage frequency of soot particles containing i carbon atoms; P(i|j) represents the fragmentation distribution function, which describes how many soot particles containing i carbon atoms are generated when a soot particle containing j carbon atoms breaks.

[0011] Furthermore, the statistical mechanics method is the Monte Carlo method. The step of using the statistical mechanics method to determine the carbon soot particulate matter balance equation of the carbon soot particulate matter balance mechanism model includes: quantifying the spatiotemporal evolution process of the discrete carbon soot particulate matter size distribution based on the Monte Carlo method to obtain the carbon soot particulate matter balance equation of the carbon soot particulate matter balance mechanism model.

[0012] Furthermore, the verification process of the breakup evolution mechanism model includes: acquiring first real data on the ignition delay and laminar flame propagation speed of aviation kerosene fuel combustion, and first simulated data on the ignition delay and laminar flame propagation speed of combustion simulated by the breakup evolution mechanism model; calculating a first simulation error based on the first real data and the first simulated data; if the first simulation error is not within a first preset range, then correcting the breakup evolution mechanism model until the first simulation error is within the first preset range; after the first simulation error is within the first preset range, acquiring second real data on the number concentration of particulate matter generated by soot during the premixed combustion of aviation kerosene fuel, and second simulated data on the number concentration of particulate matter generated by soot simulated by the breakup evolution mechanism model; calculating a second simulation error based on the second real data and the second simulated data; if the second simulation error is not within a second preset range, then correcting the breakup evolution mechanism model until the second simulation error is within the second preset range, thus obtaining the final breakup evolution mechanism model.

[0013] The second aspect of this application provides an apparatus for constructing a model of the fragmentation and evolution mechanism of soot particles from aviation kerosene combustion, comprising: an acquisition module for acquiring the kinetic mechanism of the combustion chemical reaction of aviation kerosene fuel; a first simulation module for performing soot particle dynamics simulation based on a simplified mechanism of the kinetic mechanism and particle swarm equilibrium theory to obtain a soot particle equilibrium mechanism model, incorporating a particle fragmentation mechanism into the equilibrium mechanism model, and determining the soot particle equilibrium equation of the soot particle equilibrium mechanism model using statistical mechanics methods; and a second simulation module for simulating the soot generation process of aviation kerosene fuel during combustion using the soot particle equilibrium equation, obtaining the spatiotemporal variation law of soot particle size distribution under different operating conditions, so as to construct the fragmentation and evolution mechanism model of the combustion soot particles, iteratively correcting the fragmentation and evolution mechanism model that fails verification, obtaining a final fragmentation and evolution mechanism model after successful verification, and using the final fragmentation and evolution mechanism model to predict the evolution process of soot particles generated by aviation kerosene fuel combustion under different operating conditions.

[0014] A third aspect of this application provides an electronic device, including: a memory, a processor, and a computer program stored in the memory and executable on the processor. The processor executes the program to implement the method for constructing a fragmentation evolution mechanism model of aviation kerosene combustion soot particles as described in the above embodiments.

[0015] A fourth aspect of this application provides a computer-readable storage medium having a computer program stored thereon, which is executed by a processor to implement a method for constructing a model of the fragmentation and evolution mechanism of aviation kerosene combustion soot particles as described in the above embodiments.

[0016] Therefore, this application has at least the following beneficial effects:

[0017] (1) The carbon soot particle prediction model in this application greatly improves the accuracy of simulation and prediction of carbon soot particles generated by aviation kerosene combustion by incorporating the carbon soot particle breakage dynamics mechanism.

[0018] (2) The embodiments of this application use the Monte Carlo method to solve the high-dimensional problem of probability distribution based on statistical mechanics and obtain the spatiotemporal distribution of the number concentration of carbon soot particles under different particle sizes. This method is mathematically rigorous, highly efficient, and has a small amount of computation.

[0019] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0020] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0021] Figure 1 This is a logic method diagram of the fragmentation mechanism model of aviation kerosene combustion soot particles according to an embodiment of this application;

[0022] Figure 2 This is a product structure diagram of the carbon soot particle prediction model according to an embodiment of this application;

[0023] Figure 3 A comparison diagram of ignition delay propagation speed obtained from simulation and experiment based on a simplified reaction mechanism of aviation kerosene according to embodiments of this application;

[0024] Figure 4 A comparison diagram of the laminar flame propagation speed obtained from simulation and experiment based on the simplified reaction mechanism of aviation kerosene according to embodiments of this application;

[0025] Figure 5 This is a comparison chart of the number concentration of particulate matter obtained from the simulation of soot generation in the premixed combustion process of aviation kerosene according to the embodiments of this application (including and without the crushing mechanism) and the experiment.

[0026] Figure 6 A block diagram of an apparatus for constructing a model of the fragmentation and evolution mechanism of carbon soot particles from aviation kerosene combustion according to an embodiment of this application.

[0027] Explanation of reference numerals in the attached figures:

[0028] 1-Aviation kerosene tank, 2-Pressure gauge and control valve, 3-Flow meter, 4-Air tank, 5-Heater, 6-Thermocouple, 7-Atomizing nozzle, 8-Cooling water tank, 9-Cooling water pipe, 10-Rectifying fine glass beads, 11-PC (Personal Computer) data acquisition and control terminal, 12-Data connection cable, 13-High-speed camera, 14-Premixed combustion lifting flame, 15-SMPS (Scanning Mobility Particle Size Spectrometer), 16-Soot particle sampling probe, 17-Glass jacket, 18-Coaxial jet burner (Coflow burner - a typical basic combustion device for premixing and pre-evaporating aviation kerosene with air). Detailed Implementation

[0029] The embodiments of this application are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0030] refer to Figure 1 In this embodiment, aviation kerosene tank 1 delivers aviation kerosene to a coaxial jet burner 18 inside a glass jacket 7 via a connecting pipe, pressure gauge and control valve 2, flow meter 3, heater 5, thermocouple 6, and atomizing nozzle 7; air tank 4 delivers air to the coaxial jet burner 18 inside the glass jacket 7 via a connecting pipe, pressure gauge and control valve 2, and flow meter 3; rectifier fine glass beads 10 are also provided inside the glass jacket 7 to form a premixed combustion gas between aviation kerosene and air in the coaxial jet burner 18, and generate a premixed combustion lifting flame 14 after ignition; a sampling probe 16 is provided above the lifting flame 14, and the carbon soot particle number concentration is tested by an SMPS scanning electromobility particle size spectrometer 15; a cooling water pipe 9 is provided on the lower left side of the glass jacket 7, and the other end of the cooling water pipe 9 is connected to a cooling water tank 8; a high-speed camera 13 is provided outside the glass jacket 7 and electrically connected to a data connection cable 12 to transmit data to a PC data acquisition and control terminal 11; Figure 1 The dashed lines represent the connections between devices, and the dotted lines represent the communication between devices.

[0031] Aviation kerosene tank 1 is the aviation kerosene supply source, and air tank 4 is the air supply source, both being combustible gas supply sources. The gas source is supplied from the lower end of the coaxial jet burner 18. After passing through the heater 5 and atomizing nozzle 7, the aviation kerosene mixes with air within the glass sleeve 17 to form a premixed combustion gas. Then, the premixed fuel in the coaxial jet burner 18 is ignited, producing a premixed combustion lifting flame 14. The carbon soot particles generated above the flame are collected by the carbon soot particle sampling probe 16 and their number concentration is measured by the SMPS scanning electromobility particle size analyzer 15. Subsequently, by adjusting the flow controller 3, the mixing of aviation kerosene and air can be achieved. The proportion of gas was changed, thereby altering the equivalence ratio of the mixed fuel gas. Furthermore, by adjusting the position of the soot particle sampling probe 16, sampling was conducted at different flame heights, enabling the sampling of soot particle number concentrations at different equivalence ratios (0.6-1.4) and flame heights (0.2-0.6 cm above the flame), and the influencing mechanism was analyzed. During the experiment, thermocouple 6 was used to monitor the temperature rise before jet fuel atomization, the temperature of the cooling water tank 8, and the temperature of the mixed fuel gas. Temperature observation at each point was used to determine the stability of jet fuel combustion. Simultaneously, a high-speed camera 13 was used to capture the flame morphology, further recording details of flame stability during the sampling process. In addition, a PC terminal 11 was used to control the high-speed camera 13 and thermocouple 6 and collect their data. Finally, a verification experiment was conducted to investigate the fragmentation mechanism of soot particles generated during jet fuel combustion.

[0032] Based on the above system, the following is combined with Figure 2The method for constructing a model of the fragmentation and evolution mechanism of carbon soot particles from aviation kerosene combustion is described in detail below:

[0033] Step 1: Constructing a simplified combustion chemical reaction kinetics process for an aviation kerosene model fuel.

[0034] The representative components of aviation kerosene fuel are mainly n-decane, isooctane, butylcyclohexane, and propylbenzene. The chemical reaction kinetics of various elements are relatively well-established. Using a reaction workbench, their respective reaction mechanisms are coupled. During the coupling process, repeated chemical reactions are used, primarily based on the n-decane mechanism, to construct a detailed multi-component chemical reaction kinetic model. Then, a combination of simplification methods—DRG (Directed Relation Graph Method), PCA (Principal Component Analysis), QSSA (The Quasi Steady-State Approximation), and FSSA (Full Species Sensitivity Analysis)—are employed to simplify the detailed mechanism, yielding the skeletal kinetic mechanism of the aviation kerosene model fuel. Finally, reaction path analysis is performed on the skeletal kinetic mechanism to extract important reaction pathways, resulting in the final simplified mechanism. Then, the ignition delay was calculated using Chemkin (chemical reaction kinetic model) combined with a simplified mechanism and compared with experimental data. If the accuracy did not meet the requirements, the pre-exponential factor, activation energy, etc. of the chemical reaction were considered.

[0035] Step 2: Construct a particulate matter balance mechanism model for carbon soot generation

[0036] Based on the simplified chemical reaction mechanism of the model fuel, particle swarm equilibrium theory is used to simulate particulate dynamics, studying the nucleation, coagulation, surface growth, and oxidation processes of soot particles during aviation kerosene combustion, and constructing a detailed model for soot particle formation. The particulate equilibrium equation is as follows:

[0037]

[0038] In the formula: the first term represents the nucleation rate, the second term represents particle growth and surface oxidation, and the third term represents particle coagulation or agglomeration. In the simulation of soot generation, solving the particle swarm equilibrium equation can achieve analytical analysis of the spatiotemporal evolution of soot particle size distribution.

[0039] Step 3: Incorporate particle breakage mechanism into detailed model of soot formation.

[0040] The mechanism for explaining particulate matter breakup is incorporated into the particulate matter balance equation, as shown in the following equation:

[0041]

[0042] Where: N i and N j Let represent the number density of soot particles composed of i or j carbon atoms, where j > i. The first term on the right-hand side of the equation represents the generation of smaller soot particles, mainly due to the breakup of larger soot particles. The second term represents the elimination of smaller soot particles, mainly due to the breakup of the soot particle itself. Here, kfg(i) describes the breakup frequency of soot particles containing i carbon atoms; P(i|j) is the fragmentation distribution function, describing how many soot particles containing i carbon atoms are generated when a soot particle containing j carbon atoms breaks up.

[0043] Step 4: Solve the particulate matter equilibrium equations using the Monte Carlo method.

[0044] The evolution of soot particles generated by aviation kerosene combustion can be viewed as a dynamic event of a discrete system. The Monte Carlo method, a computational method based on random numbers and possessing discrete characteristics, is similar to the discrete characteristics of particle swarms and dynamic events. The macroscopic properties of discrete particle swarms are closely related to the distribution function of variables within the swarm, with the spatiotemporal distribution of particle size being of most interest—that is, the variation of the number concentration of particles of a certain size in spatiotemporal coordinates. Theoretical methods based on Monte Carlo to solve particle swarm equilibrium equations quantify the spatiotemporal evolution of particle size distribution in discrete particle swarms to describe the dynamic process of soot particles, thereby enabling macroscopic numerical simulations of complex systems. The Monte Carlo method can handle high-dimensional space problems in a simple and direct extended way, providing a more realistic approach to the formation and evolution of particle swarm variable distribution functions described by physical models, thus achieving efficient and accurate zero-dimensional and multi-dimensional simulations of soot particle emissions.

[0045] Step 5: Simulate the soot generation process of actual aviation kerosene premixed combustion.

[0046] The above-mentioned mechanism model of soot particle formation is combined with the Navier-Stokes (NS) equation to describe the hydrodynamic process of soot particles under the influence of buoyancy during combustion in a coaxial jet burner. A set of closed equations using probability density functions is used to form a particle transport equation, which is solved using the Monte Carlo method. This simulates the soot formation process during actual aviation kerosene combustion and obtains the spatiotemporal variation law of soot particle size distribution under different operating conditions.

[0047] Step 6: Verification of the fragmentation mechanism of carbon soot particles generated from aviation kerosene combustion

[0048] The verification of the fragmentation mechanism of soot particle generation in aviation kerosene combustion, after successful verification, yields the final fragmentation evolution mechanism model, which involves the following two steps: 1) Comparing the first simulated data of ignition delay and laminar flame propagation speed in the simplified reaction mechanism simulation of aviation kerosene with the first real data of ignition delay and laminar flame propagation speed obtained from experiments, and determining whether the error is within a first preset range, such as 5%. If not, the coupling and simplification process of Chemkin's mechanism model is modified and optimized; 2) Comparing the second simulated data of particulate number concentration in the soot generation simulation of aviation kerosene premixed combustion process with the second real data of particulate number concentration obtained from experiments, and determining whether the error is within a second preset range, such as 10%. If not, the solution and iteration process of the particulate balance equation are further modified and optimized. When the error can be controlled within the threshold range, the simulation method of soot particle evolution in aviation kerosene combustion containing the fragmentation mechanism is successfully constructed.

[0049] final combination Figure 1 and Figure 2 An experiment was conducted to verify the fragmentation mechanism of carbon soot particles generated during aviation kerosene combustion, and the data obtained from the experiment are as follows: Figure 3 , Figure 4 and Figure 5 As shown, the figures represent the ignition delay propagation velocity obtained from the simplified reaction mechanism simulation and experiment of aviation kerosene, the laminar flame propagation velocity obtained from the simplified reaction mechanism simulation and experiment of aviation kerosene, and the particulate number concentration obtained from the simulation and experiment of soot generation in the premixed combustion process of aviation kerosene. The error obtained from the experiment is used to determine whether the verification is successful. If the verification is successful, the simulation method of soot particle evolution in aviation kerosene combustion with a fragmentation mechanism is successfully constructed.

[0050] The method for constructing a fragmentation and evolution mechanism model of aviation kerosene combustion soot particles proposed in this application involves obtaining the combustion chemical reaction kinetics mechanism of aviation kerosene fuel and simplifying it to obtain a simplified mechanism. Based on the simplified mechanism and particle group equilibrium theory, a soot particle dynamics simulation is performed to obtain a soot particle equilibrium mechanism model. Then, the soot particle fragmentation mechanism is incorporated into the soot particle equilibrium mechanism model, and the soot particle equilibrium equation of the soot particle equilibrium mechanism model is determined using statistical mechanics methods. Based on this, the soot generation process during aviation kerosene fuel combustion is simulated to obtain the spatiotemporal variation law of soot particle size distribution under different operating conditions. Based on the law, a fragmentation and evolution mechanism model of aviation kerosene combustion soot particles is constructed and verified. If the verification fails, it is revised until the verification passes, resulting in the final fragmentation and evolution mechanism model. The model is then used to predict the evolution process of soot particles generated by aviation kerosene fuel combustion under different operating conditions. By incorporating the soot particle fragmentation kinetics mechanism, the accuracy of simulation and prediction of soot particles generated by aviation kerosene combustion is greatly improved.

[0051] Figure 6 This is a block diagram of the apparatus for constructing a model of the fragmentation and evolution mechanism of carbon soot particles from aviation kerosene combustion according to an embodiment of this application. Figure 6 As shown, the device 10 for constructing the fragmentation and evolution mechanism model of carbon soot particles from aviation kerosene combustion includes: an acquisition module 100, a first simulation module 200, and a second simulation module 300.

[0052] The module 100 is used to acquire the combustion chemical reaction kinetics mechanism of aviation kerosene fuel; the first simulation module 200 performs soot particle dynamics simulation based on the simplified kinetic mechanism and particle group equilibrium theory to obtain a soot particle equilibrium mechanism model, incorporates particle breakage mechanism into the equilibrium mechanism model, and uses statistical mechanics to determine the soot particle equilibrium equation of the soot particle equilibrium mechanism model; the second simulation module 300 is used to simulate the soot generation process of aviation kerosene fuel during combustion using the soot particle equilibrium equation, obtain the spatiotemporal variation law of soot particle size distribution under different operating conditions, so as to construct a breakage evolution mechanism model of combustion soot particles, iteratively correct the breakage evolution mechanism model that fails the verification, and obtain the final breakage evolution mechanism model after successful verification, and use the final breakage evolution mechanism model to predict the evolution process of soot particles generated by aviation kerosene fuel combustion under different operating conditions.

[0053] It should be noted that the explanation of the above-mentioned method for constructing the fragmentation and evolution mechanism model of aviation kerosene combustion soot particles also applies to the device for constructing the fragmentation and evolution mechanism model of aviation kerosene combustion soot particles in this embodiment, and will not be repeated here.

[0054] This application also provides an electronic device, which may include: a memory, a processor, and a computer program stored in the memory and executable on the processor; when the processor executes the program, it implements the method for constructing the fragmentation and evolution mechanism model of aviation kerosene combustion soot particles provided in the above embodiments.

[0055] This application also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the above-described method for constructing the fragmentation and evolution mechanism model of aviation kerosene combustion soot particles.

[0056] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A method for constructing a fragmentation evolution mechanism model of aviation kerosene combustion soot particles, characterized in that, The method comprises the following steps: obtaining a kinetic mechanism of aviation kerosene fuel combustion chemical reaction; performing a soot particle dynamics simulation according to a simplified mechanism of the kinetic mechanism and a particle population balance theory to obtain a soot particle balance mechanism model, incorporating a particle breakage mechanism in the balance mechanism model, and determining a soot particle balance equation of the soot particle balance mechanism model by using a statistical mechanics method, wherein the soot particle balance equation is as follows: In the formula, the first term represents a nucleation rate, the second term represents particle growth and surface oxidation, and the third term represents particle coagulation or agglomeration; In the soot particle balance equation, a particle breakage mechanism is incorporated, and the equation is as follows: where: and represents the number density of soot particles consisting of i or j carbon atoms, j > i, is used to describe the frequency of break-up of soot particles containing carbon atoms, is a fragment distribution function used to describe the production of soot particles containing i carbon atoms from the break-up of soot particles containing j carbon atoms; The soot particle generation process of the aviation kerosene fuel in the combustion process is simulated by using the soot particle balance equation to obtain the temporal and spatial variation law of the soot particle size distribution under different working conditions, so as to construct a breakage evolution mechanism model of the combustion soot particle, and the breakage evolution mechanism model that fails to pass the verification is iteratively corrected, and the final breakage evolution mechanism model is obtained after the verification passes, and the evolution process of the soot particle generated by the aviation kerosene fuel combustion under different working conditions is predicted by using the final breakage evolution mechanism model.

2. The method of claim 1, wherein, The kinetic mechanism comprises reaction mechanisms of components in the aviation kerosene fuel, and the simplification process comprises: a coupling model is obtained by coupling the reaction mechanisms of the components, a skeleton kinetic mechanism is obtained by simplifying the coupling model by using a direct relationship diagram, and a target reaction path in the reaction path of the skeleton kinetic mechanism is extracted to construct the simplified mechanism.

3. The method of claim 1, wherein, The statistical mechanics method is a Monte Carlo method, and the determination of the soot particle balance equation of the soot particle balance mechanism model by using the statistical mechanics method comprises: The temporal and spatial evolution process of the discrete soot particle population size distribution is quantified based on the Monte Carlo method to obtain the soot particle balance equation of the soot particle balance mechanism model.

4. The method of claim 1, wherein, The verification process of the breakage evolution mechanism model comprises: obtaining first real data of ignition delay and laminar flame propagation speed of aviation kerosene fuel combustion, and first simulation data of ignition delay and laminar flame propagation speed of combustion simulated by the breakage evolution mechanism model; calculating a first simulation error according to the first real data and the first simulation data, and if the first simulation error is not within a first preset range, the breakage evolution mechanism model is corrected until the first simulation error is within the first preset range; after the first simulation error is within the first preset range, obtaining second real data of soot particle number concentration generated by aviation kerosene fuel in a premixed combustion process, and second simulation data of soot particle number concentration generated by the breakage evolution mechanism model; calculating a second simulation error according to the second real data and the second simulation data, and if the second simulation error is not within a second preset range, the breakage evolution mechanism model is corrected until the second simulation error is within the second preset range to obtain a final breakage evolution mechanism model.

5. A device for constructing a fragmentation evolution mechanism model of aviation kerosene combustion soot particles, characterized in that, comprise: The acquisition module is used to acquire the combustion chemical reaction kinetics mechanism of aviation kerosene fuel; The first simulation module is used to perform dynamic simulation of soot particulate matter based on the simplified mechanism of the aforementioned kinetic mechanism and the particle group equilibrium theory, thereby obtaining a soot particulate matter equilibrium mechanism model. This model incorporates a particle breakage mechanism, and statistical mechanics methods are used to determine the soot particulate matter equilibrium equations for the model. The soot particulate matter equilibrium equations are as follows: In the formula: the first term represents the nucleation rate, the second term represents particle growth and surface oxidation, and the third term represents particle coagulation or agglomeration; The particulate matter balance equation for carbon soot incorporates an explanation of the particulate matter fragmentation mechanism, as shown in the equation below: where: and Nj represents the number density of soot particles consisting of i or j carbon atoms, j > i, is used to describe the frequency of break-up of soot particles containing carbon atoms, is a fragment distribution function used to describe the production of soot particles containing i carbon atoms from the break-up of soot particles containing j carbon atoms; The second simulation module is used to simulate the generation process of soot during the combustion of aviation kerosene fuel using the soot particulate matter balance equation, to obtain the spatiotemporal variation law of soot particle size distribution under different operating conditions, so as to construct the fragmentation evolution mechanism model of the combustion soot particles, to iteratively correct the fragmentation evolution mechanism model that fails the verification, and to obtain the final fragmentation evolution mechanism model after successful verification, and to use the final fragmentation evolution mechanism model to predict the evolution process of soot particles generated by the combustion of aviation kerosene fuel under different operating conditions.

6. An electronic device, comprising: include: The method includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the method for constructing a fragmentation evolution mechanism model of aviation kerosene combustion soot particles as described in any one of claims 1-4.

7. A computer readable storage medium having stored thereon a computer program, characterized in that, The program is executed by the processor to implement the method for constructing the fragmentation evolution mechanism model of aviation kerosene combustion soot particles as described in any one of claims 1-4.

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