CN109657401B - Numerical simulation method for combustion flow field of solid fuel ramjet engine - Google Patents
Numerical simulation method for combustion flow field of solid fuel ramjet engine Download PDFInfo
- Publication number
- CN109657401B CN109657401B CN201910005280.8A CN201910005280A CN109657401B CN 109657401 B CN109657401 B CN 109657401B CN 201910005280 A CN201910005280 A CN 201910005280A CN 109657401 B CN109657401 B CN 109657401B
- Authority
- CN
- China
- Prior art keywords
- combustion
- propellant
- gas
- mass
- flow field
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/08—Thermal analysis or thermal optimisation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a numerical simulation method for a combustion flow field of a solid fuel ramjet engine, which comprises the following specific steps: firstly, carrying out gas thermodynamic calculation to obtain rich-fuel gas components and mass fractions of the components; then establishing a turbulence model, and calculating to obtain a turbulence stress term; secondly, establishing mass source items of all components of the fuel-rich gas, mass source items of oxides and energy source items of chemical reaction; then establishing a gas-phase combustion model, and calculating to obtain the gas-phase chemical reaction rate; and finally, substituting the solved numerical values into a gas phase control equation set, if the gas phase control equation set is converged, judging all flow field parameters as final results, and if the gas phase control equation set is not converged, adding relaxation factors to all initial parameters to perform the calculation again until the gas phase control equation set is converged. The simulation precision of the combustion flow field of the solid fuel ramjet engine is effectively improved by adopting the method.
Description
Technical Field
The invention relates to a combustion flow field simulation method, in particular to a numerical simulation method of a combustion flow field of a solid rocket ramjet.
Background
Numerical simulation is an important means for researching the combustion flow of the solid fuel ramjet, the simulation of the combustion flow of the solid fuel ramjet is very complex, solid fuel (namely propellant) in a main combustion chamber is decomposed to generate rich combustion gas, the rich combustion gas and air flow flowing through the main combustion chamber perform combustion chemical reaction, parameters such as speed, density and temperature of air flow near the combustion surface of the propellant can influence the temperature of the combustion surface to further influence the generation of the gas, and the parameters of the air flow can be influenced by the reaction between the generated gas and the air, and the temperature can finally reach balance due to the heat absorption of thermal decomposition and the heat dissipation of the main flow.
For the simulation of the combustion flow field of the solid fuel ramjet engine, the difficulty is mainly that the mass source terms and the energy source terms of the combustion surface of the simulated propellant are related to main flow gas, so the source terms of each point on the combustion surface are different and need to be calculated independently.
The simulation method of the combustion flow field of the existing solid fuel ramjet engine is shown in a table 1, and the adopted models comprise a basic equation, a turbulence model, a propellant decomposition model and a gas phase combustion model; wherein the basic equation is a Reynolds average N-S equation, and the turbulence model is an RNG with swirl correction k The-epsilon model and the gas phase combustion model adopt a vortex group dissipation model and a propellant decomposition model based on the Arrhenius law, and the rich combustion gas component adopts a single component and has no energy source item.
TABLE 1 short description of the existing simulation method
It has the following problems: firstly, the composition of the fuel-rich gas is complex, and only one composition is not only used without reference, but also has a large difference from the actual situation, so that the simulation error is large. Secondly, the decomposition of the solid propellant carries away some heat, which if not taken into account would cause an inaccurate number of mass source terms.
Disclosure of Invention
In view of this, the invention provides a simulation method for a combustion value of a solid fuel ramjet, which can effectively improve the simulation accuracy of a combustion flow field of the solid fuel ramjet.
The numerical simulation method of the solid fuel ramjet combustion flow field is characterized in that when numerical simulation is carried out on the solid fuel ramjet combustion flow field, a mass source item and an energy source item of a propellant combustion surface are added; the mass source items of the propellant combustion surface comprise mass source items of all components of fuel-rich gas and oxide mass source items;
the quality source items of the propellant combustion surface are as follows:
the mass source items of each component of the fuel-rich gas are as follows: multiplying the mass source term of the combustion surface of the propellant by the mass fraction of each component of the fuel gas rich in combustion; the mass source terms of the oxides are as follows: multiplying the mass source term of the propellant combustion surface by the mass of the oxide consumed by the propellant per unit mass, wherein the mass source term of the oxide is negative;
the energy source term of the combustion surface of the propellant is
Wherein: A. e a Refer to pro-factor and activation energy, respectively; r is the general gas constant, T w Identifying a temperature for a combustion face of the propellant; a. The C Is the area of the combustion surface of the propellant; rho f Is the density of the propellant, h v In order to decompose or gasify the latent heat of the propellant,
as the burning rate of the propellant, c f Specific heat of propellant, T 0 Is the initial temperature of the combustion surface of the propellant.
The method comprises the following steps:
the method comprises the following steps: performing combustion thermodynamic calculation on the propellant to obtain components of the formed fuel-rich gas, the mass fraction of each component and the temperature of the fuel-rich gas;
step two: establishing a turbulence model, and calculating turbulence stress of a combustion flow field;
step three: establishing mass source terms and oxide mass source terms of all components of the fuel gas rich in the propellant combustion surface and energy source terms of the propellant combustion surface;
step four: establishing a gas-phase combustion model, and calculating the gas-phase chemical reaction rate of a combustion flow field;
step five: substituting the parameters obtained by calculation in the first step to the fourth step and the established quality source item and energy source item of the combustion surface of the propellant as initial parameters into a gas phase control equation set, and finishing simulation if the gas phase control equation set is converged; and if the gas phase control equation set is not converged, adding relaxation factors to all initial parameters, returning to the step one, and performing the calculation again until the gas phase control equation set is converged.
Advantageous effects
According to the method, the components and the mass fraction of the fuel-rich gas are obtained through thermodynamic calculation, the mass source item and the energy source item of the fuel-rich gas decomposed by the solid propellant are calculated through the Arrhenius law, and the method is closer to the actual combustion process, so that the combustion simulation precision of the solid fuel ramjet can be effectively improved.
Drawings
FIG. 1 is a flow chart of a solid fuel ramjet combustion flow field numerical simulation method of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
The embodiment provides a numerical simulation method for a combustion flow field of a solid fuel ramjet, and the method can effectively improve the combustion simulation precision of the solid fuel ramjet.
The numerical simulation method is realized in FLUENT software, and comprises the following specific steps:
the method comprises the following steps: performing combustion thermodynamic calculation on a propellant (namely a fuel rich in combustion) by adopting a minimum Gibbs free energy method to obtain components of the fuel rich in combustion gas, mass fractions of the components and the temperature of the fuel rich in combustion gas;
step two: establishing a turbulence model, and solving turbulence stress;
establishing a turbulence model of the combustion flow field by adopting a Realizblek-epsilon model, and solving the turbulence stress of the combustion flow field;
step three: establishing a fuel-rich gas source item:
the fuel-rich gas source item comprises: a mass source term and an energy source term of a propellant combustion surface; the mass source items of the combustion surface of the propellant are total mass source items, and the mass source items comprise mass source items of all components of the fuel-rich gas and mass source items of oxides.
Taking the fuel-rich gas component obtained by thermodynamic calculation in the step one as the fuel-rich component generated by the combustion surface, wherein the combustion surface advancing rate conforms to the Arrhenius law, namely the combustion speed of the propellant
Wherein: A. e a Are pro-factor and activation energy, respectively, a =8.25 × 10 2 m/s，E a =133539j/mol, R is the universal gas constant, R =8.31451 j/(mol.k), T w The identification temperature of the grid cells of the near-propellant combustion surface.
A is to be C Xr as the total mass source term for a flour grid cell, where A C The area of the grid unit of the combustion surface on the combustion surface of the propellant is defined as the total mass source term of the grid unit on the combustion surface of the propellant
After the total mass source items of the propellant combustion surface grid units and the mass fractions of all components of the fuel-rich gas are obtained, the mass source items of all the components of the fuel-rich gas are the total mass source items multiplied by the mass fractions of all the components; the oxide mass source term is the total mass source term multiplied by the mass of oxide consumed per mass of propellant, with a negative sign.
The energy conservation relation existing between the gas phase and the solid phase on the gas-solid interface in the combustion chamber is alpha (T) ∞ -T w )＝ρ f h v r+ρ f rc f (T w -T 0 ) Wherein: rho f As propellant density, h v Latent heat of decomposition or gasification of the propellant, c f Specific heat of propellant, T ∞ Is near the main stream temperature of the combustion surface of the propellant, T 0 Is the initial temperature of the propellant fired surface grid cells. Neglecting radiation heat exchange, will rho f h v r+ρ f rc f (T w -T 0 ) As the energy source term of the combustion surface grid unit, the energy source term of the rich combustion gas of the combustion surface grid unit is
Step four: establishing a gas-phase combustion model: the gas-phase combustion model adopts a vortex group dissipation model, and the gas-phase chemical reaction rate is calculated through the vortex group dissipation model.
Step five: calculating the model of the second to the fourth steps through a gas phase control equation, wherein the calculation comprises the following steps:
solving the speed, temperature and density of fluid in a combustion flow field by using a Reynolds N-S equation set of a control equation comprising a continuous equation, a momentum equation, an energy equation and a transport equation of each component as an integral frame;
and taking parameters obtained by calculation of all the models as initial parameters to be brought into the gas phase control equation set, if the gas phase control equation set is converged, obtaining a final result, if the equation set is not converged, adding relaxation factors to all the initial parameters, returning to the calculation of the step one, repeating the whole process of the steps, and repeating the steps circularly until the equation is converged.
In conclusion, the method can simulate the steady-state whole process of the combustion of the solid fuel ramjet engine.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A numerical simulation method for a combustion flow field of a solid fuel ramjet engine is characterized by comprising the following steps: adding a quality source term and an energy source term of a propellant combustion surface when carrying out numerical simulation on a solid fuel ramjet combustion flow field; the mass source items of the propellant combustion surface comprise mass source items and oxide mass source items of all components of the fuel-rich gas;
the quality source items of the propellant combustion surface are as follows:
the quality source items of the components of the fuel-rich gas are as follows: multiplying the mass source term of the combustion surface of the propellant by the mass fraction of each component of the fuel gas rich in combustion; the mass source terms of the oxides are as follows: multiplying the mass source term of the combustion surface of the propellant by the mass of the oxide consumed by the propellant per unit mass, wherein the mass source term of the oxide is negative;
the energy source term of the combustion surface of the propellant is
Wherein: A. e a Refer to pro-factor and activation energy, respectively; r is the general gas constant, T w Identifying a temperature for a combustion face of the propellant; a. The C The area of the combustion surface of the propellant; ρ is a unit of a gradient f Is the density of the propellant, h v In order to decompose or gasify the latent heat of the propellant,
for the propellant burning rate, c f Specific heat of propellant, T 0 Is the initial temperature of the combustion surface of the propellant.
2. The solid fuel ramjet combustion flow field numerical simulation method of claim 1, wherein:
the method comprises the following steps: performing combustion thermodynamic calculation on the propellant to obtain components of the formed fuel-rich gas, the mass fraction of each component and the temperature of the fuel-rich gas;
step two: establishing a turbulence model, and calculating turbulence stress of a combustion flow field;
step three: establishing mass source terms and oxide mass source terms of all components of the fuel-rich gas of the propellant combustion surface and energy source terms of the propellant combustion surface;
step four: establishing a gas-phase combustion model, and calculating the gas-phase chemical reaction rate of a combustion flow field;
step five: substituting the parameters obtained by calculation in the first step to the fourth step and the established mass source item and energy source item of the combustion surface of the propellant as initial parameters into a gas phase control equation set, and finishing simulation if the gas phase control equation set is converged; and if the gas phase control equation set is not converged, adding relaxation factors to all initial parameters, returning to the step one, and performing the calculation again until the gas phase control equation set is converged.
3. The solid fuel ramjet combustion flow field numerical simulation method of claim 1, wherein in said first step thermodynamic calculations are performed by minimum gibbs free energy method.
4. The solid fuel ramjet combustion flow field numerical simulation method of claim 1, wherein a readable cable is adopted in the second step k-ε The model calculates the turbulence stress of the combustion flow field.
5. The solid fuel ramjet combustion flow field numerical simulation method of claim 1, wherein in the fourth step, a vortex-mass dissipation model is used to calculate the gas-phase chemical reaction rate of the combustion flow field.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910005280.8A CN109657401B (en) | 2019-01-03 | 2019-01-03 | Numerical simulation method for combustion flow field of solid fuel ramjet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910005280.8A CN109657401B (en) | 2019-01-03 | 2019-01-03 | Numerical simulation method for combustion flow field of solid fuel ramjet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109657401A CN109657401A (en) | 2019-04-19 |
| CN109657401B true CN109657401B (en) | 2022-12-23 |
Family
ID=66118455
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910005280.8A Active CN109657401B (en) | 2019-01-03 | 2019-01-03 | Numerical simulation method for combustion flow field of solid fuel ramjet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109657401B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111079235B (en) * | 2019-12-11 | 2023-04-07 | 内蒙动力机械研究所 | Method for simulating and rapidly converging internal flow field of solid rocket engine |
| CN111475939B (en) * | 2020-04-03 | 2023-04-25 | 南京信息职业技术学院 | Simulation calculation method for ballistic performance in gas jet impact liquid water column |
| CN114398844B (en) * | 2022-01-25 | 2023-04-07 | 南京航空航天大学 | Steady-state anti-icing simulation method based on continuous water film flow |
| CN115618171B (en) * | 2022-06-06 | 2023-10-24 | 北京理工大学 | Method for solving propellant combustion balance product based on homotopy algorithm |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106339551A (en) * | 2016-08-29 | 2017-01-18 | 广东电网有限责任公司电力科学研究院 | Simulation method and device for generation value of combustion characteristic of pulverized coal of power station boiler |
| CN106407594A (en) * | 2016-10-10 | 2017-02-15 | 中国神华能源股份有限公司 | Method and device for simulating oxygen-enriched combustion |
| CN107391436A (en) * | 2017-06-20 | 2017-11-24 | 北京航空航天大学 | Supersonic turbulent combustion flows computational methods based on flame front/progress variate model |
| CN107590336A (en) * | 2017-09-13 | 2018-01-16 | 哈尔滨理工大学 | Method for numerical simulation of the fuel gas pipeline leakage to internal flow |
| WO2018026345A1 (en) * | 2016-08-04 | 2018-02-08 | Halliburton Energy Services, Inc. | Time-dependent spatial distribution of at least one flow parameter in a network of fractures |
| CN107944150A (en) * | 2017-11-27 | 2018-04-20 | 南京航空航天大学 | Interior outflow multicomponent chemical reaction flow field integration numerical simulator |
| CN108304690A (en) * | 2018-01-31 | 2018-07-20 | 中国人民解放军国防科技大学 | Theoretical prediction method for burning rate of high-metal-content water-flushed engine |
-
2019
- 2019-01-03 CN CN201910005280.8A patent/CN109657401B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018026345A1 (en) * | 2016-08-04 | 2018-02-08 | Halliburton Energy Services, Inc. | Time-dependent spatial distribution of at least one flow parameter in a network of fractures |
| CN106339551A (en) * | 2016-08-29 | 2017-01-18 | 广东电网有限责任公司电力科学研究院 | Simulation method and device for generation value of combustion characteristic of pulverized coal of power station boiler |
| CN106407594A (en) * | 2016-10-10 | 2017-02-15 | 中国神华能源股份有限公司 | Method and device for simulating oxygen-enriched combustion |
| CN107391436A (en) * | 2017-06-20 | 2017-11-24 | 北京航空航天大学 | Supersonic turbulent combustion flows computational methods based on flame front/progress variate model |
| CN107590336A (en) * | 2017-09-13 | 2018-01-16 | 哈尔滨理工大学 | Method for numerical simulation of the fuel gas pipeline leakage to internal flow |
| CN107944150A (en) * | 2017-11-27 | 2018-04-20 | 南京航空航天大学 | Interior outflow multicomponent chemical reaction flow field integration numerical simulator |
| CN108304690A (en) * | 2018-01-31 | 2018-07-20 | 中国人民解放军国防科技大学 | Theoretical prediction method for burning rate of high-metal-content water-flushed engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109657401A (en) | 2019-04-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109657401B (en) | Numerical simulation method for combustion flow field of solid fuel ramjet engine | |
| Spalding | GENMIX: A general computer program for two-dimensional parabolic phenomena | |
| CN107346353B (en) | Solid comburent combustion process simulation method and server | |
| CN109408915B (en) | Simulation method for combustion flow field of solid rocket scramjet engine | |
| Larsson | Large eddy simulation of the HyShot II scramjet combustor using a supersonic flamelet model | |
| Klapdor et al. | A compressible pressure-based solution algorithm for gas turbine combustion chambers using the PDF/FGM model | |
| Bicsák et al. | Numerical simulation of combustion processes in a gas turbine | |
| Uysal et al. | A thermodynamic model to quantify the impact of cooling improvements on gas turbine efficiency | |
| Prokhorov et al. | Development of a simplified methodology for furnace aerodynamics with vortex combustion of organic fuel modeling | |
| Gray et al. | Thermodynamics for gas turbine cycles with analytic derivatives in openmdao | |
| Huelskamp et al. | Improved correlation for blowout of bluff body stabilized flames | |
| Luque et al. | Scaling of turbine metal temperatures in cooled compressible flows—experimental demonstration of a new theory | |
| CN104729855A (en) | Method for assessing influences of experiment gas pollution on supersonic combustion ramjet engine performance | |
| Vyasaprasath et al. | Numerical studies of supersonic planar mixing and turbulent combustion using a detached eddy simulation (DES) model | |
| VanZante et al. | The attenuation of a detonation wave by an aircraft engine axial turbine stage | |
| Clark et al. | Review of numerical modeling and simulation results pertaining to high-speed combustion in scramjets | |
| Klapdor et al. | Towards investigation of combustor turbine interaction in an integrated simulation | |
| Legrenzi | A coupled CFD approach for combustor-turbine interaction | |
| Zou et al. | Simulation of turbulent combustion in DLR Scramjet | |
| Hassan et al. | Reacting Dynamic Hybrid RANS/LES Computations of a Supersonic Cavity | |
| Reardon et al. | Computational modeling of radiation effects on total temperature probes | |
| Bruneflod | Flow simulations of an axisymmetric two-dimensional 3rd generation DLE burner | |
| Escobar | Rotating detonation combustion: A computational study for stationary power generation | |
| Gao et al. | Research on fuel control method of scramjet | |
| Potturi | Numerical Simulation of High-Speed Combustion Processes in Scramjet Configurations |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |