CN109657401A - A kind of solid fuel ramjet Combustion Flow Field numerical value emulation method - Google Patents
A kind of solid fuel ramjet Combustion Flow Field numerical value emulation method Download PDFInfo
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- CN109657401A CN109657401A CN201910005280.8A CN201910005280A CN109657401A CN 109657401 A CN109657401 A CN 109657401A CN 201910005280 A CN201910005280 A CN 201910005280A CN 109657401 A CN109657401 A CN 109657401A
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Abstract
The invention discloses a kind of solid fuel ramjet Combustion Flow Field numerical value emulation method, the specific steps of this method are as follows: progress combustion gas calculation of thermodynamics first obtains the mass fraction of fuel-rich gas component and each ingredient；Then turbulence model is established, turbulent stress item is calculated；Next establishes each composition quality source item of fuel-rich combustion gas, oxide mass source item and chemical reaction energy source item；Then gas-phase combustion model is established, gas-phase chemical reaction rate is calculated；The numerical value of above-mentioned solution is finally substituted into gas-phase governing equations group, if gas-phase governing equations group restrains, then determine all flow field parameters for final result, if the gas-phase governing equations group does not restrain, relaxation factor is added to re-start above-mentioned calculating all initial parameters, until the gas-phase governing equations group restrains.The simulation accuracy of solid fuel ramjet Combustion Flow Field is effectively improved using this method.
Description
Technical field
The present invention relates to a kind of Combustion Flow Field emulation modes, and in particular to a kind of solid rocket ramjet Combustion Flow Field
Numerical value emulation method.
Background technique
Numerical simulation is the important means of solid fuel ramjet combustion flows research, solid fuel ramjet
Combustion flows emulation is sufficiently complex, and solid fuel (i.e. propellant), which decomposes, in main combustion chamber generates fuel-rich combustion gas, fuel-rich combustion gas and stream
Air stream through main combustion chamber carries out combustion chemistry reaction, and propellant fires face, and nearby the parameters such as speed, density, temperature of air-flow can shadow
It rings combustion face temperature and then influences the generation of combustion gas, same combustion gas will affect the ginseng of air-flow again in turn with air reaction after generating
Number, due to the heat absorption of thermal decomposition and the heat dissipation of mainstream, temperature may eventually reach balance.
Solid fuel ramjet Combustion Flow Field is emulated, difficult point essentially consists in the Mass Sources in simulation propellant combustion face
Item and energy source item, since all source item sizes are all related with mainstream gas, the source item of every bit is all not on combustion face
With, it needs individually to calculate.
Existing solid fuel ramjet Combustion Flow Field emulation mode is shown in Table 1, and the model used includes substantially square
Journey, turbulence model, Propellant decomposition model and gas phase combustion model；Wherein fundamental equation is average Navier-Stokes equation, turbulent flow mould
Type is the RNG with swirling modificationk- ε model, gas-phase combustion model are based on using eddy-dissipation model, Propellant decomposition model
Arrhenius law, fuel-rich gas component use single component, noenergy source item.
The existing emulation mode abridged table of table 1
Its there are the problem of are as follows: firstly, the complicated component of fuel-rich combustion gas, is only not only had no basis with a kind of ingredient, and
Also can be larger with practical situation difference, cause the bigger error of simulation.Secondly, the decomposition of solid propellant is to take away
Heat, if not considering that this portion of energy is lost, it will cause the quantity inaccuracy of quality source item.
Summary of the invention
In view of this, the present invention provides a kind of solid fuel ramjet burning numerical value emulation method, can effectively mention
The simulation accuracy of high solid fuel punching engine Combustion Flow Field.
The solid fuel ramjet Combustion Flow Field numerical value emulation method, fires to solid fuel ramjet
When burning flow field progress numerical simulation, the quality source item and energy source item in propellant combustion face is added；The quality in propellant combustion face
Source item includes the quality source item and oxide mass source item of each ingredient of fuel-rich combustion gas；
The quality source item in propellant combustion face are as follows:
The quality source item of fuel-rich each ingredient of combustion gas are as follows: propellant fires the quality source item in face multiplied by the matter of each ingredient of fuel-rich combustion gas
Measure score；Oxide mass source item are as follows: propellant fires the quality source item in face multiplied by the oxidation material of unit mass propellant expenditure
Amount, oxide mass source item are negative；
Propellant combustion face energy source item be
Wherein: A, EaPre-exponential factor and activation energy respectively；R is universal gas constant, TwThe identification temperature in face is fired for propellant
Degree；ACThe area in face is fired for propellant；ρfFor propellant density, hvFor Propellant decomposition or gasification latent heat,
For propellant burning rate, cfFor propellant specific heat, T0The initial temperature in face is fired for combustion propellant.
It the steps include:
Step 1: carrying out burning calculation of thermodynamics to propellant, obtains the ingredient for being formed by fuel-rich combustion gas and each ingredient
Mass fraction, fuel-rich combustion gas temperature；
Step 2: establishing turbulence model, calculates the turbulent stress of Combustion Flow Field；
Step 3: quality source item, oxide mass source item and the propellant of propellant combustion each ingredient of the fuel-rich combustion gas in face are established
The energy source item energy source item in combustion face；
Step 4: establishing gas-phase combustion model, calculates the gas-phase chemical reaction rate of Combustion Flow Field；
Step 5: by the quality of each parameter and the propellant combustion face established that step 1 is calculated into step 4
Source item and energy source item are as initial parameter substitution gas-phase governing equations group, if the convergence of gas-phase governing equations group, emulates knot
Beam；If gas-phase governing equations group does not restrain, return step one is added after relaxation factor to re-start all initial parameters above-mentioned
It calculates, until gas-phase governing equations group restrains.
Beneficial effect
Fuel-rich gas component and mass fraction are obtained using calculation of thermodynamics in this method, using Arrhenius law meter
Calculate solid propellant decompose fuel-rich combustion gas quality source item and energy source item, with actual combustion process more closely, to
Solid fuel ramjet burning simulation accuracy can be effectively improved.
Detailed description of the invention
Solid fuel ramjet Combustion Flow Field numerical value emulation method flow chart Fig. 1 of the invention.
Specific embodiment
With reference to the accompanying drawings and examples, the present invention is described in further detail.
The present embodiment needle provides a kind of solid fuel ramjet Combustion Flow Field numerical value emulation method, using this method energy
Enough effectively improve solid fuel ramjet burning simulation accuracy.
The numerical value emulation method realizes in FLUENT software, specific steps are as follows:
Step 1: carrying out burning calculation of thermodynamics to propellant (i.e. fuel-rich fuel) using minimum Gibbs free energy method,
Obtain the temperature of the ingredient of fuel-rich combustion gas and the mass fraction of every ingredient, fuel-rich combustion gas；
Step 2: establishing turbulence model, solves turbulent stress；
Using the turbulence model of Realizablek- ε model foundation Combustion Flow Field, the turbulent stress of Combustion Flow Field is solved；
Step 3: fuel-rich combustion gas source item is established:
Fuel-rich combustion gas source item includes: the quality source item and energy source item in propellant combustion face；The wherein quality in propellant combustion face
Source item is gross mass source item, includes each composition quality source item of fuel-rich combustion gas and oxide mass source item.
The fuel-rich ingredient that the fuel-rich gas component for using calculation of thermodynamics to obtain in step 1 is generated as combustion face, combustion
Face passage rate meets Arrhenius law, i.e. propellant burning rateWherein: A, EaBefore referring respectively to
The factor and activation energy, A=8.25 × 102M/s, Ea=133539j/mol, R are universal gas constant, R=8.31451j/
(mol.k), TwThe identification temperature of surface grids unit is fired for nearly propellant.
By AC× r fires the total quality source item of surface grids unit as one, wherein ACIt is fired for combustion surface grids unit in propellant
Area on face, then the total quality source item of the grid cell is on propellant combustion face
It is fuel-rich after the mass fraction for obtaining propellant combustion surface grids unit total quality source item and fuel-rich combustion gas items ingredient
The quality source item of each ingredient of combustion gas is mass fraction of the gross mass source item multiplied by each ingredient；Oxide mass source item is gross mass source
Multiplied by unit mass propellant expenditure oxide mass, symbol is negative.
Existing energy conservation relation is α (T between gas phase and solid phase on gas-solid interface in combustion chamber∞-Tw)=ρfhvr+
ρfrcf(Tw-T0), in which: ρfFor propellant density, hvFor Propellant decomposition or gasification latent heat, cfFor propellant specific heat, T∞It is close
Propellant fires face mainstream temperature, T0The initial temperature of surface grids unit is fired for propellant.Ignore radiation heat transfer, by ρfhvr+ρfrcf
(Tw-T0) as the energy source item for firing surface grids unit, then the energy source item for firing the fuel-rich combustion gas of surface grids unit is
Step 4: establish gas-phase combustion model: gas-phase combustion model uses eddy-dissipation model, passes through eddy-dissipation model
Gas-phase chemical reaction rate is calculated.
Step 5: the model of step 2 to four is calculated by gas-phase governing equations, comprising:
Using the thunder of the governing equation of the transport equation comprising continuity equation, the equation of momentum, energy equation and each component
Promise N-S equation group, frame solves speed, temperature, the density of fluid in Combustion Flow Field as a whole；
The parameter that above-mentioned all models are calculated is brought into gas-phase governing equations group as initial parameter, if gas phase control
Equation group convergence processed, then calculated result is final result, if equation group does not restrain, after adding relaxation factor to all initial parameters
The calculating of return step one repeats step overall process, and move in circles above-mentioned steps, until equation is restrained.
To sum up, this method is capable of the permanent overall process of simulated solid fuel punching engine burning.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (5)
1. a kind of solid fuel ramjet Combustion Flow Field numerical value emulation method, it is characterised in that: to solid fuel punching press
When engine combustion flow field carries out numerical simulation, the quality source item and energy source item in propellant combustion face is added；The propellant combustion
The quality source item in face includes the quality source item and oxide mass source item of each ingredient of fuel-rich combustion gas；
The quality source item in propellant combustion face are as follows:
The quality source item of fuel-rich each ingredient of combustion gas are as follows: propellant fires the quality source item in face multiplied by the quality point of each ingredient of fuel-rich combustion gas
Number；Oxide mass source item are as follows: propellant fires oxide mass of the quality source item in face multiplied by unit mass propellant expenditure, oxygen
Compound quality source item is negative；
Propellant combustion face energy source item be
Wherein: A, EaPre-exponential factor and activation energy respectively；R is universal gas constant, TwThe identification temperature in face is fired for propellant；AC
The area in face is fired for propellant；ρfFor propellant density, hvFor Propellant decomposition or gasification latent heat,To push away
Into agent burn rate, cfFor propellant specific heat, T0The initial temperature in face is fired for combustion propellant.
2. solid fuel ramjet Combustion Flow Field numerical value emulation method as described in claim 1, it is characterised in that:
Step 1: carrying out burning calculation of thermodynamics to propellant, obtains the matter of the ingredient for being formed by fuel-rich combustion gas and each ingredient
Measure the temperature of score, fuel-rich combustion gas；
Step 2: establishing turbulence model, calculates the turbulent stress of Combustion Flow Field；
Step 3: the quality source item, oxide mass source item and propellant combustion face of propellant combustion each ingredient of the fuel-rich combustion gas in face are established
Energy source item energy source item；
Step 4: establishing gas-phase combustion model, calculates the gas-phase chemical reaction rate of Combustion Flow Field；
Step 5: by the quality source item of each parameter and the propellant combustion face established that step 1 is calculated into step 4
Gas-phase governing equations group is substituted into as initial parameter with energy source item, if gas-phase governing equations group restrains, emulation terminates；Such as
Fruit gas-phase governing equations group does not restrain, and adds return step one after relaxation factor to re-start above-mentioned calculating all initial parameters,
Until gas-phase governing equations group restrains.
3. solid fuel ramjet Combustion Flow Field numerical value emulation method as described in claim 1, which is characterized in that described
Calculation of thermodynamics is carried out by minimum Gibbs free energy method in step 1.
4. solid fuel ramjet Combustion Flow Field numerical value emulation method as described in claim 1, which is characterized in that described
Using using Realizable in step 2k-εThe turbulent stress of model calculating Combustion Flow Field.
5. solid fuel ramjet Combustion Flow Field numerical value emulation method as described in claim 1, which is characterized in that described
The gas-phase chemical reaction rate of Combustion Flow Field is calculated in step 4 using eddy-dissipation model.
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| CN111475939A (en) * | 2020-04-03 | 2020-07-31 | 南京信息职业技术学院 | Simulation calculation method for ballistic performance of gas jet impacting liquid water column |
| CN114398844A (en) * | 2022-01-25 | 2022-04-26 | 南京航空航天大学 | Steady-state anti-icing simulation method based on continuous water film flow |
| CN115618171A (en) * | 2022-06-06 | 2023-01-17 | 北京理工大学 | Propellant combustion balance product solving method based on homotopy algorithm |
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