CN111079235B - Method for simulating and rapidly converging internal flow field of solid rocket engine - Google Patents
Method for simulating and rapidly converging internal flow field of solid rocket engine Download PDFInfo
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Abstract
The invention relates to the technical research field of solid rocket engines, in particular to a method for rapidly converging simulation of an internal flow field of a solid rocket engine. The method comprises the steps of 1) guiding a grid model of the solid rocket engine into Fluent software, 2) initializing a flow field in the solid rocket engine, 3) initializing an internal flow field, and 4) calculating the flow field in the solid rocket engine. The method realizes effective regulation and control of the simulation process of the flow field in the solid rocket engine, accelerates the convergence process of the simulation calculation process of the flow field in the solid rocket engine, overcomes the problems of difficult calculation convergence, long calculation period, low efficiency and the like of the conventional calculation method, can obviously improve the simulation efficiency of the flow field in the solid rocket engine, greatly reduces the calculation period and saves the cost.
Description
Technical Field
The invention relates to the technical research field of solid rocket engines, in particular to a method for rapidly converging simulation of an internal flow field of a solid rocket engine.
Background
As a power system of the solid missile, a solid rocket engine is the heart of the solid missile, and the performance and the reliability of the solid rocket engine directly determine the performance and the working reliability of the solid missile. The solid rocket engine internal flow field simulation technology provides technical guarantee for the performance and reliability of the solid rocket engine, and is an essential part in the design and optimization process of the solid rocket engine. The solid rocket engine is a high-temperature high-pressure container, and the flowing process of fuel gas in the solid rocket engine goes from subsonic speed to sonic speed and then to supersonic speed, so that the simulation calculation process of the flow field in the solid rocket engine is not easy to converge, the period of the calculation process of the flow field in the solid rocket engine is longer, and the efficiency is lower.
The existing solid rocket engine internal flow field simulation technology generally uses commercial CFD software to perform direct numerical simulation on a simulation model, and the speed of flow field simulation convergence is improved mainly by simplifying a geometric model and adjusting and optimizing a grid model. The method mainly has the following defects: 1) Because the solid rocket engine is a high-temperature high-pressure container, the flowing process of fuel gas in the solid rocket engine goes from subsonic speed to sonic speed and then to supersonic speed, the calculation process is easy to disperse in the process of performing simulation calculation on the flow field in the solid rocket engine by adopting the prior art, so that the simulation work of the flow field in the solid rocket engine is repeated continuously, the research and development progress of the engine is directly influenced, the research and development efficiency of the engine is reduced, the convergence of the calculation result is higher while the flow field of the solid rocket engine is very difficult to converge, the error of the calculation result is larger, and the performance analysis and the optimization design of the solid rocket engine are seriously influenced; 2) In the prior art, the geometric model and the grid model need to be continuously simplified and divided again in the adjustment process, but as the powder column profiles are mostly designed into irregular profiles such as star-shaped or wing column-shaped profiles, more time is consumed in the optimization process of the grid model, and the development period and the efficiency of the solid rocket engine are seriously influenced. According to the working characteristics of the solid rocket engine and the requirements of the solid rocket engine on rapid design and optimization, the rapid convergence of the simulation calculation of the flow field in the solid rocket engine is realized by adjusting control parameters, time step length, iteration step number in each time step and the like in the calculation process of the flow field in the solid rocket engine according to a mature engineering experience method, the convergence speed and calculation efficiency of the simulation calculation of the flow field in the solid rocket engine are greatly improved, the technical innovation of the simulation calculation method of the flow field in the solid rocket engine is realized, and the method has important significance for improving the design and optimization level of the solid rocket engine.
Disclosure of Invention
Technical problem to be solved by the invention
The invention provides a method for rapidly converging flow field simulation in a solid rocket engine, which aims to solve the problems that the convergence residual of a calculation result is high, the error of the calculation result is large, and the performance analysis and the optimization design of the solid rocket engine are seriously influenced.
The technical scheme adopted by the invention
The invention provides a method for rapidly converging flow field simulation in a solid rocket engine, which comprises the following steps:
1) Introducing a grid model of the solid rocket engine into Fluent software, and conventionally setting an energy equation, a turbulence model, parameters of a flowing medium material, boundary conditions and the like involved in the calculation process;
2) Initializing and setting an internal flow field of the solid rocket engine, keeping solving control parameters as default values, and directly performing internal flow field initialization setting on the basis, wherein the initialization method preferentially selects an outlet boundary condition to perform internal flow field initialization;
3) Initializing an internal flow field, adjusting solving parameters, adjusting the solving parameters to be 1/100000 of default datse:Sup>A, and setting se:Sup>A turbulence model as an S-A model;
4) Calculating the internal flow field of the solid rocket engine: when the calculation process is the calculation of a steady-state internal flow field, calculating a certain number of steps, adjusting a solving parameter, adjusting the solving parameter to be 10 times of the size of the existing data, repeating iterative solution until the solving parameter is default data, returning to the previous iterative process if the solving parameter diverges, adjusting a turbulence model after the residual curve is stable, temporarily not adjusting the solving parameter, performing the next step of solving calculation until the residual curve is stable, repeating the iterative process until the turbulence model is the optimal turbulence model, then adjusting the solving parameter until the solving parameter is the default data, and obtaining a final calculation result at the moment; when the calculation process is transient internal flow field calculation, the calculation step length is preferably selected to be 1e-6, the iteration step number calculated in each time step length is 1000, the solving parameters and the turbulence model are adjusted according to the method for calculating the steady-state internal flow field, and when the solving parameters are default values and the turbulence model is an ideal turbulence model, the time step length and the iteration step number calculated in the time step length are adjusted.
Further, the specific transient internal flow field calculation method comprises the following steps: when the time step is 1e-6, the solving parameter is the default value and the turbulence model is the ideal turbulence model, the time step is adjusted to be 2 times of the original value, the iteration step number in each time step can be properly adjusted under the condition of the time step until the residual error curve tends to be in a stable state, and the adjustment is repeated, so that the calculated time step can be increased, and the convergence of the flow field calculation process in the solid rocket engine transient state is accelerated.
The beneficial effects obtained
The method realizes effective regulation and control of the simulation process of the flow field in the solid rocket engine, accelerates convergence of the simulation calculation process of the flow field in the solid rocket engine, overcomes the problems of difficult convergence, long calculation period, low efficiency and the like of the conventional calculation method, can obviously improve the simulation efficiency of the flow field in the solid rocket engine, greatly reduces the calculation period and saves the cost.
Drawings
FIG. 1: the solid rocket engine model is guided into a Fluent software back operation interface;
FIG. 2: a technical scheme of a method for rapidly converging flow field simulation in a solid rocket engine.
Detailed Description
The following detailed description is made with reference to the accompanying drawings and specific embodiments:
fig. 1 shows an operation interface displayed after a solid rocket engine model is introduced into commercial CFD-Fluent software. After the grid model of the solid rocket engine is introduced into Fluent software, the energy equations, turbulence models, flow medium material parameters, boundary conditions, etc. involved in the calculation process are routinely set in the interface shown in fig. 1.
After above-mentioned setting is accomplished, the interior flow field simulation of solid rocket engine technical scheme of the method of converging fast is seen in fig. 2, through the utility model discloses can realize accelerating the purpose that the interior flow field simulation of solid rocket engine calculated the convergence:
and initializing the flow field in the solid rocket engine. In the step, the solving control parameter is kept as a default value, the initialization setting of the internal flow field is directly carried out on the basis, and the initialization method preferentially selects the adoption of outlet boundary conditions to carry out the initialization of the internal flow field.
After the internal flow field is initialized, solving parameters are adjusted to be 1/100000 of default datse:Sup>A, and the turbulence model is an S-A model.
Starting calculation of the flow field in the solid rocket engine:
(1) When the calculation process is steady-state internal flow field calculation, after the calculation is started, when a certain number of steps are calculated and the residual curve is close to stability, adjusting the solving parameters to be 10 times of the existing data, and repeating iterative solving in the way until the solving parameters are default data; if the situation that the residual error curve diverges occurs in the solving process, returning to the previous iteration process, after the residual error curve is stable in the process, temporarily not adjusting solving parameters, adjusting the turbulence model, carrying out next solving calculation until the residual error curve is stable, repeating the steps until the turbulence model is the optimal turbulence model, and then adjusting the solving parameters until the solving parameters are default data. The calculation result obtained at this time is the final calculation result.
(2) When the calculation process is transient internal flow field calculation, after calculation is started, the calculation step length is preferably selected to be 1e-6, and the iteration step number calculated in each time step length is 1000. Under the condition, the solution parameters and the turbulence model are adjusted according to the method of steady-state internal flow field calculation. When the solving parameter is a default value and the turbulence model is an ideal turbulence model, adjusting the time step length and the iteration step number calculated in the time step length, and the specific method comprises the following steps: when the time step is 1e-6, the solving parameter is the default value and the turbulence model is the ideal turbulence model, the time step is adjusted to be 2 times of the original value, the iteration step number in each time step can be properly adjusted under the condition of the time step until the residual error curve tends to be in a stable state, and the adjustment is repeated, so that the calculated time step can be increased, and the convergence of the flow field calculation process in the solid rocket engine transient state is accelerated.
Claims (2)
1. A method for simulating rapid convergence of a flow field in a solid rocket engine is characterized by comprising the following steps:
1) Introducing a grid model of the solid rocket engine into Fluent software, and conventionally setting an energy equation, a turbulence model, flow medium material parameters and boundary conditions involved in the calculation process;
2) Initializing and setting a flow field of the solid rocket engine, keeping solution control parameters as default values, and directly initializing and setting the flow field on the basis, wherein the initialization method preferentially selects an outlet boundary condition to initialize the flow field;
3) Initializing se:Sup>A flow field, adjusting solving parameters, and adjusting the solving parameters to be 1/100000 of default datse:Sup>A, wherein se:Sup>A turbulence model is an S-A model;
4) Calculating the internal flow field of the solid rocket engine, when the calculation process is the steady-state internal flow field calculation, calculating a certain number of steps, adjusting the solution parameters to be 10 times of the existing data, repeatedly and iteratively solving the calculation adjustment and solution process until the solution parameters are default data, returning to the previous iteration process if the dispersion condition of the residual curve occurs in the solution process, temporarily adjusting the solution parameters after the residual curve is stable in the process, adjusting the turbulence model until the residual curve is stable, repeating the steps until the turbulence model is the optimal turbulence model, then adjusting the solution parameters until the solution parameters are default data, and obtaining the final calculation result at the moment.
2. The method for rapid convergence of flow field simulation in a solid rocket engine according to claim 1, wherein the specific method for calculating the internal flow field is as follows:
when the calculation process is transient internal flow field calculation, the calculation step length is preferably selected to be 1e-6, the iteration step number calculated in each time step length is 1000, under the condition, the solving parameters and the turbulence model are adjusted according to the method for calculating the steady-state internal flow field, and when the solving parameters are default values and the turbulence model is an ideal turbulence model, the time step length and the iteration step number calculated in the time step length are adjusted; when the time step is 1e-6, the solving parameter is the default value and the turbulence model is the ideal turbulence model, the time step is adjusted to be 2 times of the original value, the iteration step number in each time step can be properly adjusted under the condition of the time step until the residual error curve tends to be in a stable state, and the adjustment is repeated, so that the calculated time step can be increased, and the convergence of the flow field calculation process in the solid rocket engine transient state is accelerated.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107480335A (en) * | 2017-07-12 | 2017-12-15 | 南京航空航天大学 | A kind of hypersonic vehicle Iterative Design method |
| CN109255171A (en) * | 2018-08-29 | 2019-01-22 | 深圳清沣溪科技有限公司 | A kind of automatic judgement convergent method of numerical simulation calculation |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104516998A (en) * | 2013-10-08 | 2015-04-15 | 天津大学 | Analogue method based on double wall surface boundary conditions for JP5000 high velocity oxygen flame spray |
| CN106326541B (en) * | 2016-08-19 | 2020-05-15 | 广东海洋大学 | Dynamic grid boundary updating calculation method |
| CN106484980B (en) * | 2016-09-29 | 2019-08-13 | 中国人民解放军军械工程学院 | A kind of fixed rudder two dimension Correction Projectiles aerodynamic coefficient method |
| US10876732B2 (en) * | 2016-10-19 | 2020-12-29 | Gloyer-Taylor Laboratories Llc | Scalable acoustically-stable combustion chamber and design methods |
| CN106777457B (en) * | 2016-11-10 | 2022-10-18 | 内蒙动力机械研究所 | Reliability assessment software system for solid engine grain structure |
| CN107688705A (en) * | 2017-08-25 | 2018-02-13 | 哈尔滨工业大学 | The axial induced velocity computational methods in the rotor system induction flow field based on finite state |
| CN107844673A (en) * | 2017-12-14 | 2018-03-27 | 中国航发沈阳发动机研究所 | A kind of aero-engine complete machine three-dimensional pneumatic emulation mode |
| CN109408915B (en) * | 2018-10-11 | 2022-10-14 | 北京动力机械研究所 | Simulation method for combustion flow field of solid rocket scramjet engine |
| CN109657401B (en) * | 2019-01-03 | 2022-12-23 | 北京动力机械研究所 | Numerical simulation method for combustion flow field of solid fuel ramjet engine |
| CN110489777A (en) * | 2019-07-02 | 2019-11-22 | 哈尔滨理工大学 | A kind of array hole electric spark ultrasonic Compound Machining flow field simulation method |
-
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107480335A (en) * | 2017-07-12 | 2017-12-15 | 南京航空航天大学 | A kind of hypersonic vehicle Iterative Design method |
| CN109255171A (en) * | 2018-08-29 | 2019-01-22 | 深圳清沣溪科技有限公司 | A kind of automatic judgement convergent method of numerical simulation calculation |
Non-Patent Citations (1)
| Title |
|---|
| 王振国,吴晋湘,庄逢辰.计算流体动力学在液体火箭发动机中的应用.《国防科技大学学报》.1994,1-7. * |
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