ANSYS ICEM CFD Research Articles

Noble MXene nanofluids' impact on solar collector effectiveness enhancement: a CFD numerical evaluation

The thermal flat plate solar collector (FPSC) is a versatile solar harvesting system that may be integrated into various designs and base fluids. This study presents a novel investigation of using nanofluids to transfer thermal energy in an FPSC system. Using the governing equations in CFD simulations, the performance of an FPSC is studied numerically. The base fluid has been defined as a 60:40 blend of ethylene glycol and water. The effects of three distinct volume fractions of MXene nanofluids in the 0.01–0.1% range on the efficiency are investigated. The numerical findings revealed that employing MXene nanofluid increases outlet temperature efficiency by about 5.83%, 6.06%, and 6.31% when 0.01%, 0.05%, and 0.1% volume fractions of nanofluids are used, respectively. The research aims to create a validated numerical model that can be used to assess the effectiveness of FPSC utilizing ethylene glycol and water or other nanofluids of any mass fraction as a working fluid. To examine the overall effectiveness of the FPSC, a numerical model was created using Solidworks software and ANSYS ICEM CFD. The numerical findings revealed that (i) increasing the proportion of MXene nanofluid in the FPCS enhances efficiency to 0.1% volume fraction, and (ii) MXene nanoparticles may be used in the solar collector to improve efficiency.

Numerical and physical modeling of the aerodynamic process in a direct-flow coil-type boiler using a laboratory stand

The article examines the modes of gas passage through the chimney of a direct-acting steam generator set using a laboratory stand made of a cylindrical coil. The criterion for determining the gas flow regime is a dimensionless quantity called the Reynolds number. The air flow velocities and temperatures were determined experimentally. Based on these results, the Reynolds number was calculated and the flow regimes at each measurement point were determined, and the dependence of the Reynolds number on temperature and velocity was obtained, and the experiment was analyzed. With the help of the ANSYS program, a model of air movement on the stand was built. When deciphering the geometric model, the ANSYS SpaceClaim program was used. The model made it possible to estimate the distribution of the air flow velocity in the boiler model based on experimental values. Further, after constructing a geometric model using the ANSYS Icem CFD program, a dispersion model was cre-ated that showed the temperature distribution of flue gases in the external gas flow of the basic model of a direct-flow steam boiler. The processing of experimental data showed a further prospect of intensification of the heat exchange process in a direct-flow steam boiler of the coil type.

Optimization Turbine Blade Cooling by Applying Jet Impingement Cooling Channels

Abstract The aim of this paper is to optimize turbine blade cooling channels by applying jet impingement Method. The selection of experiment data for NASA 3CX turbine blade, and 3D model using solidworks software and create computational fluid dynamics (CFD) simulations used to model the coolant flow and temperature distribution in the vane, while experimental testing can validate the CFD results and provide additional insights into the cooling system's performance., ANSYS FLUENT code was used as a CFD solver, and ANSYS ICEM-CFD was used for mesh generation. MATLAB code is used for calculation using experiment data and this was helpful for simulations. Heat transfer conjugation analysis bases SST shear stress analyses K-ω turbulent model. The results conclude that providing additional information about the cooling channels and how they differ in the studies being compared. The results demonstrate that the cooling channels' hydraulic diameter decreases by a significant percentage (up to 49.70%–69.55%) as they are drawn to the trailing edge of the blade. This can have a significant impact on the heat transfer coefficients and the performance of the cooling system. The pressure side of the turbine blade is observed to follow the Hylton Model, while the current study predicts a large over-anticipated heat transfer coefficient around the Turbine blade head and on the bulk of the suction side. In terms of average heat transfer coefficient, the two models differ by 23.36%. The authors found that the cooling effectiveness for the Optimized jet impingement model is 0.4892 for whole blade and compared it with the cooling effectiveness for the optimized jet impingement model, which is 0.6936, The results of the comparison between the base model and the optimized jet impingement model suggest that the optimized model has a significantly higher cooling effectiveness. The increase in cooling effectiveness of 29.46% for the whole blade and 28.823% for the trailing edge indicates that the optimized jet impingement design provides improved cooling performance. These results highlight the importance of considering optimized cooling designs for turbine blades to maintain efficient and safe operation.

Wind responses on twin box girder bridge deck using a fluid–structure interaction approach

Wind responses on a twin box girder bridge can be observed by a wind tunnel experiment or by having a full-scale setup if possible. Another possible approach is to go through a numerical approach, which is the CFD simulation of the atmospheric boundary layer surrounding the twin box girder bridge deck. A virtual wind tunnel CFD modelling simulation was carried out on the bridge deck using the Ansys Fluent FSI technique to find out the displacement of the bridge deck. The steady-state simulations were computed. The turbulence model was used to calculate the mean force coefficients as K-ω SST. It has been seen that steady simulation is needed to get the static aerodynamic coefficients right when modelling. Ansys ICEM CFD is used for meshing the bridge deck. In this study, the wind flow behaviour around the structure is analysed at different wind incident angles of − 10°, − 5°, 0°, 5°, and 10°. The pressure variations at different wind directions are mapped in the present work. Responses across and along the wind are also depicted. It was found that the drag coefficient was higher at low angles of attack, whereas the moment and the lift coefficients showed fewer values at large angles.

Numerical investigation on the effect of slit thickness and outlet angle of the bladeless fan for flow optimization using CFD techniques

The effect of outlet thickness and outlet angle of the bladeless fan have been an alysed numerically on the aerodynamic performance of the bladeless fan. Five different aerofoil profiles have been considered for the present work is Eppler 479, Eppler169, Eppler 473, S1046 and S1048. The bladeless fan arrangement has been achieved by converting the aerodynamic models listed above. The ANSYS ICEM CFD 16.0 have been used to discretize the enclosure and bladeless fan through finite volume approach. The mesh model is then imported into ANSYS CFX 16.0 pre-processor for applying the required boundary conditions. The governing equations namely continuity and momentum are used to solve the flow physics through and across the bladeless fan and SST k-? turbulence model has been used to predict the turbulence in the bladeless fan. The effect of outlet thicknesses and outlet angles have been varied for all the five aerofoil configurations mentioned and the volumetric flow at inlet have been adjusted from 5 LPS to 80 LPS. Outlet thickness is varied from 0.8, 1.0, 1.3, 1.5 and 2 mm and the slit angle is varied from 20 degrees to 80 degrees in step of 10 degrees. The results predicted that Eppler 473 aerofoil profile showed better performance when the thickness of slit and outlet angle has been fixed constant as 1 mm and 70 degree respectively. Also, the maximum discharge flow ratio is recorded for an inlet volumetric flow rate of 80 LPS and it is found to be 34.37. The present numerical study substantiated that outlet thickness plays a dominant role on the bladeless fan’s aerodynamic performance compared to outlet angle and aerodynamic shape considered in this numerical analysis. The contours of velocity, streamline and pressure of the bladeless fan have been discussed.

Numerical investigation on the effect of slit thickness and outlet angle of the bladeless fan for flow optimization using CFD techniques

The effect of outlet thickness and outlet angle of the bladeless fan have been an alysed numerically on the aerodynamic performance of the bladeless fan. Five different aerofoil profiles have been considered for the present work is Eppler 479, Eppler169, Eppler 473, S1046 and S1048. The bladeless fan arrangement has been achieved by converting the aerodynamic models listed above. The ANSYS ICEM CFD 16.0 have been used to discretize the enclosure and bladeless fan through finite volume approach. The mesh model is then imported into ANSYS CFX 16.0 pre-processor for applying the required boundary conditions. The governing equations namely continuity and momentum are used to solve the flow physics through and across the bladeless fan and SST k-? turbulence model has been used to predict the turbulence in the bladeless fan. The effect of outlet thicknesses and outlet angles have been varied for all the five aerofoil configurations mentioned and the volumetric flow at inlet have been adjusted from 5 LPS to 80 LPS. Outlet thickness is varied from 0.8, 1.0, 1.3, 1.5 and 2 mm and the slit angle is varied from 20 degrees to 80 degrees in step of 10 degrees. The results predicted that Eppler 473 aerofoil profile showed better performance when the thickness of slit and outlet angle has been fixed constant as 1 mm and 70 degree respectively. Also, the maximum discharge flow ratio is recorded for an inlet volumetric flow rate of 80 LPS and it is found to be 34.37. The present numerical study substantiated that outlet thickness plays a dominant role on the bladeless fan’s aerodynamic performance compared to outlet angle and aerodynamic shape considered in this numerical analysis. The contours of velocity, streamline and pressure of the bladeless fan have been discussed.

Intensification of heat-exchange of a direct-flow steam boiler of a coil type based on an educational laboratory stand

In the work under consideration, using an experimental stand formed by a cylindrical coil, the modes of air movement through the flue of a ramjet steam boiler were investigated. Experimental studies have revealed shortcomings in the operation of a direct-flow steam boiler and proposed ways to increase heat transfer in a steam boiler by turbulizing the gas-air flow in the convective part of the boiler flue. The Ansys programmable engineering environment was used to simulate the heat exchange between waste gases and water in the heat exchanger. The Ansys SpaceClaim program was used to design the geometric model. Finite element grid was created using the Ansys Icem CFD program. In the process of creation, materials were selected and designated for each part of the model, water and steam temperatures inside the heat exchanger, exhaust gas temperature, boundary conditions and heat exchange conditions between them were also set. After entering all the parameters the model calculations were carried out and the results were presented in the form of a temperature distribution diagram. In conclusion, a variant of further research of aerodynamic processes in a ramjet steam boiler and a demonstration of the selected option were presented.

Numerical investigation on the performance and combustion characteristics of a cavity based scramjet combustor with novel strut injectors

A three-dimensional numerical investigation has been carried out on the performance and combustion characteristics of a scramjet combustor with and without cavity for various strut injector configurations. The geometrical shape of the injectors considered for the present study are circle, square and rectangle. The numerical model of scramjet combustor has been discretized hexahedrally through finite volume approach using ANSYS ICEMCFD 18.0 and the necessary boundary conditions are specified in ANSYS Fluent 2021 CFD code. The three-dimensional fluid flow variations through a scramjet engine with strut-based injectors and cavity have been analyzed by solving the corresponding governing equations namely continuity, momentum (Navier-Stokes) equation and energy transport equation for the non-reacting flows. In addition to the above equations species transport equation is also solved for the reacting flows. The turbulence induced in the fluid is modelled using standard K-ε turbulence model. The effect of injector shapes, mixing length, combustion efficiency and total pressure loss have been numerically simulated and plotted with and without cavity of a scramjet combustor. The results from the study predicted that circular injector with cavity showed better mixing characteristics and combustion characteristics compared to the rectangle and square model. The total pressure loss of circular injector with cavity is 5.4% higher than the other models investigated, still it is preferred because of high combustion efficiency attained with shorter span of combustor length.

Numerical Investigation on the Effect of Geometric Shape and Outlet Angle of a Bladeless Fan for Flow Optimization using CFD Techniques

A three dimensional numerical study has been carried out to investigate the effect of various geometric shapes and slit angle on performance of the bladeless fan for various aerodynamic profiles. Aerofoils considered for the present study are E169, E473 and E479 which are then reformed into a typical bladeless fan arrangement. The numerical model of bladeless fan encompassing the outer domain is discretized tetrahedrally through finite volume approach using ANSYS ICEMCFD 20.0 and the necessary boundary conditions are specified in the ANSYS Fluent 20.0 pre-processor. The three dimensional fluid flow variations through and across the aerofoil have been simulated by solving the appropriate governing equations namely continuity and Reynolds Averaged Navier-Stokes equations (RANS). The turbulence induced in the fluid is modelled using SST k-ωmode of closure. Numerically predicted results of lift, drag and streamwise velocity decay along the jet centreline of a cylindrical channel are compared with literature and a very close agreement exists between the two. Upon validation, geometric shapes - circular and square cross section with aspect ratios of 1, 1,5 and 2 and slit angles of 20, 40, 60 and 80 degree for all the above three aerofoil configurations are analysed numerically for various inlet Reynolds number. Pressure, velocity contours and stream line across the bladeless fan are presented and discussed. From the study it is observed that Eppler 473 aerofoil profile with slit thickness of 1 mm and slit angle of 80° provided the maximum discharge ratio of 34.17 for an inlet mass flow rate of 80 LPS.

Art Design of Ceramic Sculpture Based on 3D Printing Technology and Electrochemistry

In order to solve the artistic design of ceramic sculpture, we proposed a method based on 3D printing technology for ceramic sculpture. First, using ANSYS ICEMCFD simulation software, we verified the effectiveness of the ceramic sculpture design method based on 3D printing technology in this study. Second, the design method of this study is recorded as the experimental group A. The two traditional design methods are recorded as experimental group B and experimental group C, respectively. Finally, we determined and compared the effect, size error, and precision error of the three groups of design methods to design the product. Ceramic sculptures are designed by proving the design method, high pattern definition, and small surface precision error. In the three directions of x-axis, y-axis, and z-axis, the relative size error generated is small, and the error is maintained below 1.0, and the effect of the finished product is consistent. So, the surface roughness of the ceramic sculpture designed this time is low, which will not affect the dimensional accuracy of the ceramic sculpture.

The impact of a passive wall combining natural ventilation and evaporative cooling on schools’ thermal conditions in a hot climate

Students' performance is negatively influenced by poor indoor environments. In Sudan that is characterised by extreme climate, providing comfortable classrooms is required to improve the educational system that suffers from restricted budgets. To address this issue, the local government in Khartoum, the capital city of Sudan, and the Ministry of Education released a joint project to construct new schools' buildings following one of two unified prototype models. This paper evaluates the impact of a new passive wall system that combines natural ventilation and evaporative cooling on the classrooms' thermal conditions. The wall consists of two brick layers that accommodate a wet porous ceramic layer, and it has two configurations. In the first configuration, the exhausted air is circulated to the system to cool it before ejecting it into the classroom. In the second configuration, the exhausted air is dissipated from the classroom through an outlet located at a wall opposite to the wall that integrates the system. The effectiveness of the system was evaluated via assessing the classrooms’ conditions before and after activating it using EDSL TAS and ANSYS ICEM CFD programmes. The findings revealed considerable reductions in indoor air temperatures from 30.3–44.8 °C before activating the system to 18.9–26.5 °C and 21.3–23.8 °C after activating the system in the first and second configurations, respectively, which concludes the system effectiveness. The wall is environmentally clean as its operation barely consumes active energy, which makes it attractive considering the limited budget allocated for the education sector in Sudan.

ОПТИМІЗАЦІЯ НОСОВОЇ ЧАСТИНИ ФЮЗЕЛЯЖУ З ТОЧКИ ЗОРУ АЕРОДИНАМІКИ ЛІТАКА

The paper represents the analysis intended to optimize the fuselage nose section with regard to aircraft aerodynamics in the process of development of an unmanned transport aircraft (UTA). The article deals with provisions of high aerodynamic efficiency that cannot be achieved without proper selection of the shape and optimal fuselage parameters that determine mutual interference of aircraft components and units. When analyzing the flow improvement around the fuselage nose in flight, three fuselage versions were considered listed further: 1) a prototype for testing automatic flight control systems with participation of pilots; 2) a nose symmetrical relative to the fuselage rocket type cylinder axis; 3) a supposedly optimal variant based on the results of previous calculations. The aerodynamic characteristics of 3D fuselage models for positive integer Reynolds numbers (full-scale model) were calculated using the ANSYS software package. Three computational grids were built for these models in ANSYS ICEM CFD. The given version of the fuselage nose section intended for testing automatic flight control systems with participation of pilots initially has the greatest resistance among the considered variants. That is, first variant of the fuselage nose gives substantial braking zone as well as significant flow acceleration zone exists in place where fuselage is transformed into cylindrical part. The variant with the nose section symmetrical relative to the rocket type cylinder axis has smaller braking zone and less dispersed flow in place where fuselage is transformed into cylindrical part and, therefore, it has lower resistance in comparison with the first version. The fuselage execution developed on the basis of the results of previous calculations, despite the extensive acceleration zone at the junction of the nose to the cylindrical part, has shown the least resistance, respectively, and is the best of the considered variants. This is also confirmed by a comparison of streamlines over the nose surface. The streamlines are given for calculations at angle of attack of 8°; at this angle of attack, the difference in the coefficient Cx is clearly visible.

CFD simulation of the wind field around pyramidal roofed single-story buildings

For the structural safety to counter the wind load, the roof shape and the roof slope both the constraints play an important role. The present study demonstrates the pressure distribution on the pyramidal roofs of a pentagonal and hexagonal plan low-rise single-story building due to the wind load through CFD simulation. This type of roofed building may be considered as one of the cyclone shelters as it is shown by post-disaster studies that pyramidal roof is found better than other roof shapes to resist the wind load. The modeling of the building and the meshing of the models have been carried out in ANSYS ICEM CFD, while the simulation process has been performed in ANSYS Fluent. To obtain the results, ANSYS CFD-Post has been utilized. For the simulation of the turbulent wind flow, a realizable k–e turbulent model is used in the present study. In the current study, ten different building models (five with pentagonal plan and five with hexagonal plan) are generated having roof angles 20°, 25°, 30°, 35° and 40°, and all are simulated for 0°–45° wind direction @15° interval. The pressure coefficient contours for different wind directions for varying roof slopes are mapped in the present study. Results show that the hexagonal pyramidal roof surface building has low-pressure coefficients and better chances of survival than the pentagonal pyramidal roof surface building.

Conceptual Design and Hydrodynamic Research on Unmanned Aquatic Vehicle

Autonomous Underwater Vehicles (AUVs) are one of the significant types of aircraft, which are traveled in submarine by the pre-programmed control process. At the present time AUV is being projected for many serious applications together with fault exposure on the dam, tragedy monitoring, naval supervision, and fisheries safety. Interest in AUVs for ocean investigation and mapping, inspection, and forecasting have emerged progressively, in which the AUVs design methods are implemented in submarine are regularly multi-rotor arrangement AUVs. In submerged applications, multi-rotor based AUVs are low proficient in terms maneuvering practicability, existence, as a result, the designer must make available an AUV, which has the high lifetime, high efficient in devise, more secure on-flight and low continuation cost in order to endure at the decisive environment. In this article proposed a unique AUV, called Unmanned Aquatic Vehicle (UAV) inspired by the approach of flying fish, this can able to maneuver in underwater with high competence, in which estimation of resourceful have been derived based on theoretical design, manipulation realization process, communication, a existence of a UAV. Advanced numerical imitation have the ability to solve decisive problem so in this paper used CFD, in which, the ordered grid of the computational models for dissimilar types of UAVs is generated by Ansys ICEM CFD 16.2. This discretized model represents as the imitation of UAV, which is used to forecast the flow performance of the orientation module, and examine the hydrodynamic belongings on its sub-components. In this article, ANSYS-FLUENT 16.2 software is used as arithmetical solver tool, which is a influential tool for solving troubles concerning fluid mechanics. Results of the velocity, pressure allocation, and drag coefficient are analyzed. The characteristics of the drag, lift, pitching moment partial by the distance to the sea underneath and the attack angle are studied, which provided the path for UAV intend optimization

Numerical Examination on the Effect of Internal Fluid Presssure on the Hydrodynamic Response of a Marine Riser

Marine risers are long slender structures which links the floating vessel on the sea surface and its manifold on the sea bottom. It acts as a transportation means for the hydrocarbon resources underneath the sea bed. A riser mainly undergoes hydrodynamic loading which leads to Vortex induced vibrations (VIV) or Flow induced vibrations. These are motions induced on bodies interacting with an external fluid flow producing periodic irregularities on the flow which leads to fatigue damage of offshore oil exploration and production risers. Therefore, suppressing of VIV by providing helical strakes, fairings etc. is necessary in order to reduce the fatigue damage of risers due to hydrodynamic loading. The present paper deals with the numerical study on the response of a marine riserdue to the effect of internalfluid pressure. The initial work is carried out in ANSYS ICEM CFD software. The CFD solution after analysis is obtained from ANSYS FLUENT. The hydrodynamic effects like lift and drag forces along with motion responses is obtained.

Calculation and experimental studies of coolant hydrodynamics in the inlet region of fuel assembly

An innovative core with an increased energy resource was used when designing RITM-200 reactor unit. The paper presents the results of experimental and numerical simulation of hydrodynamic processes occurring in the inlet region of the RITM reactor fuel assembly model. Computational mesh of fuel assembly, containing ∼ 22 million elements was created using Ansys ICEM CFD. The values of relative axial velocities in several cross sections at the inlet to the bundle of fuel elements are obtained. At the inlet to the fuel rods bundle the velocity field is not uniform, due to the complex geometry of the fuel assembly. The obtained results of CFD-simulation can be used to determine the input boundary conditions for subchannel programs of the core thermal-hydraulic analysis. This allows taking into account uneven flow rate distribution in subchannels due to the complex geometry of the fuel assembly inlet region.

Simulation and experiment on pressure field characteristics of hydrostatic hydrodynamic hybrid thrust bearings

PurposeThis paper aims to improve the bearing capacity of hydrostatic thrust bearing under working conditions of high speed and heavy load; a new wedge-shaped structure opened on an edge of oil seal is put forward, the loss and insufficiency for hydrostatic bearing capacity are made up by using dynamic pressure, and then, hydrostatic hydrodynamic lubrication is realized.Design/methodology/approachOil film three-dimensional models of unidirectional and bi-directional hydrostatic hydrodynamic oil pad are established by using UG. The oil film pressure fields of two kinds of oil pad are simulated by using ANSYS ICEM CFD and ANSYS CFX; the pressure fields distribution characteristics are obtained, and the effects of workbench rotary speed and bearing weight on pressure field are analyzed. Also, the experimental verification is made.FindingsThe results demonstrate that with an increase in workbench rotary speed, the oil film pressure of two kinds of hybrid oil pad increases gradually, and the maximum pressure of the bi-directional one accounts for 95 per cent of the unidirectional one when the load is constant. With an increase in load, the oil film pressure of two kinds of hybrid oil pad increases gradually, the difference between them is 9.4 per cent under the condition of load of 25 t when the rotary speed is constant.Originality/valueThe paper can provide theoretical basis for a structure design of hybrid thrust bearing under different rotary speed and load conditions, and compensate the shortage of static pressure-bearing capacity by using dynamic pressure, improve the stability of vertical CNC machining equipment.

Micro TJE centrifugal compressor performance prediction Tamer S.

In this paper, the performance of a small centrifugal compressor of an UAV at design and off-design operational conditions is estimated by way of advanced commercial CFD code, ANSYS-CFX-16. Then, the gained performance is compared with published predicted performance using approximate method[1, 2]. The engine used is JetCat P200-sx, which is a single spool turbojet. Considered off-design regimes include centrifugal compressor operations at 73%, 80%, 85%, 90%, 100% and 103% of the design point rotational speed. Commercial CFD code CFX-16, is used for compressor performance prediction at design and off- design operating conditions. The computational grid is created using Turbo-Grid for compressor parts impeller and vanned diffuser. While for both intake device and vaneless diffuser an unstructured tetrahedral mesh with prism layers along the wall surfaces using ANSYS-ICEM CFD mesh is used to resolve the near-wall boundary layer. To gain a reduction in the computational analysis cost, only one passage is considered as a portion of the computational domain and the model is simulated as a steady state problem. Finally, to detect the surge point at each rotational speed the unsteady simulation on performance predictions of centrifugal compressor is investigated. It is a common practice to use compressor characteristics available in graphical form. These plots can be transformed into empirical equations that can be used in automatic calculation. Such approach was done to predict the same compressor performance[13]. The CFD detailed compressor performance is compared with the mentioned published one. The numerical CFD results illustrate good agreement with the analytical model.

Experimental studies and numerical simulation of coolant hydrodynamics in the inlet area of nuclear reactor fuel assembly

An innovative core with an increased energy resource was used when designing RITM-200 reactor unit. The paper presents the results of experimental and numerical simulation of hydrodynamic processes occurring in the inlet region of the RITM reactor fuel assembly model. Computational mesh of fuel assembly, containing ~ 22 million elements was created using Ansys ICEM CFD. The values of relative axial velocities in several cross sections at the inlet to the bundle of fuel elements are obtained. At the inlet to the fuel rods bundle the velocity field is not uniform, due to the complex geometry of the fuel assembly. The obtained results of CFD-simulation can be used to determine the input boundary conditions for subchannel programs of the core thermal-hydraulic analysis. This allows taking into account uneven flow rate distribution in subchannels due to the complex geometry of the fuel assembly inlet region.

The calculation of the asymmetrical three-dimensional flow of the combustion products in a compact size SRM

The article is devoted to the problem of calculating the complex flow of combustion products in the solid propellant combustion chamber. The paper presents a calculation of the combustion products flow for three instants of time using the example of an engine for removing of the rocket head fairing. Due to the fact that the nozzle block of the engine is divided into four nozzles, one of which has a larger diameter of the critical section, the gas flow along the internal free volume of the engine is asymmetrical. ANSYS (CFX) software package is used to solve this problem.The article gives a brief description of the engine design and the charge of solid fuel for which calculations are performed. To get out calculations, 3D models of internal free volumes created in Autodesk Inventor are used. Grid is generated in the standard ANSYS ICEM CFD package, which is integrated into the ANSYS (CFX) working environment. Calculation results are given after describing the boundary conditions. The results are presented as a velocity distribution in two mutually perpendicular planes.The proposed methodology for the gas-dynamic calculation of SRM allowed obtaining calculations of higher accuracy in comparison with engineering methods. The approach to the solution of the problem proposed in this article can be widely used not only in the design of drive engines, but other SRMs for various purposes.A