Item description

Simulation of combustion in a combustion chamber using the Species Transport model

The movement of objects in the air or other fluids has always been considered. Many new designs on moving objects in the air are made according to the desired fluid characteristics, as well as the type of movement and, of course, the specific shape of the object being sought. Given the advancement of science in simulating such phenomena, engineers have always tried to make the best possible design in this field. Many of the changes that have taken place in the appearance of such objects that move inside the fluid have been due to this issue. There are many examples in this area that have made significant changes. The body of the planes, the type of fins and their appearance, the body shape of the car, the body of ships and submarines and … There are few examples in this regard.

The largest automotive companies have also used this science to maximize the aerodynamic efficiency of their products. One of the successful companies in this field is the Audi Automobile Company.

In this analysis, the simulation of combustion in a combustion chamber is simulated and analyzed using the Species Transport model by ANSYS Fluent software.

Geometry and grid

The geometry required for this analysis has been generated by ANSYS Design Modeler software. Meshing process for this analysis is also provided by ANSYS Meshing software. The grid type used in this analysis is unstructured and the total number of cells produced for this geometry is 694928 cells.

Model

In this analysis, the K-epsilon Realizable turbulence viscosity model is used to check the fluid flow. The standard wall function is used near the wall. In this analysis, the Species Transport model for methane gas has been used to simulate combustion in the compartment. In this analysis, two-stage combustion was used. It should also be noted that combustion is considered volumetric. NOX products are also included.

Boundary conditions

The flow input for this geometry for the air inlet is considered as Mass Flow Inlet at a rate of 0.02 kg/s and for fuel inlet the Mass Flow Inlet is at a rate of 0.0006 kg/s. The outlet flow for the solution range is also considered as a Pressure Outlet and is equal to 0 Gauge Pa. The walls of the body of the combustion chamber are defined as walls and are used for the adiabatic temperature limit.

Discretization of equations

Depending on the type of flow around this object, the Coupled algorithm is used to discretize the coupled velocity and pressure equations. The momentum equation has been discretized in the Second Order Upwind.

The results are presented as velocity and pressure contours as well as streamlines.

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