Item description

Simulation of the combustion chamber in gas turbine engine

Over the past twenty years, there has been a significant increase in the use of gas turbines in various industries, power plants, planes, and rockets. The efficiency of turbines directly affects fuel consumption and dramatically reduces cost efficiency. The gas turbine consists of several parts, including air inlet, a compressor for increasing air pressure, a combustion chamber in which the combustion of fuel and air combustion takes place, the turbine for extraction of energy and, finally, gas outlet. To increase the efficiency of gas turbines, we need to examine each component and parts. Combustion in the chamber is one of the most important parts of the gas turbine. The flow inside the combustion chamber also involves chemical reactions. Therefore, the design of the combustion chamber is very important. The computational fluid dynamics analysis of the combustion chamber is essential and helps to better understand the combustion and flow patterns. The results of simulations will reduce the cost of construction and, by increasing productivity, we can contribute to a more healthy environment.

The simulation of the combustion and combustion chamber in a gas turbine engine was carried out in this project. This combustion chamber is related to the Siemens V94.2 gas turbine with a nominal capacity of 159 megawatts and an efficiency of 34.9%, one of which is a heavy-duty gas turbine, which is widely used in gas plants and the combined cycle of the country to move. Power generators are used. The turbine in Iran is manufactured by the engineering and manufacturing turbine company MAPNA (Tuga), licensed by Siemens Germany. The fuel used is liquid fuels, diesel and heavy fuel oil and gas fuels with a variety of thermal values, especially natural gas.

In this analysis, it has been attempted to simulate and analyze the combustion in the combustion chamber by Ansys Fluent software.

Geometry and Mesh

The geometry required for this analysis includes a combustion chamber, the geometry of which is entirely designed by Gambit, and the networking required by the same software for this geometry. The networking generated for this geometry is unorganized and the total number of cells created for this geometry is 3488057 cells.


To analyze the combustion process, the Species Transport model was used as a response. This model uses a mixture of gasoline and air for combustion. To analyze the turbulence of the flow generated by the interaction of this two-phase current, the K-epsilon standard turbulence viscosity model is used. The standard wall function is used near the wall. The energy equation is also activated.

The materials used in this analysis also include oxygen, nitrogen, water vapor and so on which is defined in the Material section for this analysis.

Boundary conditions

The current input for this analysis is defined as Velocity Inlet for input air and is equal to 4m / s. The air temperature is also considered to be 300K. For input fuel flow, the Velocity Inlet boundary condition is used at 3m / s at 300K. In this analysis, to reduce the computation time instead of solving the process across the domain, the process is solved only in part of the domain. For this purpose, the Periodic boundary condition is used in the lateral boundaries. The output of the flow range is also considered as a pressure outlet for the combustion mixture.

Discretization of equations

To solve the equations, the Coupled algorithm is used in this analysis. Also, a pressure-based solution for flow resolution is used. The First Order Upwind method is used to discriminate equations. It is used only for the discretization of the second-order pressure equations.

In the end, the results are shown as cantors of velocity, pressure and temperature contours.

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