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The Design – Axial Turbo Jet Engine Simulation | ANSYS Fluent

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A turbojet is an airbreathing jet engine, typically used in aircraft. It consists of a gas turbine with a propelling nozzle. The gas turbine has an air inlet, a compressor, a combustion chamber, and a turbine (that drives the compressor). The compressed air from the compressor is heated by burning fuel in the combustion chamber and then allowed to expand through the turbine. The turbine exhaust is then expanded in the propelling nozzle where it is accelerated to high speed to provide thrust.

In this analysis, it has been tried to analyze the simulation of an axial turbojet engine, using the ANSYS Fluent software.

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The Design – Axial Turbo Jet Engine Simulation

| ANSYS Fluent

A turbojet is an airbreathing jet engine, typically used in aircraft. It consists of a gas turbine with a propelling nozzle. The gas turbine has an air inlet, a compressor, a combustion chamber, and a turbine (that drives the compressor). The compressed air from the compressor is heated by burning fuel in the combustion chamber and then allowed to expand through the turbine. The turbine exhaust is then expanded in the propelling nozzle where it is accelerated to high speed to provide thrust.

In this analysis, it has been tried to analyze the simulation of an axial turbojet engine, using the ANSYS Fluent software.

Geometry & Grid

The geometry required for this analysis was generated by Ansys Design Modeler software. The meshing required for this analysis was also generated by Ansys Meshing software. The mesh type used in this analysis is unstructured. The total number of volume properties for shell & tube geometry is 7,1643e-002 m³.

Model

In this analysis, the k-epsilon Realizable turbulence viscosity model has been used to check the fluid flow, and also the Scalable Wall Function near the walls has been used.

Boundary Condition

In this analysis, the Cell Zone Condition for the design modeler part is defined by the Mesh Motion tab, and the rotational velocity speed of 477.4646 rpm is given to the design modeler.

Discretization of Equations

Due to the type of heat transfer in this analysis, a Pressure-Based solver has been used to solve the equations and the SIMPLE Algorithm for the discretization of velocity and pressure has been used. The energy and momentum equations have been discretized in the second-order upwind.

The results are presented as velocity contours.

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