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The Design – Axial Turbo Jet Engine Simulation | ANSYS CFX

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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 CFX software.

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The Design – Axial Turbo Jet Engine Simulation

| ANSYS CFX

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 CFX 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 geometry is 1,8421e-002 m³.

Model

In this analysis,  a steady-state analysis type was used to obtain the results to check the fluid flow. In this analysis, non-buoyant models have been used and stationary domain motion has also been activated in this analysis. In this analysis, a k-Epsilon model was used to study the air at 25 C flow and isothermal fluid models of the heat transfer.

Boundary Condition

In this analysis, the flow inlet, which only includes the air at 25 C, is defined as a velocity inlet. The mass flow rate value of mass and momentum velocity inlet is 20 [m s^-1]. The turbulence of the design modeler is set as a medium with an intensity equal to 5 %. The heat transfer is considered a static temperature. The static temperature of heat transfer is 25 [C].

Discretization of Equations

In this analysis, high-resolution is used for the advection scheme of the basic settings. In this analysis, the first-order is used for turbulence numerics. In this analysis, the residual type of convergence criteria is RMS and the residual target of convergence criteria is 1.E-4.

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

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