Gas Turbine
Faculty: Dr. Matt Hyre, Dr. Mike Sexton
Students: Matt Kania, Raevon Pulliam
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Summary of Project:
In a turbojet engine, efficiency is a key component to engine performance when trying to get a maximum output of thrust.  In an attempt to analyze performance, the SR-30 Turbojet Engine owned by the Virginia Military Institute was used to create a computational model of the turbojet engine. The model was created and analyzed using Inventor, Gambit, Harpoon, and Fluent by combining a previously made combustion model with a model of the compression side.  The compressor model was made by using scaled pictures of the actual components.  Once this model was created it was checked against the actual turbojet engine for accuracy.  This fundamental model can be used as a platform to optimize fuel to air mixture, and modified nozzles can be created and installed on the turbojet to see if actual performance is improved.  In an attempt to make the SR-30 more useful in labs to illustrate this point, several interchangeable nozzles can be created for future students to see how the fuel to air mixture affects the thrust of the engine.
The nozzle, casing, MAF sensor, and the RPM sensor were all created with measurements taken by hand and geometries from the manufacturer.
After several failed attempts to mesh in GAMBIT, HARPOON was acquired and was used to create the mesh.
Animation of particle flow through the compressor. 
(Post processing done with Ensight. )
Completed Combustor Geometry and Mesh
Animation of particle flow through the combustor.