Three-Dimensional Computational Modeling of an SR-30 Turbojet Engine ME-444-06: Cooperative Engineering Center

Engineers: Cadets Matthew A. Kania and Raevon M. Pulliam Advisor: LTC Matthew R. Hyre

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 this, the SR-30 Turbojet Engine owned by the Virginia Military Institute was used. To do this, a computational model of the turbojet engine was created and analyzed using Inventor, Gambit, Harpoon, and Fluent. The model was created by combining a previously made combustion side model with a model of the compression side. The compressor side model was made by using scaled pictures of the actual components. The data that was output from the final computational run was validated from experimentally collected data. These results were also used to perform a thermodynamic validation of the system.

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.

Figure 1: Velocity Profile Through the End of the Nozzle and the Compressor

Figure 2: Temperature Plot in Combustor