Experimental and numerical studies of sr30 turbojet engine combustion

The SR30 Turbojet Engine is a research-focused gas turbine capable of running on multiple different fuels derived through various sources. The maximum design parameters of the turbine are provided by the manufacturer and are utilized as a basis for comparison with simulated results and experimental results. The simulation’s parameters were set accordingly to the provided maximum values and used to simulate airflow through the turbine. The model was setup with an inlet mass flow rate of 0.5kg/s, 0.33kg/s, and 0.167kg/s, with 0.5kg/s being the maximum and 0.33kg/s and 0.167kg/s being 2/3 and 1/3 of the maximum flow rate respectively. The maximum experimental velocity of the flow after the compressor impeller was 473m/s, the simulated maximum velocity in a 2-D plane was 398m/s and in 3-D it was 478m/s. The simulated values are within a small margin of error with the experimental and calculated values due to the refined boundary conditions. The 3-D streamlines displayed the concentrations of high velocity in the compressor and turbine blades at a maximum velocity of 425m/s. This observation was also applicable to the vorticity of the flow and also confirmed the findings found in the experimental testing. The velocity vectors depicting the air flow displayed some unusual behavior by flowing in the opposite direction of the intended flow; however, the large concentrations confirmed the increased speed at the compressor blade tips which had a peak velocity of 539m/s. The addition of combustion to the simulation of the turbine could be conducted in a future investigation with modifications to the boundary conditions to better accommodate for more accurate results that reflect the experimentally obtained results.