INLET MASS FLOW MODELING AND MEASUREMENT THROUGH A TRANSONIC AXIAL COMPRESSOR FAN

Includes supplementary materialThis study investigated the creation of a 3-D computational fluid dynamics model of the Transonic Compressor Rig used for the testing of the Naval Postgraduate School Military Fan. This modeled rig conditions the flow into the rotor while measuring the mass flow rate during experimental testing. Using these simulations, a new bell mouth inlet attachment was designed for the rig to further increase confidence in experimental mass flow data. The goal of computational modeling was to observe upstream flow conditions and validate the model against experimental results, while also providing data for further testing. Also documented in this thesis is the performance data from the smooth casing rotor-only tests. All testing was performed at the Turbopropulsion Laboratory at the Naval Postgraduate School. The bell mouth attachment design process included the evaluation of shape and diameter sizing for the desired pressure readings. The computational model was created using compressible flow turbulence modeling and run for various pressure differentials. A parametric study on throttle indexing was created by imitating the throttle’s opening through the manipulation of the model’s geometry. Results gave insight into upstream characteristics of the flow prior to the compressor, while also showing promising comparisons to recorded test data. Future work will involve the inclusion of the bell mouth attachment in both testing and analytical simulation.Ensign, United States NavyApproved for public release. distribution is unlimite