This SBIR project proposes to develop a computational tool for fan broadband noise prediction based on a large-eddy-simulation (LES) approach. The proposed approach combines the advantages of those existing high-fidelity methods in literature for simulation of NASA 22-in fan noise source diagnostic test (SDT), i.e., the LES with the WALE SGS model for turbulence simulation and modeling, and the Cartesian mesh approach for rotor-stator coupling, and the consideration of the whole rotor and stator annulus in simulation. Much more accurate spatial discretization schemes will also be used for improving the prediction of turbulent eddies and acoustic waves. As a feasibility study, the Phase I outcome will demonstrate the feasibility of the proposed LES approach for accurate simulation of NASA 22-in fan noise source diagnostic test. Therefore, it is meaningful to fully develop, demonstrate, and validate this software tool in Phase II.
The Advanced Air Transport Technology (AATT) and Commercial Supersonic Technology (CST) Projects would benefit from the developed computational tool that could be used to predict the performance and noise impacts of those novel engine installations for noise reduction. The Transformational Tools and Technologies (TTT) Project would benefit from the developed computational tool to enhance the ability to consider acoustics earlier in the aircraft design process.
DoD's High Performance Computing Modernization Program would benefit from this computational tool that could provide them a useful tool for fan broadband noise prediction. Design engineers in engine manufacturers can use the developed computational tool to explore various noise reduction concepts and validate fast, low-fidelity analytical methods for trade-off studies and performance prediction.