Boundary layer ingestion (BLI) is a popular area of research by many entities in aerospace due to the potential for large fuel burn savings, but research on the noise implications of this technology is limited. The noise generated by the interaction of the engine fan and the aircraft boundary layer has relatively large uncertainties. The purpose of this project is to identify, develop, and validate a parametric module for a generic BLI engine that can predict the noise from the engine fan, taking into account the specifics of the aircraft and engine configuration and design. Parameters influencing the model include aerodynamic distortion parameters or others that may affect the noise of the propulsor. The module developed will be based on lower order methods but will seek to validate such methods against higher fidelity approaches and any publicly available experimental data sets.
This research will provide the FAA with a tool for the rapid assessment of BLI impacts on the noise of future advanced airplane concepts. This tool will allow designers to identify potential noise-related impacts for BLI propulsion concepts early in the conceptual design process and to identify potential solutions for mitigation of such impacts if they exist. This capability will also enable the FAA to rapidly evaluate concepts to assess their noise viability in the future. The product of this work will be developed in such a way so as to enable integration with NASA noise prediction tools, potentially in a follow-on effort.
Last Updated 7/7/2020