Abstract
Fan noise is a major contributor to the noise problem of an airplane jet engine. An understanding of the acoustics of the jet engine is necessary in order to successfully control the fan noise of the engine. A numerical boundary element method model has been developed using Sysnoise to simulate active noise control of fan noise in the engine duct. Control of multiple radial modes is targeted through the use of a modal controller using Newton’s algorithm. Results from the model are compared with measurements made previously using the NASA Glenn Research Center test rig facility. Currently work is progressing on the numerical implementation of control on a more realistic geometry.
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