Contributions from the combustor to the overall propulsion noise of civilian transport aircraft are starting to become important due to turbofan design trends and expected advances in mitigation of other noise sources. During on-ground, static-engine acoustic tests, combustor noise is generally sub-dominant to other engine noise sources because of the absence of in-flight effects. Consequently, noise-source separation techniques are needed to extract combustor-noise information from the total noise signature in order to further progress. A novel four-signal source-separation method is applied to data from a static, full-scale engine test and compared to previous methods. The new method is, in a sense, a combination of two- and three-signal techniques and represents an attempt to alleviate some of the weaknesses of each of those approaches. This work is supported by the NASA Advanced Air Vehicles Program, Advanced Air Transport Technology Project, Aircraft Noise Reduction Subproject and the NASA Glenn Faculty Fellowship Program.
Full-Scale Turbofan Engine Noise-Source Separation Using a Four-Signal Method
2016
28 pages
Report
Keine Angabe
Englisch
Mathematical models , Microphones , Far fields , Engine tests , Noise measurement , Aircraft , Data processing , Acoustic measurement , Signal detectors , Full scale tests , Aircraft noise , Computational aeroacoustics , Combustion chambers , Signal analysis , Propulsion system configurations , Signature analysis , Signal measurement , Engine noise , Noise generators , Static tests , Turbofan engines
Turbofan-engine noise suppression
AIAA | 1966
|Turbofan-engine noise suppression
AIAA | 1967
|