NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Semi-Empirical Modeling and Prediction of Direct Combustor NoiseDue to turbofan design trends, advances in fan-noise-mitigation techniques, and expected aircraft configuration changes, the impact on overall airport community noise from certain aircraft-propulsion noise sources, such as fan and jet noise, will be reduced at all certification points in the future. The situation with regard to turbofan-core noise is less clear however. Combustor noise in particular—which presently is an important core-noise component, but not dominant from an overall noise perspective—could become more prominent in upcoming high-power-density core designs. Its detailed source structure in the combustor, including the indirect combustor-noise mechanism, and the effects of the propagation path through the engine and exhaust nozzle need to be better understood. This report reviews the current status of modeling and prediction of direct combustor noise. This work is carried out under the NASA Advanced Air Vehicles Program, Advanced Air Transport Technology Project, Aircraft Noise Reduction Subproject.
Document ID
20190000001
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Hultgren, Lennart S.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
January 2, 2019
Publication Date
December 1, 2018
Subject Category
Environment Pollution
Report/Patent Number
NASA/TM?2018-220041
GRC-E-DAA-TN63363
Funding Number(s)
WBS: WBS 081876.02.03.50.06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Turbomachinery Noise
Aeroacoustics
Combustor Noise
No Preview Available