Computational Aeroacoustics of a Separate Flow Exhaust System with Eccentric Inner Nozzle
2007 (English)In: 45th AIAA Aerospace Sciences Meeting 2007, 2007, 28-39 p.Conference paper (Refereed)
A major issue related to our modern way of life is the noise caused by jet engine powered airliners. Methods to reduce the jet noise were proposed in the last decades starting with the introduction of high bypass turbofan engines. A numerical investigation of flow and acoustics of a separate flow exhaust system is performed in the present paper. The goal is to investigate how the noise generated by a separate flow jet engine exhaust is influenced if the symmetry of the jet exhaust geometry is broken by having the inner nozzle and the center body off the center line axis of the fan nozzle. A decomposition of flow variables is used that allows separation of flow and acoustic computations. Large Eddy Simulation approach is employed to compute the flow field and the acoustic sources. The inhomogeneous wave equation is used to compute the acoustic near- and far-fields. Using this method, previous numerical studies of the symmetric (baseline) configuration showed good agreement between the computed data and the experimental results. Comparisons between the near- and far-field baseline concentric case and the computations obtained using the eccentric configuration are performed showing an acoustic benefit for the offset case.
Place, publisher, year, edition, pages
2007. 28-39 p.
Jet Noise Supression, Off-set nozzles, Large Eddy Simulation, Acoustic Analogy
Fluid Mechanics and Acoustics Aerospace Engineering
IdentifiersURN: urn:nbn:se:kth:diva-48017ISBN: 13: 978-1-56347-890-1OAI: oai:DiVA.org:kth-48017DiVA: diva2:456615
45th AIAA Aerospace Sciences Meeting 2007. Reno, NV. 8 January 2007 - 11 January 2007
QC 20111117. AIAA 2007-132011-11-152011-11-152011-11-17Bibliographically approved