Aero-acoustic performance of adaptive nacelle inlet
2015 (English)In: 21st AIAA/CEAS Aeroacoustics Conference, 2015Conference paper (Other academic)Text
The aero-acoustic investigation of the fan noise propagation is conducted. The fan noise is propagated through the series of adaptive inlet shapes of turbofan engine toward the far field. The inlet shape adaptation is made by changing position of one points on the front part of the inlet contour. The investigation is performed without the influence of the mean flow. The propagation of two acoustic modes was investigated, the combination of first radial mode with first and the second circumferential mode. The intensity and directivity of the fan noise in the far field is observed. A finite element solver for convected Helmholtz equation is used in the inner part of the inlet, with perfectly matched layer boundary condition close to the inlet entrance. The outer part of domain is coupled and solved by Kirchoff integral method. The results showed the influence of the inlet shape adaptation on the noise intensity level as well as the directivity of propagation.
Place, publisher, year, edition, pages
Acoustic noise, Circumferential modes, Convected Helmholtz equation, Finite element solver, Inlet shape, Kirchoff integral method, Noise intensities, Perfectly Matched Layer, Radial mode, Aeroacoustics
IdentifiersURN: urn:nbn:se:kth:diva-186744ScopusID: 2-s2.0-84962502761ISBN: 9781624103674OAI: oai:DiVA.org:kth-186744DiVA: diva2:931770
21st AIAA/CEAS Aeroacoustics Conference, 2015, 22 June 2015 through 26 June 2015
QC 201605302016-05-302016-05-132016-08-18Bibliographically approved