Change search
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf
Analyzing the Impact of the Inlet Temperature on the Acoustic Noise Production from a Supersonic Jet using LES
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.ORCID iD: 0000-0001-7715-863X
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.ORCID iD: 0000-0001-7330-6965
KTH, School of Engineering Sciences (SCI), Mechanics.
Aerospace Engineering, University of Cincinnati.
2013 (English)In: Proceedings of Meetings on Acoustics / [ed] Acoustical Society of America, American Institute of Physics (AIP), 2013, 030011- p.Conference paper, Published paper (Refereed)
Abstract [en]

Non-ideal expanded supersonic jets emerging from a nozzle produce three different types of noise, i.e., shock-associated broadband noise,screech noise, and the turbulent mixing noise. The screech tone occurs due to self-excitation in a feedback-loop of flow propagating downstream and acoustic wave interaction. In downscaled laboratory experiments often the screech noise occurs, while the real applied exhaustjet of a gas turbine engine does not show this phenomena. Apart from a geometric scaling difference, usually a lower temperature is employed in experimental studies. The compressible Navier-Stokes equations are simulated numerically by a large eddy simulation approach to investigate the effect of jet operation temperature onto the noise development in a supersonic jet originating from a convergent-divergent nozzle. The jet-exit Mach-number is 1.56, while the total temperature ratios are 1.27, 2.46, and 3.65. The differences in the acoustic near-field will be presented and the interaction of flow-field with acoustic waves will be analyzed and compared to each other.

Place, publisher, year, edition, pages
American Institute of Physics (AIP), 2013. 030011- p.
Series
Proceedings of Meetings on Acoustics, ISSN 1939-800X ; Vol. 19
Keyword [en]
Supersonic Jet, temperature effects, LES, acoustics
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-124157DOI: 10.1121/1.4799241Scopus ID: 2-s2.0-84878961768OAI: oai:DiVA.org:kth-124157DiVA: diva2:633228
Conference
21st International Congress on Acoustics, ICA 2013 - 165th Meeting of the Acoustical Society of America; Montreal, QC, Canada, 2-7 June, 2013
Note

QC 20140618

Available from: 2013-06-26 Created: 2013-06-26 Last updated: 2017-03-24Bibliographically approved

Open Access in DiVA

No full text

Other links

Publisher's full textScopusPublished article

Authority records BETA

Semlitsch, BernhardMihaescu, Mihai

Search in DiVA

By author/editor
Semlitsch, BernhardMihaescu, MihaiFuchs, LaszloGutmark, Ephraim
By organisation
MechanicsLinné Flow Center, FLOW
Aerospace Engineering

Search outside of DiVA

GoogleGoogle Scholar

doi
urn-nbn

Altmetric score

doi
urn-nbn
Total: 25 hits
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf