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
Large Eddy Simulations of Microjets Impact on Supersonic Jet Exiting a C-D Conical Nozzle
KTH, School of Engineering Sciences (SCI), Mechanics, Fluid Physics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.ORCID iD: 0000-0001-7715-863X
KTH, School of Engineering Sciences (SCI), Mechanics, Fluid Physics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.ORCID iD: 0000-0001-7330-6965
KTH, School of Engineering Sciences (SCI), Mechanics, Fluid Physics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW.
2013 (English)Conference paper, Published paper (Other academic)
Abstract [en]

The effect of multiple microjets on the acoustic noise production originating from a super-sonic jet exhausting a gas turbine engine is studied numerically using the Large Eddy Simulation (LES) approach. The nozzle exit design Mach-number is 1.56, while the total temperature ratio is kept to 1.27. The nozzle contour is a double cone converging- diverging nozzle. The emerging jet is slightly over-expanded. A double shock-diamond pattern develops in the supersonic flow. The study focuses on the changes in the flow pattern, the shock-associated noise and the radiated near-field acoustics when using fluidics as compared with a baseline, (i.e. without fluidics).

Just downstream of the nozzle lip, twelve cylindrical microjets are placed circumferentially, with a 60 inclination angle towards the nozzle centerline axis, in the streamwise flow direction. The pressurized mass-flow feeding the microjets is assumed to be initially at ambient conditions. The amount of pressurization is given as an Injection Pressure Ratio (IPR) and represents the investigation parameter.

Acoustic based experiments performed at University of Cincinnati (UC) exhibited acous- tic benefit when using the mentioned set-up for the microjets. However, the impact that injection had on the flow-field was dicult to be quantified. Thus, LES calculations have been performed to analyze the compressible flow-field, the shock-structure alteration and thrust evaluations associated with the fluidics. 

Place, publisher, year, edition, pages
AIAA, 2013. 135- p.
Keyword [en]
Fluid dynamics, Acoustics, Large Eddy Simulation
National Category
Fluid Mechanics and Acoustics Aerospace Engineering
Research subject
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-141038Scopus ID: 2-s2.0-84883715328ISBN: 978-162410213-4 (print)OAI: oai:DiVA.org:kth-141038DiVA: diva2:694157
Conference
19th AIAA/CEAS Aeroacoustics Conference
Note

QC 20140409

Available from: 2014-02-05 Created: 2014-02-05 Last updated: 2015-03-04Bibliographically approved

Open Access in DiVA

No full text

Scopus

Authority records BETA

Semlitsch, BernhardMihaescu, Mihai

Search in DiVA

By author/editor
Semlitsch, BernhardMihaescu, MihaiFuchs, Laszlo
By organisation
Fluid PhysicsLinné Flow Center, FLOW
Fluid Mechanics and AcousticsAerospace Engineering

Search outside of DiVA

GoogleGoogle Scholar

isbn
urn-nbn

Altmetric score

isbn
urn-nbn
Total: 51 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