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
Aeroelastic forced response of a bladed drum from a low pressure compressor
KTH, School of Industrial Engineering and Management (ITM), Energy Technology, Heat and Power Technology.
2016 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

The purpose of this master thesis is to provide a reliable methodology to predict the forced response of a monoblock bladed drum from a low pressure compressor. Pre-test forced response calculations have already been made at Techspace Aero in 2013. Now that experimental data are available, the methodology has to be adapted to ensure the best numerical-experimental correlation possible. The final goal is that, at the end of the thesis, engineers at Techspace Aero will be able to launch reliable forced response simulations within a short amount of time. For the sake of confidentiality, some data are not revealed, such as the engine name, some numerical values (forced response, aerodynamic damping, frequency of the mode etc…) and axis scales.

In this paper, the study focuses on the forced response of a rotor blade from the first stage under the excitation from the upstream stator. The mode under investigation is the 2S2, the one that responded during the experiment. The TWIN approach is used to compute the forced response of the rotor blade. With this approach, a steady stage computation has first to be carried on as an initialization. Then two unsteady computations are necessary. The first, without blade motion, will provide the excitation aerodynamic forces. The aerodynamic damping will be extracted from the second one, where the motion of the blade is imposed on a given eigenmode. The forced response can then be computed with these two results and some additional structural data.  The results will be compared to the experimental value.

Place, publisher, year, edition, pages
2016.
Keyword [en]
Aeroelasticity, Forced response, Bladed drum, Low pressure compressor
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-183376OAI: oai:DiVA.org:kth-183376DiVA: diva2:910163
Presentation
2016-02-16, 14:00 (English)
Supervisors
Examiners
Available from: 2016-03-21 Created: 2016-03-08 Last updated: 2016-03-21Bibliographically approved

Open Access in DiVA

fulltext(8795 kB)96 downloads
File information
File name FULLTEXT01.pdfFile size 8795 kBChecksum SHA-512
7fe4d02e77e061e866a719cee832602d84cf5941ff397fd2f3574e934ebc356b38ecb4b6c3c1add71768b39bf6b2ef179705bdb133f512c7ae8bfead2494e31a
Type fulltextMimetype application/pdf

Search in DiVA

By author/editor
Lamouroux, Julien
By organisation
Heat and Power Technology
Aerospace Engineering

Search outside of DiVA

GoogleGoogle Scholar
Total: 96 downloads
The number of downloads is the sum of all downloads of full texts. It may include eg previous versions that are now no longer available

urn-nbn

Altmetric score

urn-nbn
Total: 178 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