Ir al contenido (pulsa Retorno)

Universitat Politècnica de Catalunya

    • Català
    • Castellano
    • English
    • LoginRegisterLog in (no UPC users)
  • mailContact Us
  • world English 
    • Català
    • Castellano
    • English
  • userLogin   
      LoginRegisterLog in (no UPC users)

UPCommons. Global access to UPC knowledge

Banner header
60.707 UPC E-Prints
You are here:
View Item 
  •   DSpace Home
  • E-prints
  • Departaments
  • Departament de Mecànica de Fluids
  • Ponències/Comunicacions de congressos
  • View Item
  •   DSpace Home
  • E-prints
  • Departaments
  • Departament de Mecànica de Fluids
  • Ponències/Comunicacions de congressos
  • View Item
JavaScript is disabled for your browser. Some features of this site may not work without it.

Uncertainty quantification in large eddy simulations of a rich-dome aviation gas turbine

Thumbnail
View/Open
Main article (4,422Mb) (Restricted access)   Request copy 

Què és aquest botó?

Aquest botó permet demanar una còpia d'un document restringit a l'autor. Es mostra quan:

  • Disposem del correu electrònic de l'autor
  • El document té una mida inferior a 20 Mb
  • Es tracta d'un document d'accés restringit per decisió de l'autor o d'un document d'accés restringit per política de l'editorial
Share:
 
 
10.1115/GT2017-64835
 
  View Usage Statistics
Cita com:
hdl:2117/185913

Show full item record
Jofre Cruanyes, LluísMés informacióMés informacióMés informació
Document typeConference report
Defense date2017
Rights accessRestricted access - publisher's policy
Attribution-NonCommercial-NoDerivs 3.0 Spain
Except where otherwise noted, content on this work is licensed under a Creative Commons license : Attribution-NonCommercial-NoDerivs 3.0 Spain
Abstract
In this work, a rich-dome aviation combustor operating over a range of high-power conditions is investigated using multiple Large Eddy Simulations (LES). The LES flow solutions are obtained with CharLES, a massively-parallel framework for compressible, reacting flows in complex geometries. The CharLES solver constructs a body-conforming mesh from the 3D Voronoi diagram of a set of regularly distributed seed points within the computational domain. The computational domain spans from the compressor exit plane to the combustor exit plane and includes the passages around the combustor liners. A baseline solution is first obtained at nominal conditions using a reference grid and validated using non-dimensional exit profile. Non-intrusive Uncertainty Quantification (UQ) is then employed to characterize the uncertainties on a few key combustor metrics. It is found that the overall variability at the exit plane is actually larger than the input uncertainty. This highlights the non-linear coupling between the flow and the reacting processes inside the combustor. Areas of high temperature variability are highlighted, especially downstream of the dilution holes. Finally, it is found that uncertainty in fuel flowrate has a greater impact on outlet quantities whereas uncertainty in air inlet temperature has a greater impact on liner quantities.
CitationJofre, L. Uncertainty quantification in large eddy simulations of a rich-dome aviation gas turbine. A: Turbomachinery Technical Conference & Exposition. "Proceedings of ASME Turbo Expo 2017: Turbomachinery Technical Conference & Exposition". 2017, p. 1-11. 
URIhttp://hdl.handle.net/2117/185913
DOI10.1115/GT2017-64835
ISBN978-0-7918-5077-0
Publisher versionhttps://doi.org/10.1115/GT2017-64835
Collections
  • Departament de Mecànica de Fluids - Ponències/Comunicacions de congressos [182]
Share:
 
  View Usage Statistics

Show full item record

FilesDescriptionSizeFormatView
2017_MYDLSJI_ASMEGT.pdfBlockedMain article4,422MbPDFRestricted access

Browse

This CollectionBy Issue DateAuthorsOther contributionsTitlesSubjectsThis repositoryCommunities & CollectionsBy Issue DateAuthorsOther contributionsTitlesSubjects

© UPC Obrir en finestra nova . Servei de Biblioteques, Publicacions i Arxius

info.biblioteques@upc.edu

  • About This Repository
  • Contact Us
  • Send Feedback
  • Privacy Settings
  • Inici de la pàgina