The Influence of Different Geometries for a Vaned Diffuser on the Pressure Distribution in a Centrifugal Compressor

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dc.identifier.uri http://dx.doi.org/10.15488/3602
dc.identifier.uri https://www.repo.uni-hannover.de/handle/123456789/3634
dc.contributor.author Teipel, Ingolf
dc.contributor.author Wiedermann, Alexander
dc.date.accessioned 2018-08-23T12:15:41Z
dc.date.available 2018-08-23T12:15:41Z
dc.date.issued 1985
dc.identifier.citation Teipel, I.; Wiedermann, A.: The Influence of Different Geometries for a Vaned Diffuser on the Pressure Distribution in a Centrifugal Compressor. In: International Journal of Turbo and Jet Engines 2 (1985), Nr. 4, S. 337-344. DOI: https://doi.org/10.1515/TJJ.1985.2.4.337
dc.description.abstract In this paper the transonic flow field in a vaned diffuser of a centrifugal compressor has been studied. Different geometries of the diffuser blades have been considered. Particularly with respect to the pressure field it is important to understand their influence on the development of the shock waves. For this problem a centrifugal compressor with high pressure ratio per stage has been examined. It is assumed that the impeller speed is so large that the flow may become transonic at the impeller exit. To calculate flows with shocks a time-marching method is used for solving the two-dimensional Euler equations in a conservative form. A MacCormack's second order difference scheme is applied. There are two important points which have been studied in this paper. Firstly the geometry of the blades as far as the thickness distribution is concerned is kept unchanged and only the stagger angle has been altered. The performance maps of these diffusers and their effect on the whole machine will be discussed. Secondly the results which have been obtained by using vanes with different thickness distributions will be presented. Mean values of the quantities used for the performance map will be shown. Wall pressure distributions as well as fields of isobars and of constant Mach numbers will be demonstrated to provide a better understanding of the pressure recovery in centrifugal compressor diffusers. © Martinus Nijhoff Publishers, Dordrecht and Freund Publishing House eng
dc.language.iso eng
dc.publisher Leiden : Martinus Nijhoff Publishers
dc.relation.ispartofseries International Journal of Turbo and Jet Engines 2 (1985), Nr. 4
dc.rights Es gilt deutsches Urheberrecht. Das Dokument darf zum eigenen Gebrauch kostenfrei genutzt, aber nicht im Internet bereitgestellt oder an Außenstehende weitergegeben werden. Dieser Beitrag ist aufgrund einer (DFG-geförderten) Allianz- bzw. Nationallizenz frei zugänglich.
dc.subject Transonic Flow Field eng
dc.subject Diffuser eng
dc.subject Shock Waves eng
dc.subject.ddc 530 | Physik ger
dc.subject.ddc 620 | Ingenieurwissenschaften und Maschinenbau ger
dc.title The Influence of Different Geometries for a Vaned Diffuser on the Pressure Distribution in a Centrifugal Compressor
dc.type article
dc.type Text
dc.relation.issn 03340082
dc.relation.doi https://doi.org/10.1515/TJJ.1985.2.4.337
dc.bibliographicCitation.issue 4
dc.bibliographicCitation.volume 2
dc.bibliographicCitation.firstPage 337
dc.bibliographicCitation.lastPage 344
dc.description.version publishedVersion
tib.accessRights frei zug�nglich


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