Blade Vibration on Centrifugal Compressors — Blade Response to Different Excitation Conditions

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dc.identifier.uri http://dx.doi.org/10.15488/3604
dc.identifier.uri https://www.repo.uni-hannover.de/handle/123456789/3636
dc.contributor.author Haupt, U.
dc.contributor.author Bammert, K.
dc.contributor.author Rautenberg, M.
dc.date.accessioned 2018-08-23T12:15:41Z
dc.date.available 2018-08-23T12:15:41Z
dc.date.issued 1987
dc.identifier.citation Haupt, U.; Bammert, K.; Rautenberg, M.: Blade Vibration on Centrifugal Compressors — Blade Response to Different Excitation Conditions. In: International Journal of Turbo and Jet Engines 4 (1987), S. 271-284. DOI: https://doi.org/10.1515/TJJ.1987.4.3-4.271
dc.description.abstract Results and analysis of blade vibration measurements on a high pressure ratio/high mass flow centrifugal compressor made with strain gages and using multichannel telemetry are described for compressors with 3 different types of vaned diffusers. Considerable high frequency blade excitation and vibration of the shallow region near the impeller outlet were observed. Initial progress to predict this dangerous excitation caused by the diffuser vanes was made with the help of FE computations using a simplified element system consisting of the vibrating zones of a 90ºsector of the impeller. Satisfactory agreement with measured vibration data was achieved. The influence of rotating stall on blade excitation was investigated using different types of vaned diffusers leading to different numbers of rotation stall zones and variations in the rotational speed of the cells. Blade vibration intensity due to surge in conjunction with variations of the diffuser is also considered. Holographic interferometry was successfully applied to blade vibration measurements on compressors in operation. The investigation was aimed at studying the occurrence of blade modes and the vibratory behavior of the different blades near the interesting inlet zone. The occurrence of different constellations of blade modes at a resonance point and at an operating point far from resonance was demonstrated. © Freund Publishing House Ltd. eng
dc.language.iso eng
dc.publisher Berlin : De Gruyter
dc.relation.ispartofseries International Journal of Turbo and Jet Engines 4 (1987)
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 Blade Vibration eng
dc.subject High Pressure Ratio eng
dc.subject Centrifugal Compressor eng
dc.subject.ddc 620 | Ingenieurwissenschaften und Maschinenbau ger
dc.title Blade Vibration on Centrifugal Compressors — Blade Response to Different Excitation Conditions
dc.type article
dc.type Text
dc.relation.issn 03340082
dc.relation.doi https://doi.org/10.1515/TJJ.1987.4.3-4.271
dc.bibliographicCitation.volume 4
dc.bibliographicCitation.firstPage 271
dc.bibliographicCitation.lastPage 284
dc.description.version publishedVersion
tib.accessRights frei zug�nglich


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