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International Journal of Turbo & Jet-Engines

Ed. by Sherbaum, Valery / Erenburg, Vladimir

IMPACT FACTOR 2018: 0.863

CiteScore 2018: 0.66

SCImago Journal Rank (SJR) 2018: 0.211
Source Normalized Impact per Paper (SNIP) 2018: 0.625

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Volume 31, Issue 3


Flow Pattern Characterization for a Centrifugal Impeller

Efrén M. Benavides
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  • Universidad Politécnica de Madrid, ETSI Aeronáuticos (UPM), Pza. Cardenal Cisneros 3, 28040 Madrid (Spain)
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Published Online: 2012-10-26 | DOI: https://doi.org/10.1515/tjj-2012-0035


This paper proposes a model for characterizing the flow pattern of a centrifugal impeller attending to the severity of the reverse flow. The model assumes 1) a definition of an escaping particle as the one that flows in every operational point from the trailing edge towards the leading edge of the impeller blades, and 2) a characterization of flow where an operational point is said to have a theoretical flow pattern if it is not possible to establish a fully-reversed escaping particle on it. Therefore, the first part of the article is focused on defining an escaping particle for a centrifugal compressor. The model locates over the map of a centrifugal impeller the line that splits the map in two regions: the region on the right hand side, where a theoretical flow pattern can exist, and the region on the left, where a theoretical flow pattern cannot exist. Therefore, the locus of this line marks a frontier where the expected performance of the impeller cannot be sustained as high as expected. The second part of the article uses a high-performance commercial centrifugal impeller wheel for contrasting the model. A qualitative characterization of the surge line, conclusions and discussions are presented.

Keywords: stability; surge; compressor map; flow pattern; efficiency line

PACS: 47.20.-k; 47.85.Kn; 89.20.Bb; 89.20.Kk; 89.40.-a; 89.40.Dd

About the article

Received: 2012-08-26

Accepted: 2012-08-28

Published Online: 2012-10-26

Published in Print: 2014-08-01

Citation Information: International Journal of Turbo & Jet-Engines, Volume 31, Issue 3, Pages 199–220, ISSN (Online) 2191-0332, ISSN (Print) 0334-0082, DOI: https://doi.org/10.1515/tjj-2012-0035.

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