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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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2191-0332
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Volume 36, Issue 2

Issues

Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method

Sercan Acarer
  • Corresponding author
  • Department of Mechanical Engineering, İzmir Katip Çelebi University, 35620 Çiğli/İzmir, Turkey
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  • Other articles by this author:
  • De Gruyter OnlineGoogle Scholar
/ Ünver Özkol
Published Online: 2017-02-22 | DOI: https://doi.org/10.1515/tjj-2016-0083

Abstract

The two-dimensional streamline curvature through-flow modeling of turbomachinery is still a key element for turbomachinery preliminary analysis. Basically, axisymmetric swirling flow field is solved numerically. The effects of blades are imposed as sources of swirl, work input/output and entropy generation. Although the topic is studied vastly in the literature for compressors and turbines, combined modeling of the transonic fan and the downstream splitter of turbofan engine configuration, to the authors’ best knowledge, is limited. In a prior study, the authors presented a new method for bypass fan modeling for inverse design calculations. Moreover, new set of practical empirical correlations are calibrated and validated. This paper is an extension of this study to rapid off-design analysis of transonic by-pass fan systems. The methodology is validated by two test cases: NASA 2-stage fan and GE-NASA bypass fan case. The proposed methodology is a simple extension for streamline curvature method and can be applied to existing compressor methodologies with minimum numerical effort.

Keywords: bypass fan; through-flow; streamline curvature; off-design; performance map

PACS: Computational techniques/fluid dynamics; 47.11.-j

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About the article

Received: 2016-12-28

Accepted: 2017-01-19

Published Online: 2017-02-22

Published in Print: 2019-05-27


The author(s) received no financial support for the research, authorship, and/or publication of this article.


Citation Information: International Journal of Turbo & Jet-Engines, Volume 36, Issue 2, Pages 137–146, ISSN (Online) 2191-0332, ISSN (Print) 0334-0082, DOI: https://doi.org/10.1515/tjj-2016-0083.

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