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Towards simulation of NASA35 axial compressor

Xiang, Junting, Schlüter, Jorg Uwe and Duan, Fei 2015, Towards simulation of NASA35 axial compressor, Aircraft engineering and aerospace technology, vol. 87, no. 6, pp. 571-583, doi: 10.1108/AEAT-03-2015-0073.

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Title Towards simulation of NASA35 axial compressor
Author(s) Xiang, JuntingORCID iD for Xiang, Junting orcid.org/0000-0003-1790-1692
Schlüter, Jorg UweORCID iD for Schlüter, Jorg Uwe orcid.org/0000-0001-7783-1361
Duan, Fei
Contributor(s) Varatharajoo, Renuganth
Journal name Aircraft engineering and aerospace technology
Volume number 87
Issue number 6
Start page 571
End page 583
Total pages 14
Publisher Emerald Group Publishing
Place of publication Bingley, Eng.
Publication date 2015-10-05
ISSN 0002-2667
Keyword(s) numerical methods
compressor performance
NASA35 axial compressor
Summary Purpose – This paper aims to validate and analyse the NASA35 axial compressor performance based on a numerical approach. Design/methodology/approach – Knowledge about flow property change during compressor operation at high and relatively low speed is still limited. This work provides a numerical approach to address these problems. Validation of numerical methods is proposed to generate confidence the numerical approach adopted, and after that, analysis of compressor performance at different operation conditions is carried out. Findings – The numerical methods proposed are proved capable in predicting compressor performance. Changes of flow property during compressor operation are discussed and explained. Research limitations/implications – The current numerical work is carried out based on the first stage of the NASA35 axial compressor, where the interactive effects from adjacent stage are not counted in. Furthermore, the steady-state simulation enforces an averaging of flow at rotor-stator interface, where the transient rotor-stator interaction is removed. Practical implications – This work validates the numerical methods used in the prediction of NASA35 axial compressor performance, and a similar numerical approach can be used for other turbomachinery simulation cases. Originality/value – This work reinforces the understanding of axial compressor operation and provides reliable results for further investigation of a similar type of compressor. In addition, details of flow field within the NASA35 compressor during operation are given and explained which experiments still have difficult to achieve.
Language eng
DOI 10.1108/AEAT-03-2015-0073
Field of Research 090199 Aerospace Engineering not elsewhere classified
091307 Numerical Modelling and Mechanical Characterisation
Socio Economic Objective 970109 Expanding Knowledge in Engineering
HERDC Research category C1.1 Refereed article in a scholarly journal
ERA Research output type C Journal article
Copyright notice ©2015, Emerald Group Publishing Limited
Persistent URL http://hdl.handle.net/10536/DRO/DU:30084468

Document type: Journal Article
Collection: School of Engineering
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