Aerodynamic and structural performances of a single-stage transonic axial compressor with blade fillet radius
International Journal of Intelligent Unmanned Systems
ISSN: 2049-6427
Article publication date: 2 February 2022
Issue publication date: 29 June 2023
Abstract
Purpose
This study’s investigation aims to clarify the effect of an additional geometry, i.e. a fillet radius, to the blades of a single-stage transonic axial compressor, NASA Stage 37, on its aerodynamic and structural performances.
Design/methodology/approach
Applying the commercial simulation software and the one-way fluid–structure interaction (FSI) approach, this study first evaluated the simulation results with the experimental data for the aerodynamic performances. Second, this paper compared the structural performances between the models with and without fillets.
Findings
This research analyses the aerodynamic results (i.e. total pressure ratio, adiabatic efficiency, stall margin) and the structural outcomes (i.e. equivalent von Mises stress, total deformation) of the single-stage transonic axial compressor NASA Stage 37.
Originality/value
This paper mentions the influence of blade fillets (i.e. both rotor hub fillet and stator shroud fillet) on the compressor performances (i.e. the aerodynamic and structural performances).
Keywords
Acknowledgements
The authors are also grateful to the cooperation between Viettel Aerospace Institute (Vietnam), Hanoi University of Science and Technology, and Le Quy Don Technical University for the support during this research.
Funding: This study was funded by the Foundation for Science and Technology of Le Quy Don Technical University under the grant number 20.1.048.
Citation
Chu, H.-Q. and Dinh, C.-T. (2023), "Aerodynamic and structural performances of a single-stage transonic axial compressor with blade fillet radius", International Journal of Intelligent Unmanned Systems, Vol. 11 No. 3, pp. 407-424. https://doi.org/10.1108/IJIUS-07-2021-0069
Publisher
:Emerald Publishing Limited
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