The purpose of this work is to study the aerodynamic performance of a tandem C4 base-profile compressor blade using numerical tools. In this paper, the flow along the tandem blade is studied for various relative blade positions. In all the studied cases, the front blade is fixed and the position of the rear blade is varied as a function of the axial and tangential displacements. A computer code was developed in "Visual Basic" using linear strength vortex-panel method to predict the aerodynamic performance of the tandem blade.
| Published in |
American Journal of Aerospace Engineering (Volume 2, Issue 1-1)
This article belongs to the Special Issue Hands-on Learning Technique for Multidisciplinary Engineering Education |
| DOI | 10.11648/j.ajae.s.2015020101.17 |
| Page(s) | 74-92 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2014. Published by Science Publishing Group |
Tandem Blades, Linear Strength Vortex Panel Method, Rotor, Stator, Axial-Compressor
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| [10] | J. McGlumphy, W.-F. Ng, S. R. Wellborn, and S. Kempf, "Numerical investigation of tandem airfoils for subsonic axial- flow compressor blades," Journal of Turbomachinery, Vol. 131, pp. 1-8, April 2009. |
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APA Style
Atef Mohamed Alm-Eldien, Ahmed Farouk Abdel Gawad, Gamal Hafaz, Mohamed Gaber Abd El Kreim. (2014). Performance Evaluation of the Tandem C4 Blades for Axial-Flow Compressors. American Journal of Aerospace Engineering, 2(1-1), 74-92. https://doi.org/10.11648/j.ajae.s.2015020101.17
ACS Style
Atef Mohamed Alm-Eldien; Ahmed Farouk Abdel Gawad; Gamal Hafaz; Mohamed Gaber Abd El Kreim. Performance Evaluation of the Tandem C4 Blades for Axial-Flow Compressors. Am. J. Aerosp. Eng. 2014, 2(1-1), 74-92. doi: 10.11648/j.ajae.s.2015020101.17
AMA Style
Atef Mohamed Alm-Eldien, Ahmed Farouk Abdel Gawad, Gamal Hafaz, Mohamed Gaber Abd El Kreim. Performance Evaluation of the Tandem C4 Blades for Axial-Flow Compressors. Am J Aerosp Eng. 2014;2(1-1):74-92. doi: 10.11648/j.ajae.s.2015020101.17
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Download@article{10.11648/j.ajae.s.2015020101.17,
author = {Atef Mohamed Alm-Eldien and Ahmed Farouk Abdel Gawad and Gamal Hafaz and Mohamed Gaber Abd El Kreim},
title = {Performance Evaluation of the Tandem C4 Blades for Axial-Flow Compressors},
journal = {American Journal of Aerospace Engineering},
volume = {2},
number = {1-1},
pages = {74-92},
doi = {10.11648/j.ajae.s.2015020101.17},
url = {https://doi.org/10.11648/j.ajae.s.2015020101.17},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.s.2015020101.17},
abstract = {The purpose of this work is to study the aerodynamic performance of a tandem C4 base-profile compressor blade using numerical tools. In this paper, the flow along the tandem blade is studied for various relative blade positions. In all the studied cases, the front blade is fixed and the position of the rear blade is varied as a function of the axial and tangential displacements. A computer code was developed in "Visual Basic" using linear strength vortex-panel method to predict the aerodynamic performance of the tandem blade.},
year = {2014}
}
TY - JOUR T1 - Performance Evaluation of the Tandem C4 Blades for Axial-Flow Compressors AU - Atef Mohamed Alm-Eldien AU - Ahmed Farouk Abdel Gawad AU - Gamal Hafaz AU - Mohamed Gaber Abd El Kreim Y1 - 2014/10/17 PY - 2014 N1 - https://doi.org/10.11648/j.ajae.s.2015020101.17 DO - 10.11648/j.ajae.s.2015020101.17 T2 - American Journal of Aerospace Engineering JF - American Journal of Aerospace Engineering JO - American Journal of Aerospace Engineering SP - 74 EP - 92 PB - Science Publishing Group SN - 2376-4821 UR - https://doi.org/10.11648/j.ajae.s.2015020101.17 AB - The purpose of this work is to study the aerodynamic performance of a tandem C4 base-profile compressor blade using numerical tools. In this paper, the flow along the tandem blade is studied for various relative blade positions. In all the studied cases, the front blade is fixed and the position of the rear blade is varied as a function of the axial and tangential displacements. A computer code was developed in "Visual Basic" using linear strength vortex-panel method to predict the aerodynamic performance of the tandem blade. VL - 2 IS - 1-1 ER -
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