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Improving the performance and work-absorbing capacity of the axial-flow compressor by using tandem blades.

Document Type : Original Article

Authors

Islamic Azad University Science and Research Branch

Abstract

The compressor blade is responsible for increasing the flow pressure. By adding a blade behind the main blade, the compressor performance can be improved by increasing the pressure ratio and reducing the weight. The tandem improves the performance and increases the compressor absorption coefficient by increasing the pressure ratio, preventing flow separation and controlling the boundary layer. This has led compressor designers to seek to reduce weight, increase pressure ratio and increase efficiency by using tandem. The geometry of the compressor blade and stage along with its tandem has been obtained from previous valid sources and has been drawn in three dimensions and numerically analyzed. Then the various parameters for the blade and the tandem are examined separately and the pressure and velocity vectors are plotted to show the control of the vortices, which results in improved compressor performance. The characteristic curve of the compressor and the pressure ratio for this particular tandem are also plotted at the end. Calculations show that by using the tandem and removing the excess vortex after the main blade, we will see a 28.5% increase in total pressure, a 15% decrease in relative mach number and a 1.5% decrease in entropy.

Keywords

Main Subjects

Article Title [Persian]

Improving the performance and work-absorbing capacity of the axial-flow compressor by using tandem blades.

Authors [Persian]

  • Alireza Sekhavat Benis
  • Reza Aghaei Togh

Islamic Azad University Science and Research Branch

Abstract [Persian]

The compressor blade is responsible for increasing the flow pressure. By adding a blade behind the main blade, the compressor performance can be improved by increasing the pressure ratio and reducing the weight. The tandem improves the performance and increases the compressor absorption coefficient by increasing the pressure ratio, preventing flow separation and controlling the boundary layer. This has led compressor designers to seek to reduce weight, increase pressure ratio and increase efficiency by using tandem. The geometry of the compressor blade and stage along with its tandem has been obtained from previous valid sources and has been drawn in three dimensions and numerically analyzed. Then the various parameters for the blade and the tandem are examined separately and the pressure and velocity vectors are plotted to show the control of the vortices, which results in improved compressor performance. The characteristic curve of the compressor and the pressure ratio for this particular tandem are also plotted at the end. Calculations show that by using the tandem and removing the excess vortex after the main blade, we will see a 28.5% increase in total pressure, a 15% decrease in relative mach number and a 1.5% decrease in entropy.

Keywords [Persian]

  • Compressor
  • Rotor
  • Tandem
  • Compressor characteristics
  • Performance improving
References
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[6] McGlumphy, J., Ng, W., Wellborn, S. R., and Kempf, S. (March 25, 2010). "3D Numerical Investigation of Tandem Airfoils for a Core Compressor Rotor." ASME. J. Turbomach.July 2010;132(3): 031009. https://doi.org/10.1115/1.3149283
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[8] Rzadkowski, Romuald & Gnesin, V.I. & Kolodyazhnaya, Luba. (2013). Unsteady Forces Acting on Rotor Blades in Five and Half Compressor Stage. Advances in Vibration Engineering. 12. 287-301.
[9] M., Rajadurai & Mohanasundaram, R & Revathi, M & Karthikeyan, A. (2014). 3D Computational Studies of Low-Speed Axial Flow Compressor Rotor Incorporating Tandem Blades. International Journal of Engineering Research and Development. 10. 2278-800.
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[13] Baojie LIU, Chuanhai ZHANG, Guangfeng AN, Du FU, Xianjun YU, Using tandem blades to break loading limit of highly loaded axial compressors,Chinese Journal of Aeronautics, Volume 35, Issue 4, 2022,Pages 165-175, ISSN 1000-9361, https://doi.org/10.1016/j.cja.2021.07.031.
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Journal of Aerospace Science and Technology
Volume 16, Issue 1
June 2023
Pages 146-158
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