Document Type : Original Article


Islamic Azad University Science and Research Branch


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.


Main Subjects

[1] U.K. Saha, B. Roy, Experimental investigations on tandem compressor cascade performance at low speeds, Experimental Thermal and Fluid Science, Volume 14, Issue 3, 1997, Pages 263-276, ISSN 0894-1777,
[2] Reza Shams Aldini Lori, Abulqasem Masgarportousi, Hamza Eshraghi, Transient Numerical Analysis of Single Stage Tandem Compressor, Amirkabir Mechanical Engineering Journal, Volume 51, Number 2, 2018, Pages 399 to 411
[3] M. Eftari, H. Javaniyan, M.R. Shahhoseini, F. Ghadak ,M. Rad, Performance Modeling and Examination of Losses in the Axial -Flow Compressor, JAST. Vol. 9, No. 1, pp 75-86
 [4] Carstens, V., Kemme, R., & Schmitt, S. (2003). Coupled simulation of flow-structure interaction in turbomachinery. Aerospace Science and Technology, 7, 298-306.
[5] McGlumphy, J., Ng, W., Wellborn, S. R., and Kempf, S. (February 3, 2009). "Numerical Investigation of Tandem Airfoils for Subsonic Axial-Flow Compressor Blades." ASME. J. Turbomach. April 2009; 131(2): 021018.
[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.
[7] Jonathan McGlumphy, Wing-Fai Ng, Steven R. Wellborn, Severin Kempf, 3D Numerical Investigation of Tandem Airfoils for a Core Compressor Rotor, Journal of Turbomachinery, JULY 2010.
[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.
[10] Ahmed, Mohamed & Owis, Farouk & Hashim, Ali. (2017). The Impact of Tandem Rotor Blades on the Performance of Transonic Axial Compressors. Aerospace Science and Technology. 67. 10.1016/j.ast.2017.04.019.
[11] Pan, Ruochi & Song, Zhaoyun & Liu, Bo. (2020). Optimization Design and Analysis of Supersonic Tandem Rotor Blades. Energies. 13. 3228. 10.3390/en13123228.
[12] Е. V. doroshenko, Yu. M. tereshchenko, Yu. Yu. tereshchenko, А. o. kushchinskiy, Aeroacoustics Characteristics of the Axial Compressor Stage with tandem impeller, Geotechnical and Mining Mechanical engineering, Machine Building. DOI:10.29202/nvngu/2019­1/9
[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,
[14] Sushanlal Babu, Probuddho Chatterjee , and Pradeep A M , "Transient nature of secondary vortices in an axial compressor stage with a tandem rotor", Physics of Fluids (in press) (2022);
[15] J. A. Brent, J. G. Cheatham, and D. R. Clemmons, single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors, part v - analysis and design of stages d and e, december1972, pratt & whitney aircraft, division of united aircraft corporation, florida research and development center, prepared for national aeronautics and space administration, NASA Lewis Research Center, Contract NAS3-11158.
[16] Wilcox, D. C.,’ Turbulence Modeling for CFD’, 2nd edition ed. DCW Industries Inc., 1998.
[17] Yue, S., Wang, Y. & Wang, H. Design and Optimization of Tandem Arranged Cascade in a Transonic Compressor. J. Therm.Sci. 27, 349–358(2018).
[18] H. Cohen, CFC Rogers, HIH Saravanamutto, Gas Turbine Theory, Longman Group limited, 1996, P.179.