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A Method for Selection of Optimum Solidity in Design of a Tandem Compressor Blade Row

Document Type : Original Article

Author

Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

Abstract

In the current article, using results of previous researches, a guideline has been developed to select a proper value for solidity of a tandem blade row in an axial flow compressor stage. Next, using this guideline, a highly loaded tandem compressor stage has been designed. To verify the selected solidity value, some other cases have been designed with different solidity values. Other geometrical parameters have been selected similarly in all cases. At the next stage, a three dimensional numerical model is developed to predict the characteristic performance of each tandem stage. The model is validated with the experimental results of NASA Stage and Rotor 37, and the level of the accuracy of the model is presented. Using a similar model, the performance of all cases has been derived and the effect of solidity variation on the overall performance of machine has been discussed. Lastly, the effect of solidity variation on the tip leakage flow structure near peak efficiency point is discussed for all cases.

Keywords

Main Subjects

Article Title [Persian]

A Method for Selection of Optimum Solidity in Design of a Tandem Compressor Blade Row

Author [Persian]

  • Hamzeh Eshraghi

Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

Abstract [Persian]

In the current article, using results of previous researches, a guideline has been developed to select a proper value for solidity of a tandem blade row in an axial flow compressor stage. Next, using this guideline, a highly loaded tandem compressor stage has been designed. To verify the selected solidity value, some other cases have been designed with different solidity values. Other geometrical parameters have been selected similarly in all cases. At the next stage, a three dimensional numerical model is developed to predict the characteristic performance of each tandem stage. The model is validated with the experimental results of NASA Stage and Rotor 37, and the level of the accuracy of the model is presented. Using a similar model, the performance of all cases has been derived and the effect of solidity variation on the overall performance of machine has been discussed. Lastly, the effect of solidity variation on the tip leakage flow structure near peak efficiency point is discussed for all cases.

Keywords [Persian]

  • Solidity
  • Compressor
  • Tandam
  • CFD
  • NASA-37
References
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[2] Brent, JA., and Clemmons, DR., “Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors. Part VIII: Final report,” NASA Lewis Research Center, NASA CR-134713, 1975.
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[8] Eshraghi, H., Boroomand, M., and Tousi, A.M., “Design and Analysis of a Highly Loaded Tandem Compressor Stage,” ASME 2014 International Mechanical Engineering Congress and Exposition, Montreal, Quebec, Canada, 2014, pp. V001T01A071. doi:10.1115/IMECE2014-39750
[9] M. Mohsen, F. M. Owis, A. A. Hashim, “The impact of tandem rotor blades on the performance of transonic axial compressors,” Aerospace Science and Technology, Vol. 67, 2017, pp. 237-248. doi: 10.1016/j.ast.2017.04.019
[10] Yue S, Wang Y, Wang H. “Design and optimization of tandem arranged cascade in a transonic compressor,” Journal of Thermal Science, Vol. 27, No. 4, 2018, pp.349-358. doi: 10.1007/s11630-018-1013-4
[11] Song Z, Liu B. “Optimization design for tandem cascades of compressors based on adaptive particle swarm optimization,” Engineering Applications of Computational Fluid Mechanics, Vol. 12, No. 1, 2018, pp.535-552. doi: 10.1080/19942060.2018.1474806
[12] Yang Z, Liu B, Mao X, Zhang B, Wang H. “Research on the Influence of Inflow Conditions on the Aerodynamic Performance of a Tandem Cascade,” Journal of Applied Fluid Mechanics, Vol 15. No. 6, 2022, pp.1745-1758. doi: 10.47176/jafm.15.06.1206
[13] Tournier, J.M., El-Genk, MS., “Axial flow, multi-stage turbine and compressor models,” Energy Conversion and Management, Vol. 51, No. 1, 2010, pp.16-29. doi:10.1016/j.enconman.2009.08.005
[14] Reid, L., and Moore, R.D., “Design and Overall Performance of Four Highly Loaded, High-Speed Inlet Stages for an advanced High-Pressure-Ratio Core Compressor,” NASA Lewis Research Center, NASA Technical Paper 1337, 1978.
[15] Suder, K. L., ” Experimental investigation of the flow field in a transonic, axial flow compressor with respect to the development of blockage and loss,” NASA Lewis Research Center, NASA Technical Memorandum 107310, 1996.
Journal of Aerospace Science and Technology
Volume 16, Issue 1
June 2023
Pages 16-30
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