Journal of Computational & Applied Research in Mechanical Engineering (JCARME)

Document Type : Research Paper

Authors

Sarallah Abbasi ¹
Ali Joodaki ²

¹ School of Mechanical Engineering, Arak University of Technology, Arak , Iran

² The university University of Ayatollah ozma Boroujerdi at Iran

https://doi.org/10.22061/jcarme.2019.3614.1420

Abstract

In This paper, a parametric study of compressor performances was performed by streamline curvature method (SLC). Effects of three input parameters in design process, e.g., number of blades, distribution of blade thickness, and blade sweep angels, on the main objective parameters in aerodynamic design, e.g., velocity distribution, efficiency and pressure ratio, has been investigated in the parametric study. Initially, a certain two stage axial compressor has been designed by SLC. Validation of the results is confirmed by comparing the obtained results with the experimental ones. Regarding various values for aforementioned input parameters, the first stage of the axial compressor is redesigned and the output parameter is established. Therefore, the sensitivity of the design results to each of the aforementioned parameters is recognized. Results show that increasing the blades sweep angle causes to improve the flow behavior such as efficiency and pressure ratio in axial fan and reducing it have a completely contrary result. Also, reducing the rotors blades number leads to an increase in the pressure ratio and efficiency while its increase cause to a contrary result. , it is concluded that reduction in the blades number has the stronger effect on the performance parameters than its increment. The results also show that effect of the thickness in the hub is greater than the thickness of the tip and its increase leads to reduce both efficiency and pressure ratio.

Graphical Abstract

Keywords

dor

20.1001.1.22287922.2020.10.1.20.5

Main Subjects

Aerodynamics

References

[1] Gallimore, S. J., Bolger, J. J. ‌ and Cumpsty, N. A., The Use of Sweep and Diahedral in Multistage Axial Flow Compressor Blading. Part 1: University Research and Methods Development, Proceedings of ASME Turbo Expo, Amsterdam, the Netherlands, GT-2002-30328, (2002).

[2] Benini, E., and Biollo, R., On the Aerodynamics of Swept and Leaned Transonic Compressor Rotors. ASME Turbo Expo, Spain, GT2006-90547, (2006).

[3] Denton, J. D. and Xu, L., The Effects of Lean and Sweep on Transonic Fan Performance. Proceedings of ASME Turbo Expo, Amsterdam, The Netherlands, GT-2002- 30327.

[4] Cai, N., Xu, J. and Benaissa, A., Aerodynamic and Aeroacoustic Performance of a Skewed Rotor. Proceedings of ASME Turbo Expo, Atlanta, GA, GT-2003-38592, (2003).

[5] Fischer, A., Riess, W. and Seume, J., Performance of Strongly Bowed Stators in a 4-Stage High Speed Compressor. Proceedings of ASME Turbo Expo, Atlanta, GA, GT-2003-38392, (2003).

[6] Samad, A. and Kim, K. Y., Multi-objective optimization of an axial compressor blade. Journal of Mechanical Science and Technology, Vol. 22, No. 5, pp. 999-1007, (2008).

[7] Hao,C., Fang, Z., Donghai,J., Xingmin, G., Effect of blade sweep on inlet flow in axial compressor cascades, Chinese Journal of Aeronautics, Volume 28, No. 1, pp. 103-111, (2015).

[8] batti, M., Patel, V., Optimization of number of blade in high pressure compressor, International Journal of Emerging Technology and Advanced Engineering, Vol. 4, No. 6, pp. 287-292, (2014).

[9] Roelke, R. J. And, Haas, J. E., The Effect of Rotor Blade Thickness and Surface Finish on the performance of a Small Axial Flow Turbine. Gas Turbine Annual Meeting sponsored by American Society of Mechanical Engineers, London, England, April 18-22, (1982).

[10] Zheng, M., Li, Y., Teng, H., Hu, J., Tian, Z., Zhao, Y. , Effect of blade number on performance of drag type vertical axis wind turbine, Applied Solar Energy, 52(4):315-320, 2016 with 534 Reads.

[11] Sarraf, C., Nouri, H., Ravelet, F., Bakir, F., Experimental study of blade thickness effects on the global and local performances of a Controlled Vortex Designed axial flow fan. Experimental Thermal and Fluid Science, Vol. 35, No. 4, pp. 684-693, (2011).

[12] Lakshminarayana B., Fluid Dynamics and Heat Transfer of Turbomachinery. John Wiley & Sons, New York, (1996).

[13] Pachidis, V., Prediction of engine Performance under Compressor inlet Flow Distortion Using Streamline Curvature. J. Eng. Gas Turbines Power, Vol. 129, No. 1, pp. 97-103, (2007).

[14] Hearsey,R. M., Practical Compressor Aerodynamic Design. Advanced Topics in Turbomachinery Technology, Principal Lecture Series No. 2، Concepts ETI, (1986).

[15] Hu, J. F., Ou-Yang, H., ZHu, X. Ch., Qiang, X. Q. and Du, Z., An improved streamline curvature approach for transonic axial compressor performance prediction. J. Aerospace Engineering, Vol. 225, No. 5, pp. 575-584, (2011).

[16] Gong, W., Kang, R., Bin Zhang, W., A new finite difference method to solve the velocity gradient equation in streamline curvature method. Advances in Mechanical Engineering, Vol. 8, No. 9, pp. 1–13, (2016).

[17] Swan, W., A practical method of predicting transonic compressor performance. ASME J. Eng. Power, Vol. 83, pp. 322-330, (1976).

[18] Griepentrog, H., Secondary flow losses in axial compressors. AGARD LS 39, (1970).

[19] Cumpsty N. A., Compressor Aerodynamics. John Wiley & Sons, New York, (1989).

[20] Lieblein, S., Incidence and Deviation-Angle Correlations for Compressor Cascades J. Basic Eng, Vol 82, No. 3, pp. 575-584, (1960).

[21] Storer, J.A AND cumpsty, N., an approximation analysis and prediction method for tip clearance loss in axial compressors. Transactions of the ASME, Journal of Turbomachinery, Vol 116, pp. 648-656, (1994).

[22] Urasek, D. C., William, T. G., Cunnan, W. S., Performance of a Two Stage Fan Having Low Aspect Ratio First Stage Rotor Blading. NASA Technical Paper 1493, (1979).

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