Effect of blade profile on the performance characteristics of axial compressor in design condition

Abbasi, Sarallah; Joodaki, Ali

doi:10.22061/jcarme.2018.3168.1349

تعداد نشریات	11
تعداد شماره‌ها	228
تعداد مقالات	2,321
تعداد مشاهده مقاله	3,651,973
تعداد دریافت فایل اصل مقاله	2,683,242

	Effect of blade profile on the performance characteristics of axial compressor in design condition
Journal of Computational & Applied Research in Mechanical Engineering (JCARME)
مقاله 10، دوره 9، شماره 2 - شماره پیاپی 18، فروردین 2020، صفحه 287-296 اصل مقاله (1.52 M)
نوع مقاله: Research Paper
شناسه دیجیتال (DOI): 10.22061/jcarme.2018.3168.1349
نویسندگان
Sarallah Abbasi^* ¹؛ Ali Joodaki²
¹School of Mechanical Engineering, Arak University of Technology, Arak, 38181-41167, Iran
²Faculty of Engineering, University of Ayatollah Alozma Boroujerdi, Boroujerd, Iran
تاریخ دریافت: 25 آذر 1396، تاریخ بازنگری: 08 آبان 1397، تاریخ پذیرش: 13 آبان 1397
چکیده
The choice of geometrical shape of the blades has a considerable effect on aerodynamic performance and flow characteristics in axial compressors. In this paper, the effects of the blades shape on the aerodynamic design characteristics are investigated based on Streamline Curvature Method (SCM). Initially, the Streamline Curvature Method (SCM) is used for designing a two-stage axial compressor. Comparing the current results with experimental ones indicates good agreement. The first stage of the axial compressor is selected with three different blade profiles. The first case (case I) has the polynomial camber with naca thickness distribution series 6. The second case (case II) has the standard naca profile series 6 and the third case (case III) has the modified standard naca profile series 4. Results reveal that using the standard airfoils in the stators leads to improved flow conditions such as loss coefficient and pressure ratio. On the contrary, this profile selection may cause an increase in the stagger angle that is not favorable. Aerodynamic Design with a polynomial camber line in the rotor demonstrates a better aerodynamic behavior in loss coefficient, pressure ratio and diffusion factor. Whilst the use of such a camber line in the stator leads to the formation of less favorable aerodynamics conditions in comparison to the standard airfoil.
کلیدواژه‌ها
Axial Compressor؛ Streamline Curvature Method؛ Blade Geometry؛ Design condition

مراجع
[1] R.N. Sharma, “Economics of mine ventilation,” In Proceedings of International Conference on Mineral Industry: Issues on Economics, Environment and Technology (pp. 75–87). India: The Mining, Geological and Metallurgical Institute of India, (2002). [2] B. Eck, Fans; “design and operation of centrifugal, axial flow,” and cross-flow fans, Oxford: Pergamon Press, (1973). [3] P.K. Sen, “Reducing power consumption for axial flow mine ventilation fans,” Journal of Mines, Metals and Fuels, Vol.45, No. (9–10), pp. 301–303, (1997). [4] W.A. Hustrulid & R.L. Bullock, “Underground mining methods: engineering fundamentals and international case studies,” Englewood, CO: Society for Mining, Metallurgy and Exploration, (2001). [5] J. Herricl, E. ameesm, and E. Johnr, “Systematic Two-Dimensional Cascade Tests of NACA 65-Series Compressor Blades at Low Speeds,” NACA-TR-1368, (1951). [6] I. Felixr, “Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique, NACA-TN-3913, (1954). [7] Mellorg, “Aerodynamic Performance of Axial Compressor Cascades with Application to Machine Design,” MIT Gas Turbine Lab, Report No. 3S, (1957). [8] B. Lakshminarayana, “Fluid Dynamics and Heat Transfer of Turbomachinery,” John Wiley & Sons, New York, (1996). [9] V. Pachidis, “Prediction of engine Performance under Compressor inlet Flow Distortion Using Streamline Curvature,” J. Eng. Power, Vol. 89, No. 4, pp. 478-490, (2006). [10] Hearsey، R. M, “Practical Compressor Aerodynamic Design, Advanced Topics in Turbomachinery Technolog,” Principal Lecture Series No. 2, Concepts ETI, 1986. [11] I. Templalexis, P. Pilidis, V. Pachidis, and P. Kotsiopoulos, “ Development of a Two-Dimensional Streamline Curvature Code,” J. Turbomach, Vol. 133, No. 1, 0110031-7, (2011). [12] J. F. Hu, H. Ou-Yang, X. Ch. ZHu, X. Q. Qiang, and Z. Du, “An improved streamline curvature approach for transonic axial compressor performance prediction,” J. Aerospace Engineering Vol. 225, No. 5, 575-584, (2011). [13] W. Gong, R. Kang, W. Bin Zhang, “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). [14] C.C. Koch, L. H. Smith, “Loss Sources and Magnitudes in Axial Flow Compressors,” Transactions of the ASME, Journal of Engineering for Power, Vol. 98, No. 3, pp. 411-424, (1976). [15] W. C. Swan, “A Practical Method Of Predicting Transonic-Compressor Performance,” Journal of Engineering for Power, Vol. 83, No. 3, pp. 322–330, (1958). [16] H. R. Griepentrog, “Secondary Flow Losses in Axial Compressors,” AGARD LS 39, (1970). [17] JA Storer and NA cumpsty, “An approximation analysis and prediction method for tip clearance loss in axial compressors,” J. Turbomach, Vol. 116, NO. 4, pp. 648-656, (1994). [18] S. Lieblein, “Incidence and Deviation-Angle Correlations for Compressor Cascades,” J. Basic Eng Vol. 82, No. 3, pp. 575-584, (1960). [19] NA. Cumpsty, “Compressor aerodynamics,” John Wiley & Sons. New York, (1989). [20] D. C. Urasek, T. G. William, W. S. Cunnan, “ Performance Of a Two Stage Fan Having Low Aspect Ratio First Stage Rotor Blading,” NASA Technical Paper 1493, (1979). [21] G. R. Frost, R. M. Hearsey, A. J. Wennerstrom, “a computer program for the specification of axial compressor airfoils,” project 7065, Aerospace Research Laboratories, (1972). [22] I.H. Abbott, A.E. Von Doenhoff, “Theory of Wing Sections: Including a Summary of Airfoil Data,” (1959).
آمار تعداد مشاهده مقاله: 1,453 تعداد دریافت فایل اصل مقاله: 1,700

سامانه مدیریت نشریات علمی. طراحی و پیاده سازی از سیناوب

پیوندهای مفید

آمار

Effect of blade profile on the performance characteristics of axial compressor in design condition