دانشگاه تربیت دبیر شهید رجائی
انتشارات دانشگاه تربیت دبیر شهید رجائی

  اخبار و اعلانات

 آمار

تعداد نشریات11
تعداد شماره‌ها210
تعداد مقالات2,098
تعداد مشاهده مقاله2,877,161
تعداد دریافت فایل اصل مقاله2,084,970
Abbasi, Sarallah, Joodaki, Ali. (1399). Parametric study on axial compressor performance in design condition. فناوری آموزش, 10(1), 271-279. doi: 10.22061/jcarme.2019.3614.1420
Sarallah Abbasi; Ali Joodaki. "Parametric study on axial compressor performance in design condition". فناوری آموزش, 10, 1, 1399, 271-279. doi: 10.22061/jcarme.2019.3614.1420
Abbasi, Sarallah, Joodaki, Ali. (1399). 'Parametric study on axial compressor performance in design condition', فناوری آموزش, 10(1), pp. 271-279. doi: 10.22061/jcarme.2019.3614.1420
Abbasi, Sarallah, Joodaki, Ali. Parametric study on axial compressor performance in design condition. فناوری آموزش, 1399; 10(1): 271-279. doi: 10.22061/jcarme.2019.3614.1420

Parametric study on axial compressor performance in design condition

Journal of Computational & Applied Research in Mechanical Engineering (JCARME)
مقاله 20، دوره 10، شماره 1 - شماره پیاپی 19، آذر 2020، صفحه 271-279    اصل مقاله (1.25 M)
نوع مقاله: Research Paper
شناسه دیجیتال (DOI): 10.22061/jcarme.2019.3614.1420
نویسندگان
Sarallah Abbasi* 1؛ Ali Joodaki2
1School of Mechanical Engineering, Arak University of Technology, Arak, 38181-41167, Iran
2University of Ayatollah Alozma Boroujerdi, Mechanical Engineering, Borujerd, Iran
تاریخ دریافت: 17 اردیبهشت 1397،  تاریخ بازنگری: 18 بهمن 1397،  تاریخ پذیرش: 01 اسفند 1397 
چکیده
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.
کلیدواژه‌ها
Axial compressor؛ Streamline curvature method؛ Blade geometry؛ Design condition
مراجع

[1] S. J. Gallimore, J. J Bolger, and N. A. Cumpsty, 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] E. Benini, and R. Biollo, On the Aerodynamics of Swept and Leaned Transonic Compressor Rotors. ASME Turbo Expo, Spain, GT2006-90547, (2006).

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

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

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

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

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

[8] M. Batti, V. Patel, 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] R. J. Roelke, and, J. E. Haas, 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] M. Zheng, Y. Li, H. 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] C. Sarraf, H. Nouri, F. Ravelet, F. Bakir, 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] B. Lakshminarayana, Fluid Dynamics and Heat Transfer of Turbomachinery. John Wiley & Sons, New York, (1996).

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

[15] J. F. Hu, H. Ou-Yang, X. ZHu, 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] 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).

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

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

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

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

[21] J. A. Storer, and N. Cumpsty, 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] 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).

آمار
تعداد مشاهده مقاله: 902
تعداد دریافت فایل اصل مقاله: 882


سامانه مدیریت نشریات علمی. طراحی و پیاده سازی از سیناوب