The Aerodynamic Effects of the Blade Lean on a High-Aspect-Ratio Transonic Axial Flow Rotor
Subject Areas : aerospace
Mansour
Asghari
1
()
Mohsen
Agha Seyed Mirzabozorg
2
()
Mahmood
Adami
3
()
Keywords: Adiabatic efficiency, CFD, Low-Transonic rotor, High-Aspect-Ratio, Tangentially leaned, Axial flow Compressor,
Abstract :
In this study, the effect of tangential blade lean on the aerodynamic characteristics of low-transonic, high-aspect-ratio axial flow compressor rotor has been investigated by using the computational fluid dynamics. The B-Spline curvature with four control points of 25%, 50%, 75% and 100% of span have been used to define the blade stacking line. Various leaned rotors have been created by rotating the circumferential position of control points and they have been simulated by Computational Fluid Dynamics (CFD). At the best state, the leaned blade improves the adiabatic efficiency and total pressure ratio of compressor about 0.55% and 0.75%, respectively. The results show that, lean angle at 100% span has most effect in the peak adiabatic efficiency rather than lean angle at other control points. Also, the results indicate that, in low-transonic, high-aspect-ratio rotor blades, the tangential change of the stacking line only causes the reduction of secondary flow, while the previous studies on high-transonic low-aspect-ratio rotor blades, such as NASA Rotor 37 and NASA Rotor 67 revealed the movement of shock wave toward the downstream and the reduction of the secondary flow.
[1] Weingold, H. D., Neubert, R. J., Behlke, R. F., et al., “Reduction of Compressor Stator Endwall Losses through the Use of Bowed Stators”, Journal of Turbomachinery, Vol. 111, 1997, pp. 161- 168.
[2] Sasaki, T., Breugelmans, F., “Comparison of Sweep and Dihedral Effects on Compressor Cascade Performance”, Journal of Turbomachinery, Vol. 120, 1998, pp. 454–463.
[3] Gummer, V., Wenger, U., and Kau, H. P., “Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Flow Compressor”, Journal of Turbomachinery, Vol. 123, 2001, pp. 40-48.
[4] Gallimore, S. J., Bolger, J. J., Cumpsty, N. A., et al., “The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading-Part II: Low and High-Speed Designs and Test Verification”, Journal of Turbomachinery, Vol. 124, 2002, pp. 531-541.
[5] Gallimore, S. J., Bolger, J. J., Cumpsty, N. A., et al., “The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading-Part I: University Research and Methods Development”, Journal of Turbomachinery, Vol. 124, 2002, pp. 521–532.
[6] Roy, B., Laxmiprasanna, P. A., Borikar, V., et al., “Low Speed Studies of Sweep and Dihedral Effects on Compressor Cascades”, Proceeding of ASME TURBO EXPO 2002, Amsterdam, Netherlands, Vol. 3-6, 2002, pp. GT-2002-30441.
[7] Bergner, J., Hennecke, D. K., Hoeger, M., et al., “Darmstadt Rotor No.2- Part II: Design of Lean Rotor Blades”, International Journal of Rotating Machin, Vol. 9, 2003, pp. 385–391.
[8] Fischer, A., Riess, W., and Seume, J. R., “Performance of Strongly Bowed Stators in a Four-Stage High-Speed Compressor”, Journal of Turbomachinery, Vol. 126, 2004, pp. 333-338.
[9] Ahn, C. S., Kim, K. Y., “Aerodynamic Design Optimization of a Compressor Rotor with Navier-Stockes Analysis”, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, Vol. 217, 2003, pp. 179-183.
[10] Denton, J. D., Xu, L., “The Effects of Lean and Sweep on Transonic Fan Performance”, Proceeding of ASME TURBO EXPO 2002, Amsterdam, Netherlands, Vol. 3-6, 2002, pp. GT-2002-30327.
[11] Oyama, A., Liou, M. S., and Obayashi, S. h., “High-Fidelity Swept and Leaned Rotor Blade Design Optimization using Evolutionary Algorithm”, 16th AIAA Computational Fluid Dynamics Conference, Orlando, Florida, Vol. 23-26, 2003, pp. AIAA 2003-4091.
[12] Takahashi, Y., Hamatake, H., and Katoh, Y., “Experimental and Numerical Investigations of Endwall Flow in a Bowed Compressor Cascade”, 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Tucson, Arizona, Vol. 10-13, 2005, pp. AIAA 2005-3638.
[13] Jang, Ch. M., Samad, A., and Kim, K. Y., “Optimal Design of Swept, Leaned and Skewed Blades in a Transonic Axial Compressor”, Proceedings of GT2006 ASME Turbo Expo 2006: Power for Land Sea and Air, Barcelona, Spain, Vol. 8-11, 2006, pp. GT-2006-90384.
[14] Yang, L., Hua, O., and Zhao-Hui D., “Optimization Design and Experimental Study of Low-Pressure Axial Fan with Forward-Skewed Blades”, International Journal of Rotating Machine, 2007, Article ID 85275.
[15] Zhang, Y. J., Chen, F., Guo-tai, F., et al., “Effect of Turning Angle on Flow Field Performance of Linear Bowed Stator in Compressor at Low Mach Number”, Chinese Journal of Aeronautics, Vol. 19, No. 4, 2006, pp. 271-277.
[16] Benini, E., “Three-Dimensional Multi-Objective Design Optimization of a Transonic Compressor Rotor”, AIAA Journal of Propulsion Power, Vol. 20, No. 3, 2004, pp. 559–65.
[17] Benini, E., Biollo, R., “Aerodynamics of Swept and Leaned Transonic Compressor-Rotors”, Journal of Applied Energy, Vol. 84, 2007, pp. 1012–1027.
[18] Sun, P., Han, J., Zhong, J., et al., “Effects of Bowed Stators on a Transonic Fan with Distorted Inlet”, Proceedings of ASME Turbo Expo 2008: Power for Land, Sea and Air, Berlin, Germany, Vol. 9-13, 2008, pp. GT-2008-50523.
[19] Chen, F., Li, Sh., Su, J., et al., “Experimental Study of Bowed-Twisted Stators in an Axial Transonic Fan Stage”, Chinese Journal of Aeronautics, Vol. 22, 2009, pp. 364-37.
[20] Razavi, S. R., Boroomand, M., “Optimal Design and Aerodynamics Study of Leaned Transonic Axial Flow Fan Rotors”, ASME 2014 International Mechanical Engineering Congress and Exposition, Montreal, Quebec, Canada, Vol. 14–20, 2014, pp. IMECE 2014-39796.
[21] Hutchinson, B. R., Raithby, G. D., “A Multigrid Method Based on Additive Correction Strategy”, Journal of Numerical Heat Transfer, Vol. 9, No. 5, 1986, pp. 511–37.
[22] Launder, B. E., Spalding, D. B., “The Numerical Computation of Turbulent Flows”, Journal of Computational Methods in Applied Mechanical Engineering, Vol. 3, 1974, pp. 269–289.
[23] Moore, R. D., Reid, L., “Performance of Single Stage Axial Flow Transonic Compressor with Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and with Design Pressure Ratio of 2.05”, NASA TP 1659, April 1980.