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Analysis of Aerodynamic Performance in an Annular Compressor Bowed Cascade with Large Camber Angles

Chen, Shaowen    (School of Energy Science and Engineering Harbin Institute of Technology   ); Chen, Fu    (School of Energy Science and Engineering Harbin Institute of Technology  );
  • 초록

    The effects of positively bowed blade on the aerodynamic performance of annular compressor cascades with large camber angle were experimentally investigated under different incidences. The distributions of the exit total pressure loss and secondary flow vectors of compressor cascades were analyzed. The static pressure was measured by tapping on the cascade surfaces, and the ink-trace flow visualizations were conducted. The results show that the value of the optimum bowed angle and optimum bowed height decrease because of the increased losses at the mid-span with the increase of the caber angle. The C-shape static pressure distribution along the radial direction exists on the suction surface of the straight cascade with large r camber angles. When bowed blade is applied, the larger bowed angle and larger bowed height will further enhance the accumulation of the low-energy fluid at the mid-span, thus deteriorate the flow behavior. Under $60^{\circ}$ camber angle, flow behavior near the end-wall region of some bowed cascades even deteriorates instead of improving because the blockage of the separated flow near the mid-span keeps the low-energy fluid near the end-walls from moving towards the mid-span region, and as a result, a rapid augmentation of the total loss is easy to take place under large bowed angle. With the increase of camber angle, the choice range of bowed angle corresponding to the best performance in different incidences become narrower.


  • 주제어

    Cascade experiment .   compressor .   camber angle.  

  • 참고문헌 (8)

    1. Bryce, H. D., Cherrett, M. A., Lyes, P. A., 1995, Three-dimensional flow in a highly loaded single-stage transonic fan,” ASME Journal of Turbomachinery, Vol. 117, No. 2, pp. 22-25. 
    2. Emmerson, P. R., 1996, Three-dimensional flow calculations of the stator in a highly loaded transonic fan,”ASME Turbo Expo, Amsterdam, Birmingham , 96-GT-546. 
    3. Carter, C. J., Guillot, S. A., Ng, W. F., 2001, Aerodynamic performance of a high-turning compressor stator with flow control, AIAA Paper, 2001-3973. 
    4. WANG, Z. Q., SU, J. X., ZHONG, J. J., 1994, New progress of investigation into mechanism of reducing energy loss in cascades with curved and twisted blades, Journal of Engineering Thermophysics, 15(2): 40-44 (in Chinese) 
    5. Wang, H. S., Zhong, J. J., 2002, Wang, Z. Q., Effects of blade positive curving on aerodynamic performance of compressor cascades, Journal of Propulsion Technology, Vol. 23, No. 4, pp. 321-324. 
    6. Breugelmans, F. A. E., 1985, Influence of incidence angle on the secondary flow in compressor cascade with different dihedral distribution, Beijing, ISABE Paper 85-7078. 
    7. Sasaki, T., Breugelmans, F. A. E., 1998, Comparison of sweep and dihedral effects on compressor cascade performance, Transactions of ASME Journal of Turbormachinary, Vol. 120, No. 4, pp. 454-463. 
    8. Wang, D., 2001, Experimental investigations of blade curving effect on aerodynamic characteristics of compressor cascades, Ph. D. Thesis, Department of Energy Science and engineering, Harbin Institute of Technology, Harbin, China. 

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