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Stall Inception and Development Process Due to Tip Leakage Flow in Axial Compressor Rotor Blades Row

Published online by Cambridge University Press:  13 March 2014

R. Taghavi-Zenou ,
S. Abbasi  and
S. Eslami
R. Taghavi-Zenou*
Affiliation:
School of Mechanical Engineering, Iran University of Science and TechnologyNarmak, Tehran 16877, Iran
S. Abbasi
Affiliation:
School of Mechanical Engineering, Iran University of Science and TechnologyNarmak, Tehran 16877, Iran
S. Eslami
Affiliation:
School of Mechanical Engineering, Iran University of Science and TechnologyNarmak, Tehran 16877, Iran
*
[email protected]
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Abstract

This paper deals with tip leakage flow structure in subsonic axial compressor rotor blades row under different operating conditions. Analyses are based on flow simulation utilizing computational fluid dynamic technique. Three different circumstances at near stall condition are considered in this respect. Tip leakage flow frequency spectrum was studied through surveying instantaneous static pressure signals imposed on blades surfaces. Results at the highest flow rate, close to the stall condition, showed that the tip vortex flow fluctuates with a frequency close to the blade passing frequency. In addition, pressure signals remained unchanged with time. Moreover, equal pressure fluctuations at different passages guaranteed no peripheral disturbances. Tip leakage flow frequency decreased with reduction of the mass flow rate and its structure was changing with time. Spillage of the tip leakage flow from the blade leading edge occurred without any backflow in the trailing edge region. Consequently, various flow structures were observed within every passage between two adjacent blades. Further decrease in the mass flow rate provided conditions where the spilled flow ahead of the blade leading edge together with trailing edge backflow caused spike stall to occur. This latter phenomenon was accompanied by lower frequencies and higher amplitudes of the pressure signals. Further revolution of the rotor blade row caused the spike stall to eventuate to larger stall cells, which may be led to fully developed rotating stall.

Keywords

Axial compressorSpike stall inceptionTip leakage flowFrequency spectrum
Type
Research Article
Information
Journal of Mechanics , Volume 30 , Issue 3 , June 2014 , pp. 307 - 313
Copyright
Copyright © The Society of Theoretical and Applied Mechanics, R.O.C. 2014 

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References

REFERENCES

1.Day, I. J., “Stall Inception in Axial Flow Compressors,” Journal of Turbomachinery, ASME, 115, pp. 1–9 (1993).Google Scholar
2.Chen, J., “Flow Instability and its Control in Compression Systems,” Journal of Thermal Science, 12, pp. 1–9 (2002).Google Scholar
3.Moore, F. K. and Greitzer, E. M., “A Theory of Post-Stall Transients in Axial Compression Systems, Part I — Development of Equations, Part II — Applications,” Journal of Engineering for Gas Turbines and Power, 108, pp. 231–239 (1986).Google Scholar
4.Spakovszky, Z., “Application of Axial and Radial Compressor Dynamic System Modeling,” Ph.D. Dissertation, Massachusetts Institute of Technology U.S.A. (2001)Google Scholar
5.Outa, E., “Rotating Stall and Stall-Controlled Performance of a Single Stage Subsonic Axial Compressor,” Journal of Thermal Science, 15, pp. 1–13 (2006).Google Scholar
6.He, L., “Computational Study of Rotating Stall Inception in Axial Compressors,” Journal of Propulsion and Power, 13, pp. 31–38 (1997).Google Scholar
7.Ismail, J. O. and He, L., “Three Dimensional Computation of Rotating Stall Inception,” Proceedings of the 2nd European Turbomachinery Conference, Antwerpen (1997).Google Scholar
8.Hoying, D. A., Tan, C. S. and Vo, H. D., et al., “Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception,” Journal of Turbomachinery, ASME, 121, pp. 735–742 (1999).Google Scholar
9.Hah, C., Rabe, D. C. and Wadia, A. R., “Role of Tip-Leakage Vortices and Passage Shock in Stall Inception in a Swept Transonic Compressor Rotor,” ASME, Paper No. GT2004-53867 (2004).Google Scholar
10.Vo, H. D., Tan, C. H. and Greitzer, E. M., “Criteria for Spike Initiated Rotating Stall,“ Journal of Turbomach, ASME, 130, p. 011023 (2008).Google Scholar
11.Deppe, A., Saathoff, H. and Stark, U., Discussion: “Criteria for Spike Initiated Rotating Stall,” (Vo, H.D., Tan, C. S., Greitzer, E. M., Journal of Turbomachinery, ASME, 130, p. 011023) (2008).Google Scholar
12.Graf, M. B., Greitzer, E. M., Marble, F. E. and Sharma, O. P., “Effects of Stator Pressure Field on Upstream Rotor Performance,” ASME, Paper 99-GT-99 (1999)Google Scholar
13.Furukawa, M., Inoue, M., Saiki, K. and Yamada, K., “The Role of Tip Leakage Vortex Breakdown in Compressor Rotor Aerodynamics,” Journal of Turbomachinery, 121, pp. 469–480 (1999).CrossRefGoogle Scholar
14.Furukawa, M., Saiki, K., Yamada, K. and Inoue, M., “Unsteady Flow Behavior Due to Breakdown of Tip Leakage Vortex in an Axial Compressor Rotor at Near-Stall Condition,” ASME, Paper 2000-GT-666 (2000).Google Scholar
15.Zhang, H. W., Deng, X. Y., Lin, F., Chen, J. Y. and Huang, W. G., “A Study on the Mechanism of Tip Leakage Flow Unsteadiness in an Isolated Compressor Rotor,” ASME, Paper GT2006-91123 (2006).Google Scholar
16.Du, J., Lin, F., Zhang, H. W. and Chen, J. Y., “Numerical Investigation on the Originating Mechanism of Unsteadiness in Tip Leakage Flow for a Transonic Fan Rotor,” ASME, Paper GT2008-51463 (2008).Google Scholar
17.Tong, Z. T., Lin, F., Chen, J. Y. and Nie, C. Q., “The Self-Induced Unsteadiness of Tip Leakage Vortex and Its Effect on Compressor Stall Inception,” ASME, Paper GT2007-27010 (2007).Google Scholar
18.Geng, S., Lin, F., Chen, J., Zhang, H. and He, L., “Circumferential Propagation of Tip Leakage Flow Unsteadiness for a Low-Speed Axial Compressor,” Journal of Thermal Science, 18, pp. 202–206 (2009).Google Scholar
19.Du, J., Lin, F., Zhang, H. W. and Chen, J. Y., “Numerical Simulation on the Effect of Tip Clearance Size on Unsteadiness in Tip Clearance Flow,” Journal of Thermal Science, 17, pp. 337–342 (2008)Google Scholar
20.Inoue, M., Kuroumaru, M. and Fukuhara, M., “Behavior of Tip Leakage Flow Behind an Axial Compressor Rotor,” Journal of Turbomachinery, ASME, 108, pp.7–14 (1986).Google Scholar
21.Furukawa, M., Inoue, M., Saiki, K. and Yamada, K., “The Role of Tip Leakage Vortex Breakdown in Compressor Rotor Aerodynamics,” Journal of Turbomachinery, 121, pp. 469–480 (1999).Google Scholar