Passive control of hub-corner separation/stall using axisymmetric-hub contouring

Abstract

Numerical simulations were performed to investigate the forming mechanism of the compressor/fan hub-corner separation/stall. Taking the small-scaled vortex in the detached regions into account, scale adaptive simulation model coupled with shear stress transport model (SAS–SST turbulence model) does well in capturing the flow structures in the compressor. At near stall condition, low-momentum stall cell originates from the leading edge of the stator near hub, contributes to the greater turning angle at the suction side because of endwall viscosity, rolls, and lifts up in spanwise direction. The same then interacts with the wake in the downstream passage of stator, nearly taking up the whole passage downstream. Three vortex centres are generated at the hub induced by the boundary layer separation flow, one near the stator leading edge, a second one at the blade trailing edge near the suction side, and a third one near the middle passage, and further swirled up to the blade suction surface which can be recognized as thepassage vortex developed by the radial and circumferential pressure differences. Axisymmetric-hub contouring (a type of passive flow control techniques) has resulted in performance improvement of the compressor. Main contribution of performance enhancement is attributed to the suppression of hub-corner separation. Significant influence of axisymmetric contouring has been found on boundary layer separation structures near hub and passage vortex, which affects the formation and development of hub-corner stall.

Keywords

compressor/fan hub-corner separation/stall SAS–SST model axisymmetric-hub contouring

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References

Yanfeng, Z. Investigation of endwall flow behaviour and its control strategies in highly-loaded compressor. PhD Dissertation, Northwestern Polytechnical University, People's Republic of China, 2009.

Lewin, E., Kožulovic, D., and Stark, U. Experimental and numerical analysis of hub-corner stall in compressor cascades. ASME paper no. GT2010-22704, 2010.

Horlock, J., Percival, P., Louis, J., and Lakshminarayana, B. Wall stall in compressor cascades. ASME paper no. 64-WA/FE-29, 1964.

Lucke, J. R., Sanz, W., Benestschik, H., Gallus, H. E., and Platzer, M. F. Numerical investigation of transition and hub-corner stall phenomena inside an annular compressor cascade. AIAA paper no. 96-2655, 1996.

Hah

Loellbach

Development of hub corner stall and its influence on the performance of axial compressor blade rows. ASME J. Turbomach., 1999, 121, 67–77.

Weber, A., Schreiber, H.-A., Fuchs, R., and Steinert, W. 3-D transonic flow in a compressor cascade with shock-induced corner stall. ASME paper no. GT2001-0345, 2001.

Gbadebo, S. A., Cumpsty, N. A., and Hynes, T. P. Three-dimensional separations in axial compressors. ASME paper no. GT2004-53617, 2004.

Lei

V. M.

Spakovszky

Z. S.

Greitzer

E. M.

A criterion for axial compressor hub-corner stall. ASME J. Turbomach., 2008, 130, 031006.1–031006.10.

Jialing

L. U.

Wuli

C. H. U.

Junqiang

Z. H. U.

Zhiwei

L. I. U.

Application and development of endwall contouring in turbomachinery (in Chinese). J.Engng Therm. Energy Power, 2009, 24(6), 687–691.

10.

Dorfner, C., Nickee, E., and Voss, C. Axisasymmetric profiled endwall design using multiobjective optimization linked with 3D RANS-flow-simulations. ASME paper no. GT2007-27268, 2007.

11.

Dorfner

Hergt

Nicke

Moenig

Advanced non-axisymmetric endwall contouring for axial compressors by generating an aerodynamic separator – Part I: principal cascade design and compressor application. J. Turbomach., 2011, 133, 021026-1–021026-1.

12.

Hergt

Dorfner

Steinert

Nicke

Schreiber

H.-A.

Advanced non-axisymmetric endwall contouring for axial compressors by generating an aerodynamic separator – Part II: experimental and numerical cascade investigation. J. Turbomach., 2011, 133, 021027-1–021027-1.

13.

Jialing, L. U., Wuli, C. H. U., and Yanhui, W. U. Effects of endwall profiling on axial flow compressor stage. ASME paper no. GT2009-59418, 2009.

14.

Hoeger, M., Cardamone, P., and Fottner, L. Influence of endwall contouring on the transonic flow in a compressor blade. ASME paper no. GT-2002-30440, 2002.

15.

Menter, F. R. and Egorov, Y. Revisiting the turbulent scale equation. In Proceedings of IUTAM Symposium on One hundred years of boundary layer research, Göttingen, Germany, 12–14 August 2004.

16.

Menter, F. and Egorov, Y. SAS turbulence modelling of technical flows. In Proceedings of the Sixth International ERCOFTAC Workshop on Direct andlarge eddy simulation VI, University of Poitiers,France, 12–14 September 2006, Springer, available from http://www.springerlink.com/index/T3323WML93L271HN.pdf.

17.

Menter, F. R, Kuntz, M., and Bender, R. A scale-adaptive simulation model for turbulent flow predictions. AIAA paper no. 2003-0767, 2003.

18.

Menter, F. R. and Egorov, Y. A scale-adaptive simulation model using two-equation models. In Proceedings of the 43rd Aerospace sciences meeting and exhibit, Reno, Nevada, 10–13 January 2005, AIAA paper no. 2005-1095.

19.

Menter, F. R. and Egorov, Y. Turbulence modeling of aerodynamic flows. International aerospace CFD conference, Paris, France, 18–19 June 2007.