Fluid Mechanics and Flight Mechanics

Research progresses of stall precursor-suppressed casing treatment

  • SUN Xiaofeng ,
  • SUN Dakun
Expand
  • School of Energy and Power Engineering, Beihang University, Beijing 100191, China

Received date: 2015-05-22

  Revised date: 2015-06-03

  Online published: 2015-09-29

Supported by

National Natural Science Foundation of China (51236001, 51106154); National Basic Research Program of China (2012CB720201); Aeronautical Science Foundation of China (2014ZB51018)

Abstract

Modern aeroengine has been developed for high thrust to weight ratio, so the fan/compressor must support higher blade loading. Under this situation, it becomes more and more difficult to meet stall margin requirements. The casing treatment is one of the most effective ways to enhance the stall margin. A kind of casing treatment, named stall precursor-suppressed (SPS), has been developed recently. The stall inception model can be used to determine the variation range of the stall margin improvement with the SPS casing treatment for both subsonic fan and transonic compressor. The model predicts that 7.6% and 6.8% of stall margin improvement (SMI) can be achieved in a subsonic fan TA36 and a transonic compressor J69 Stage, respectively. The effectiveness of the SPS casing treatment is investigated and the experimental results show that the SPS casing treatment can achieve 5.5% and 9.3% of the SMI in TA36 and J69 Stage, respectively. Due to the fact that the distributions of the total pressure ratio along the spanwise are kept the same as those of the solid wall casing at the same mass flow rate, the SPS casing treatments with a small open area ratio and large backchamber enhance the stall margin without an obvious efficiency loss and a change of the pressure-rise characteristics. Furthermore, the generation and the evolution of the stall inception waves are suppressed and the non-linear development of the stall process is delayed with the SPS casing treatment.

Cite this article

SUN Xiaofeng , SUN Dakun . Research progresses of stall precursor-suppressed casing treatment[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(8) : 2529 -2543 . DOI: 10.7527/S1000-6893.2015.0153

References

[1] Wennerstrom A J. Highly loaded axial flow compressors: history and current development[J]. Journal of Turbomachinery, 1990, 112(4): 567-578.
[2] Takata H, Tsukuda Y. Stall margin improvement by casing treatment-its mechanism and effectiveness[J]. Journal of Engineering for Power, 1977, 99(1): 121-133.
[3] Fujita H, Takata H. A study of configurations of casing treatment for axial flow compressors[J]. Bulletin of Japan Society Mechanical Engineers, 1984, 27(230): 1675-1681.
[4] Smith G D J, Cumpsty N A. Flow phenomena in compressor casing treatment[J]. Journal of Engineering for Gas Turbines and Power, 1984, 106(3): 532-541.
[5] Lee N K W, Greitzer E M. Effects of compressor endwall suction and blowing on stability enhancement[J]. Journal of Turbomachinery, 1990, 112(1): 133-144.
[6] Ivanov S K, Dudkin V E, Peredery V P, et al. Axial flow ventilation fan: U. K. (19) GB (11) 2 124 303A[P]. 1987-11-02.
[7] Kang C S, Mckenzie A B, Elder R L. Recessed casing treatment effects on fan performance and flow field, ASME Paper, 95-GT-197[R]. New York: ASME, 1995.
[8] Azimian A R, Elder R L, Mckenzie A B. Application of recess vaned casing treatment to axial flow fans[J]. Journal of Turbomachinery, 1990, 112(1): 145-150.
[9] Ziabasharhagh M, Mckenzie A B, Elder R L. Recess vane passive stall control, ASME Paper, 92-GT-36[R]. New York: ASME, 1992.
[10] Houghton T, Day I. Enhancing the stability of subsonic compressors using casing grooves[J]. Journal of Turbomachinery, 2010, 133(2): 021007.
[11] Sakuma Y, Watanabe T, Himeno T, et al. Numerical analysis of flow in a transonic compressor with a single circumferential casing groove: influence of groove location and depth on flow instability[J]. Journal of Turbomachinery, 2013, 136(3): 031017.
[12] Du J, Liu L, Nan X, et al. The dynamics of pre-stall process in an axial low-speed compressor with single circumferential casing groove, ASME Paper, GT2013-95432[R]. New York: ASME, 2013.
[13] Li J, Lin F, Wang S, et al. Extensive experimental study of circumferential single groove in an axial flow compressor, ASME Paper, GT2014-26859[R]. New York: ASME, 2014.
[14] Kern M, Horn W, Hiller S J, et al. Effects of tip injection on the performance of a multi-stage high-pressure compressor[J]. CEAS Aeronautical Journal, 2011, 2(1-4): 99-110.
[15] Kroeckel T, Hiller S J, Jeschke P. Application of a multistage casing treatment in a high speed axial compressor test rig, ASME Paper, GT2011-46315[R]. New York: ASME, 2011.
[16] Crook A J, Greitzer E M, Tan C S, et al. Numerical simulation of compressor endwall and casing treatment flow phenomena[J]. Journal of Turbomachinery, 1993, 115(3): 501-512.
[17] Brignole G A, Danner F C T, Kau H P. Time resolved simulation and experimental validation of the flow in axial slot casing treatments for transonic axial compressors, ASME Paper, GT2008-50593[R]. New York: ASME, 2008.
[18] Wilke I, Kau H P. A numerical investigation of the flow mechanisms in a high pressure compressor front stage with axial slots[J]. Journal of Turbomachinery, 2004, 126(3): 339-349.
[19] Iyengar V, Sankar L N, Niazi S. Assessment of the self-recirculating casing treatment concept applied to axial compressors, AIAA-2005-0632[R]. Reston: AIAA, 2005.
[20] Gourdain N, Wlassow F, Ottavy X. Effect of tip clearance dimensions and control of unsteady flows in a multi-stage high-pressure compressor[J]. Journal of Turbomachinery, 2012, 134(5): 051005.
[21] Greitzer E M, Nikkanen J P, Haddad D E, et al. A fundamental criterion for the application of rotor casing treatment[J]. Journal of Fluids Engineering, 1979, 101(2): 237-243.
[22] Sun X F. On the relation between the inception of rotating stall and casing treatment, AIAA-1996-2579[R]. Reston: AIAA, 1996.
[23] Sun X F, Sun D K, Yu W W. Model to predict stall inception of transonic axial flow fan/compressors[J]. Chinese Journal of Aeronautics, 2011, 24(6): 687-700.
[24] Sun X F, Jing X D. High-intensity sound absorption at an orifice with bias flow[J]. Journal of Propulsion and Power, 2002, 18(3): 718-720.
[25] Jing X D, Sun X F. Numerical simulation on the nonlinear acoustic properties of an orifice[J]. AIAA Journal, 2000, 38(9): 1565-1572.
[26] Jing X D, Sun X F. Effect of plate thickness on impedance of perforated plates with bias flow[J]. AIAA Journal, 2000, 38(9): 1573-1578.
[27] Jing X D, Sun X F. Sound-excited flow and acoustic nonlinearity at an orifice[J]. Physics of Fluids, 2002, 14(1): 268-276.
[28] Zhao H W, Sun X F. Active control of wall acoustic impedance[J]. AIAA Journal, 1999, 37(7): 825-831.
[29] Jing X D, Sun X F. Experimental investigations of perforated liners with bias flow[J]. Journal of the Acoustical Society of America, 1999, 106: 2436-2441.
[30] Sun X F, Sun D K, Liu X H, et al. Theory of compressor stability enhancement using novel casing treatment, Part I: methodology[J]. Journal of Propulsion and Power, 2014, 30(5): 1224-1235.
[31] Sun D K, Liu X H, Jin D H, et al. Theory of compressor stability enhancement using novel casing treatment, Part II: experiment[J]. Journal of Propulsion and Power, 2014, 30(5): 1236-1247.
[32] Sun D K, Liu X H, Sun X F. An evaluation approach for the stall margin enhancement with SPS casing treatment[J]. Journal of Fluids Engineering, 2015, 137(8): 081102.
[33] Sun D K, Nie C Q, Liu X H, et al. Further investigation on transonic compressor stall margin enhancement with SPS casing treatment[J]. Journal of Turbomachinery, 2015 (accepted).
[34] Dong X, Sun X, Li F, et al. Effects of rotating inlet distortion on compressor stability with SPS casing treatment[J]. Journal of Fluids Engineering, 2015, 137(11): 111101.
[35] Liu X H, Sun D K, Sun X F, et al. Flow stability theory for fan/compressors with annular duct and novel casing treatment[J]. Chinese Journal of Aeronautics, 2012, 25(2): 143-154.
[36] Dong X, Liu X H, Sun D K, et al. Experimental investigation on SPS casing treatment with bias flow[J]. Chinese Journal of Aeronautics, 2014, 24(6): 1352-1362.
[37] Xiong S, Sun D K, Suo Q L, et al. Experimental investigation of novel casing treatment on stall margin enhancement under inlet distortion[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(12): 2692-2700 (in Chinese). 熊珊, 孙大坤, 所秋玲, 等. 进气畸变条件下新型机匣处理扩稳效果实验研究[J]. 航空学报, 2013, 34(12): 2692-2700.
[38] Dong X, Liu X H, Sun D K, et al. Experimental investigation of stall margin enhancement using novel casing treatment under the rotating inlet distortion[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(9): 2411-2425 (in Chinese). 董旭, 刘小华, 孙大坤, 等. 旋转畸变条件下新型机匣处理扩稳效果试验[J]. 航空学报, 2014, 35(9): 2411-2425.
[39] Strazisar A J, Bright M M, Thorp S, et al. Compressor stall control through endwall recirculation, ASME Paper, GT2004-54295[C]. New York: ASME, 2004.
[40] Yamaguchi N, Ogata M. Improvement of stalling characteristics of an axial-flow fan by radial-vaned air separators[J]. Journal of Turbomachinery, 2010, 132(2): 021015.
[41] Howe M S. Theory of vortex sound[M]. Cambridge: Cambridge Press, 2002.
[42] Bechert D W. Sound absorption caused by vorticity shedding, demonstrated with a jet flow[J]. Journal of Sound and Vibration, 1980, 70(3): 389-405.
[43] Howe M S. On the theory of unsteady high Reynolds number flow through a circular aperture[C]//Proceedings of the Royal Society London A366, 1979.
[44] Dowling A P, Hughes I J. Sound absorption by a screen with regular array of slits[J]. Journal of Sound and Vibration, 1992, 156(3): 387-405.
[45] Jing X D, Sun X F, Wu J S, et al. Effect of grazing flow on the acoustic impedance of an orifice[J]. AIAA Journal, 2001, 39(8): 1478-1484.
[46] Sun X F, Jing X D, Zhang H, et al. Effect of grazing-bias flow interaction on acoustic impedance of perforated plates[J]. Journal of Sound and Vibration, 2002, 254(3): 557-573.
[47] Sun X F, Liu X H, Hou R, et al. A general theory of flow instability inception in turbomachinery[J]. AIAA Journal, 2013, 51(7): 1675-1687.
[48] Liu X H, Sun D K, Sun X F. Basic studies of flow-instability inception in axial compressors using eigenvalue method[J]. Journal of Fluids Engineering, 2014, 136(3): 031102.
[49] Liu X H, Zhou Y P, Sun X F, et al. Calculation of flow instability inception in high speed axial compressors[J]. Journal of Turbomachinery, 2015, 137(6): 061007.
[50] Garnier V H, Epstein A H, Greitzer E M. Rotating waves as a stall inception indication in axial compressors[J]. Journal of Turbomachinery, 1991, 113(2): 290-302.

Outlines

/