The inlet swirl distortion and non-uniform tip clearance have great effects on aero-engine performance and stall margin. In this paper, the effects of paired swirl distortion on the aerodynamic stability and stall inception of a single stage axial compressor with non-uniform tip clearance are quantitatively analyzed by using the swirl distortion descriptors. The experimental results show that the paired swirl distortion dominated by co-rotating swirl improves the stability of the axial compressor. For a single-stage axial compressor with eccentricity of 100%, the stall inception starts at the maximum tip clearance with clean inlet. The initial position of the stall inception is determined by the maximum tip clearance when the small intensity paired swirl distortion exists at the compressor inlet. As the swirl intensity increases, it shifts towards the position of the counter rotating swirl vortex core. The inlet swirl will not change the type of stall inception.
XU Rong
,
HU Jun
,
WANG Xuegao
,
JIANG Chao
,
LI Wenyu
. Experimental Research on Inlet Steady Swirl Distortion in an Axial Compressor with Non-Uniform Tip Clearance[J]. Journal of Thermal Science, 2023
, 32(1)
: 286
-296
.
DOI: 10.1007/s11630-022-1729-z
[1] Guo R.W., Seddon J., Swirl characteristics of an S-shaped air intake with both horizontal and vertical offsets. Aeronautical Quarterly, 1983, 34(2): 130–146.
[2] Dustin J.F., Lowe K.T., O′Brien W.F., Experimental quantification of fan rotor effects on inlet swirl using swirl distortion descriptors. Journal of Engineering for Gas Turbines and Power, 2018, 140: 082603.
[3] Society of automotive engineers. A methodology for assessing inlet swirl distortion. 2010, Aerospace Information Report No. AIR5686.
[4] Hu W.B., Cheng B.Q., Chen Z.M., et al., Investigation on effects of bulk swirl distortion on compressor performance. Journal of Propulsion Technology, 2015, 36: 1325–1330.
[5] Pazur W., Fottner L., The influence of inlet swirl distortions on the performance of a jet propulsion two-stage axial compressor. Journal of Turbomachinery, 1991, 113(2): 258–268.
[6] Hill P.G., Peterson C.R., Mechanics and thermodynamics of propulsion (2nd revised and enlarged edition). Aviation Industry Press, 2015.
[7] Guo J., Hu J., Development of body force model for steady inlet distortions in high-speed multistage compressor. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2017, 231(9): 1650–1659.
[8] Alford J., Protecting turbo-machinery from self-excited rotor whirl. ASME Journal of Engineering for Gas Turbines and Power, 1965, 87: 333–334.
[9] Freeman C., Tip clearance effects in axial turbomachines (VKI Lecture Series). von Karman Institute, Sint-Genesius-Rode, Belgium, 1985.
[10] Graf M.B., Wong T.S., Greitzer E.M., et al., Effects of nonaxisymmetric tip clearance on axial compressor performance and stability. ASME Journal of Turbomachinery, 1998, 120(4): 648–661.
[11] Young A.M., Cao T., Day I.J., et al., Accounting for eccentricity in compressor performance predictions. Journal of Turbomachinery, 2017, 139(9): 091008.
[12] Storer J.A., Cumpsty N.A., An approximate analysis and prediction method for tip clearance loss in axial compressors. ASME Journal of Turbomachinery, 1994, 116(4): 648–656.
[13] Bennington M.A., Ross M.H., Cameron J.D., et al., An experimental and computational investigation of tip clearance flow and its impact on stall inception. 2010, ASME Paper No. GT2010-23516.
[14] Xu W., Sun P., Yang G., et al., Numerical research on inlet total pressure distortion in a transonic compressor with non-axisymmetric stator clearance. Journal of Thermal Science, 2020, 29: 893–905.
[15] Day I.J., Stall, surge, and 75 years of research. Journal of Turbomachinery, 2016, 138: 011001.
[16] Furukawa M., Inoue M., Saiki K., et al., The role of tip leakage vortex breakdown in compressor rotor aerodynamics. Transactions of ASME Journal of Turbomachinery, 1999, 121(3): 469–480.
[17] Hoying D.A., Tan C.S., Vo H.D., et al., Role of blade passage flow structurs in axial compressor rotating stall inception. Transactions of ASME Journal of Turbomachinery, 1998, 121(4): 735–742.
[18] Schlechtriem S., Lötzerich M., Breakdown of tip leakage vortices in compressors at flow conditions close to stall. ASME International Gas Turbine & Aeroengine Congress & Exhibition. American Society of Mechanical Engineers, 1997, Paper No: 97-GT-041, V001T03A004.
[19] Furukawa M., Saiki K., Yamada K., et al., Unsteady flow behavior due to breakdown of tip leakage vortex in an axial compressor rotor at near-stall condition. ASME Turbo Expo 2000: Power for Land, Sea, and Air, Paper No: 2000-GT-0666, V001T03A112.
[20] Zhang L., He R.Y., Wang S.L., et al., A review of rotating stall in vaneless diffuser of centrifugal compressor. Journal of Thermal Science, 2020, 29(2): 323–342.
[21] Day I.J., Stall inception in axial flow compressors. Journal of Turbomachinery, 1993, 115: 1–9.
[22] Mcdougall N.M., Cumpsty N.A., Hynes T.P., Stall inception in axial compressors. Journal of Turbomachinery, 1988, 112(1): 116–123.
[23] Camp T.R., Day I.J., A study of spike and modal stall phenomena in a low-speed axial compressor. Journal of Turbomachinery, 1998, 120(3): 393–401.
