ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Effects of casing deformation on blade rows flow field characteristics in an axial-flow compressor
Received date: 2015-11-11
Revised date: 2016-01-06
Online published: 2016-01-18
Supported by
National Natural Science Foundation of China
In the actual machining, installation and using process, the problems of casing deformation, rotor eccentricity and nonuniform rotor blade heights exist to some extent in all axial-flow compressors, resulting in circumferential nonuniform tip clearance. With the deepening of the research on axial-flow compressor flow, the nonuniform clearance becomes the problem should be considered. The focus of this investigation is on the nonuniform clearance caused by casing deformation and its effect on the flow field characteristics of the rotor rows. The new parameter representing the nonuniformity of tip clearance is recommended, and the modeling approach for the nonaxisymmetry compressor is introduced. Three numerical models with different tip clearance nonuniformities are investigated by both steady and unsteady calculations. The effects of nonuniform clearance on aerodynamic performance and flow loss distribution are analyzed. The unsteady pressure fluctuation and aerodynamic force are also discussed. The results indicate that the nonuniform clearance can contribute to performance degradation and the circumferential asymmetrical flow field in blade tip regions. Due to the "wake" of the upstream blade row, flow field asymmetry of the back rotor row is more obvious than that of the front rotor row. There is direct correspondence between the nonuniform clearance layout and the aerodynamic force distribution in the circumferential direction. The blade aerodynamic force is higher at small tip clearance regions and lower at large tip clearance regions, increasing the amplitude of the aerodynamic force in casing deformation.
CHEN Yingxiu , HOU Anping , ZHANG Mingming , ZHANG Simu . Effects of casing deformation on blade rows flow field characteristics in an axial-flow compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(11) : 3284 -3295 . DOI: 10.7527/S1000-6893.2016.0010
[1] SMITH L H. The effect of tip clearance on the peak pressure rise of axial-flow fans and compressors[Z]. ASME Symposium on Stall, 1958:149-152.
[2] BAGHDADI S. Modeling tip clearance effects in multistage axial compressors[J]. Journal of Turbomachinery, 1996, 118(4):697-705.
[3] SMITH L H. Casing boundary layers in multistage axial flow compressors[J]. Flow Research on Blading, 1970, 106(1):635-647.
[4] CHRISTOPHER H, RICHARD W, GARY P. Effect of tip clearance on fan noise and aerodynamic performance:AIAA-2005-2875[R]. Reston:AIAA, 2005.
[5] GRAF M B, WONG T S, GREITZER E M, et al. Effects of nonaxisymmetric tip clearance on axial compressor performance and stability[J]. Journal of Turbomachinery, 1998, 120(4):648-661.
[6] THOMAS H J. Unstable natural vibration of turbine rotors induced by the clearance flow in glands and blading[J]. Bulletin de L'A.I.M., 1958,71(11/12):1039-1063.
[7] ALFORD J. Protecting turbomachinery from self-excited rotor whirl[J]. Journal of Engineering for Power, 1965, (87):333-343.
[8] SONG S J, MARTINE-SANCHEZ M. Rotordynamic forces due to turbine tip leakage:part 1-Blade scale effects[J]. Journal of Turbomachinery, 1997, 119(4):695-703.
[9] SONG S J, MARTINE-SANCHEZ M. Rotordynamic forces due to turbine tip leakage:part 2-Radius scale effects and experimental verification[J]. Journal of Turbomachinery,1997, 119(4):704-713.
[10] SONG S J. Inviscid rotor dynamic damping forces due to nonaxisymmetric tip clearance in turbines[J]. AIAA Journal, 1998, 36(12):2163-2169.
[11] EHRICH F. Rotor whirl forces induced by the tip clearance effect in axial flow compressors[J]. ASME Journal of Vibration and Acoustics, 1993, 115(4):509-515.
[12] STORACE A, EHRICH F, SONG S J, et al. Unsteady flow and whirl-inducing forces in axial-flow compressors:part I-Experiment[J]. Journal of Turbomachinery, 2001, 123(3):433-445.
[13] 梁武昌, 楚武利, 朱俊强, 等. 非轴对称尖部间隙对轴流压气机性能影响的实验研究[J]. 航空动力学报, 2004, 19(2):233-236. LIANG W C, CHU W L, ZHU J Q, et al. Effect of asymmetric tip clearance on axial flow compressor performance[J]. Journal of Aerospace Power, 2004, 19(2):233-236(in Chinese).
[14] CHEN Y X, HOU A P, ZHANG M M, et al. Effects of nonuniform tip clearance on fan performance and flow field:ASME-GT2015-42133[R]. New York:ASME, 2015.
[15] RABE D. Influence of inlet distortion on transonic compressor blade loading:AIAA-1995-2461[R]. Reston:AIAA, 1995.
[16] DONG X, SUN D, LI F, et al. Effects of rotating inlet distortion on compressor stability with SPS casing treatment[J]. Journal of Fluids Engineering, 2015, 112(29):59-60.
[17] DANIELE C L, TEREN F. Prediction of compressor stall for distorted and undistorted inlet flow[J]. Journal of Aircraft, 1975, 12(10):841-846.
[18] SPAKOVSZKY Z S, WEIGL H J, PADUANO J D, et al. Rotating stall control in a high-speed stage with inlet distortion:part II-Circumferential distortion[J]. Journal of Turbomachinery, 1999, 121(3):517-524.
[19] ANSYS. Computational fluid dynamics soft ware package user guide[CP/DK]. Canonsburg, PA:ANSYS, Inc., 2014.
[20] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8):1598-1605.
[21] MONTOMOLI F, NAYLOR E, HODSON H P, et al. Unsteady effects in axial compressors:A multistage simulation[J]. Journal of Propulsion & Power, 2013, 29(5):1001-1008.
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