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TECHNICAL PAPERS

Analysis of Aerodynamically Induced Whirling Forces in Axial Flow Compressors

[+] Author and Article Information
Z. S. Spakovszky

Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Turbomach 122(4), 761-768 (Feb 01, 2000) (8 pages) doi:10.1115/1.1312801 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

Smith, L., 1958, “The Effect of Tip Clearance on the Peak Pressure Rise of Axial-Flow Fans and Compressors,” Proc. ASME Symposium on Stall, pp. 149–152.
Thomas,  H., 1958, “Unstable Natural Vibration of Turbine Rotors Induced by the Clearance Flow in Glands and Blading,” Bull. de l’A.I.M, 71, No. 11/12, pp. 1039–1063.
Alford,  J., 1965, “Protecting Turbomachinery From Self-Excited Rotor Whirl,” ASME J. Eng. Power, 87, pp. 333–344.
Colding-Jorgensen,  J., 1992, “Prediction of Rotor Dynamic Destabilizing Forces in Axial Flow Compressors,” ASME J. Fluids Eng., 114, pp. 621–625.
Ehrich,  F., 1993, “Rotor Whirl Forces Induced by the Tip Clearance Effect in Axial Flow Compressors,” ASME J. Vibr. Acoust., 115, pp. 509–515.
Yan, L., Hong, J., Li, Q., Zhu, Z., and Zhao, F., 1995, “Blade Tip Destabilizing Force and Instability Analysis for Axial Rotors of Compressors,” Beijing University of Aeronautics and Astronautics Report.
Song,  S., and Martinez-Sanchez,  M., 1997, “Rotordynamic Forces Due to Turbine Tip Leakage: Part I—Blade Scale Effects,” ASME J. Turbomach., 119, pp. 695–703.
Storace, A., Wisler, D., Shin, H. W., Beacher, B., Ehrich, F., Spakovszky, Z., Martinez-Sanchez, M., and Song, S., 2000, “Unsteady Flow and Whirl Inducing Forces in Axial-Flow Compressors; Part I—Experiment,” ASME Paper No. 2000-GT-565.
Ehrich, F., Spakovszky, Z., Martinez-Sanchez, M., Song, S., Wisler, D., Storace, A., Shin H. W., and Beacher, B., 2000, “Unsteady Flow and Whirl Inducing Forces in Axial-Flow Compressors; Part II—Analysis,” ASME Paper No. 2000-GT-566.
Gordon, K., 1999, “Three-Dimensional Rotating Stall Inception and Effects of Rotating Tip Clearance Asymmetry in Axial Compressors,” Ph.D. thesis, Department of Aeronautics and Astronautics, MIT.
Hynes,  T., and Greitzer,  E., 1987, “A Method for Assessing Effects of Circumferential Flow Distortion on Compressor Stability,” ASME J. Turbomach., 109, pp. 371–379.
Graf,  M., Wong,  T., Greitzer,  E., Marble,  F., Tan,  C., Shin,  H. W., and Wisler,  D., 1998, “Effects of Nonaxisymmetric Tip Clearance on Axial Compressor Performance and Stability,” ASME J. Turbomach., 120, pp. 648–661.
Moore,  F., and Greitzer,  E., 1986, “A Theory of Post-Stall Transients in Axial Compressors: Part I—Development of the Equations,” ASME J. Eng. Gas Turbines Power, 108, pp. 68–76.
Spakovszky, Z., Paduano, J., Larsonneur, R., Traxler, A., and Bright, M., 2000, “Tip-Clearance Actuation with Magnetic Bearings for High-Speed Compressor Stall Control,” ASME Paper No. 2000-GT-528.
Al-Nahwi, A., 2000, “Aerodynamic-Rotordynamic Interaction in Axial Compression Systems,” Ph.D. thesis, Dept. of Mechanical Engineering, MIT.

Figures

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Compressor performance prediction for a steady shaft offset of Δε=0.7 percent in the four repeating stage compressor reported in 5
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Unsteady momentum control volume analysis locked to rotor frame
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Definition of reference frames: rotor frame (x,y), rotating asymmetry frame (x,y), and absolute frame (x̃,ỹ)
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Alford β parameter for four stage compressor reported in 5 and model prediction
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Simplified blade loading analysis for compressors and turbines
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Simplified whirl analysis of four-stage compressor
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Spool loading parameter βspool for four repeating stage compressor reported in 5
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Compressor flow field with inertia effects included (solid) and inertia effects neglected (dashed) for a given tip-clearance distribution δε (dotted)
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Effect of flow inertia on rotor forces due to spool pressure loading
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Alford β parameter and spool loading parameter βspool for forced rotor whirl
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Magnitude and phase of fundamental wave form of flow coefficient (solid) and nondimensional spool pressure (dashed) for ϕ=0.391

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