The Role of Tip Leakage Flow in Spike-Type Rotating Stall Inception

Journal of Turbomachinery - Tập 141 Số 6 - 2019
M. Hewkin-Smith1, Graham Pullan2, S. D. Grimshaw2, E. M. Greitzer3, Z. S. Spakovszky3
1Whittle Laboratory, University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, UK e-mail:
2Whittle Laboratory, University of Cambridge, 1 JJ Thomson Avenue, Cambridge, CB3 0DY, UK
3Gas Turbine Laboratory, Massachusetts Institute of Technology, 77 Massachusetts Avenue, 41-205 L, Cambridge, MA 02139

Tóm tắt

This paper describes the role of tip leakage flow in creating the leading edge separation necessary for the onset of spike-type compressor rotating stall. A series of unsteady multipassage simulations, supported by experimental data, are used to define and illustrate the two competing mechanisms that cause the high incidence responsible for this separation: blockage from a casing-suction-surface corner separation and forward spillage of the tip leakage jet. The axial momentum flux in the tip leakage flow determines which mechanism dominates. At zero tip clearance, corner separation blockage dominates. As clearance is increased, the leakage flow reduces blockage, moving the stall flow coefficient to lower flow, i.e., giving a larger unstalled flow range. Increased clearance, however, means increased leakage jet momentum and contribution to leakage jet spillage. There is thus a clearance above which jet spillage dominates in creating incidence, so the stall flow coefficient increases and flow range decreases with clearance. As a consequence, there is a clearance for maximum flow range; for the two rotors in this study, the value was approximately 0.5% chord. The chordwise distribution of the leakage axial momentum is also important in determining stall onset. Shifting the distribution toward the trailing edge increases flow range for a leakage jet dominated geometry and reduces flow range for a corner separation dominated geometry. Guidelines are developed for flow range enhancement through control of tip leakage flow axial momentum magnitude and distribution. An example is given of how this might be achieved.

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Tài liệu tham khảo

1991, Rotating Waves as a Stall Inception Indication in Axial Compressors, ASME J. Turbomach., 113, 290, 10.1115/1.2929105

1993, Stall Inception in Axial Flow Compressors, ASME J. Turbomach., 115, 1, 10.1115/1.2929209

1955, Compressor Surge and Stall Propagation, Trans. ASME, 77, 455

2015, Origins and Structure of Spike-Type Rotating Stall, ASME J. Turbomach., 137, 051007, 10.1115/1.4028494

2013, An Explanation for Flow Features of Spike-Type Stall Inception in an Axial Compressor Rotor, ASME J. Turbomach., 135, 021023, 10.1115/1.4007570

2008, Criteria for Spike Initiated Rotating Stall, ASME J. Turbomach., 130, 10.1115/1.2750674

2015, Rotating Stall Observations in a High Speed Compressor—Part II: Numerical Study, ASME J. Turbomach., 137, 051003, 10.1115/1.4028558

1990, Tip Leakage Flow in Axial Compressors, ASME J. Turbomach., 113, 252, 10.1115/1.2929095

1993, Loss Mechanisms in Turbomachines, ASME J. Turbomach., 115, 621, 10.1115/1.2929299

1999, Endwall Blockage in Axial Compressors, ASME J. Turbomach., 121, 499, 10.1115/1.2841344

1987, Three-Dimensional Flows and Loss Reduction in Axial Compressors, ASME J. Turbomach., 109, 354, 10.1115/1.3262113

1984, Experimental Study of a High-Throughflow Transonic Axial Compressor Stage, ASME J. Eng. Gas Turbines Power, 106, 552, 10.1115/1.3239606

1990, Stall Inception in Axial Compressors, ASME J. Turbomach., 112, 116, 10.1115/1.2927406

Wisler, D. C., Beacher, B. F., and Shin, H.-W., 2002, “Effects of Loading and Clearance Variation on Tip Vortex and Endwall Blockage,” Ninth International Symposium in Transport Phenomena and the Dynamics of Rotating Machinery (ISROMAC), Honolulu, HI, Feb. 10–14, Paper No. FD-ABS-004.

Zhang, Z., Yu, X., and Liu, B., 2012, “Characteristics of the Tip Leakage Vortex in a Low-Speed Axial Compressor With Different Rotor Tip Gaps,” ASME Paper No. GT2012-69148.10.1115/GT2012-69148

1989, Compressor Aerodynamics, 343

1965, Leakage and Secondary Flows in Compressor Cascades, 3483

Gbadebo, S. A., 2003, “Three-Dimensional Separations in Axial Compressors,” Ph.D. thesis, University of Cambridge, Cambridge, UK.

1977, Core Compressor Exit Stage Study—Volume I: Blade Design

Nolan, S. P. R., 2005, “Effect of Radial Transport on Compressor Tip Clearance Flow Structures and Enhancement of Stable Flow Range,” Master's thesis, Massachusetts Institute of Technology, Cambridge, MA.https://pdfs.semanticscholar.org/4e20/a8d7e5daa3b0918f85579d4623c4d2c29f06.pdf

1995, On the Identification of a Vortex, J. Fluid Mech., 285, 69, 10.1017/S0022112095000462

1982, Casing Wall Boundary-Layer Development Through an Isolated Compressor Rotor, ASME J. Eng. Power, 104, 805, 10.1115/1.3227347

1981, Stalling Pressure Rise Capability of Axial Flow Compressor Stages, ASME J. Eng. Power, 103, 645, 10.1115/1.3230787

2002, The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part II: Low and High-Speed Designs and Test Verification, ASME J. Turbomach., 124, 533, 10.1115/1.1507334

2011, An Accelerated 3D Navier–Stokes Solver for Flows in Turbomachines, ASME J. Turbomach., 133, 021025, 10.1115/1.4001192

2005, On the Use of Atmospheric Boundary Conditions for Axial-Flow Compressor Stall Simulations, ASME J. Turbomach., 127, 349, 10.1115/1.1861912

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Journal of Turbomachinery

Tập 141 Số 6

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