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TECHNICAL PAPERS

Three-Dimensional Unsteady Flow for an Oscillating Turbine Blade and the Influence of Tip Leakage

[+] Author and Article Information
D. L. Bell, L. He

School of Engineering, University of Durham, Durham, DH1 3LE, United Kingdom

J. Turbomach 122(1), 93-101 (Feb 01, 1998) (9 pages) doi:10.1115/1.555432 History: Received February 01, 1998
Copyright © 2000 by ASME
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References

He,  L., and Denton,  J. D., 1994, “Three Dimensional Time-Marching Inviscid and Viscous Solutions for Unsteady Flows Around Vibrating Blades,” ASME J. Turbomach., 116, pp. 469–476.
Gerolymos,  G. A., 1994, “Advances in the Numerical Integration of the Three-Dimensional Euler Equations in Vibrating Cascades,” ASME J. Turbomach., 115, pp. 781–790.
Hall,  K. C., and Lorence,  C. B., 1993, “Calculation of Three-Dimensional Unsteady Flows in Turbomachinery Using the Linearized Harmonic Euler Equations,” ASME J. Turbomach., 115, pp. 800–809.
Sjolander, S. A., 1997, “Physics of Tip Clearance Flows I & II,” VKI Lecture Series 1997-01 on Secondary and Tip-Clearance Flows in Axial Flow Turbomachines, Von Karman Institute for Fluid Dynamics, Belgium.
Bell, D. L., and He, L., 1997, “Three Dimensional Unsteady Pressure Measurements for an Oscillating Turbine Blade,” ASME Paper No. 97-GT-105.
Bell, D. L., and He, L., 1998, “Three Dimensional Unsteady Flow Around a Turbine Blade Oscillating in Bending Mode—An Experimental and Computational Study,” Proc. 8th ISUAAT. Stockholm, Sweden.
Bell, D. L., 1999, “Three Dimensional Unsteady Flow for an Oscillating Turbine Blade,” Ph.D. Thesis, University of Durham, U.K.
Denton,  J. D., 1983, “An Improved Time-Marching Method for Turbomachinery Flow Calculations,” ASME J. Eng. Gas Turbines Power, 105, pp. 514–524.
Jameson, A., Schmidt, W., and Turkel, E., 1981. “Numerical Solutions of the Euler Equations by Finite Volume Method Using the Runge–Kutta Timestepping Scheme,” AIAA Paper No. 81-1259.

Figures

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Schematic of data acquisition hardware
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Data acquisition and reduction; sample results at 70 percent span, suction surface (k: 0.25)
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Predicted and measured blade pressure distribution
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Experimental test for linearity, k: 0.50; first harmonic pressure response at two bending amplitudes (lines denote measurements obtained at the normal bending amplitude, and symbols those obtained at the reduced bending amplitude)
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Predicted and measured first harmonic pressure response (reduced frequency: 0.25)
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Quasi-three-dimensional prediction of |Cp1|—suction surface, k: 0.25
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Predicted and measured variation in aerodynamic damping with reduced frequency
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Inlet total pressure profile in pitch-averaged form
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Variation in blade pressure distribution with tip gap
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Pitch-averaged measurements of loss (Ȳ), and exit flow angle (ᾱ) 75 percent chord downstream
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Secondary velocity vectors (exit traverse plane, 75 % C downstream)
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Variation in aerodynamic damping with tip gap
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Variation in amplitude of first harmonic pressure at tip section (90 percent span) with tip clearance − k: 0.25 and 0.75
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Variation in phase of first harmonic pressure at tip section (90 percent span) with tip clearance − k: 0.25 and 0.75

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