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TECHNICAL PAPERS

Active Control of Tip Clearance Flow in Axial Compressors

[+] Author and Article Information
Jin Woo Bae, Choon S. Tan

Gas Turbine Laboratory, Massachusetts Institute of Technology, Cambridge, MA

Kenneth S. Breuer

Division of Engineering, Brown University, Providence, RI

J. Turbomach 127(2), 352-362 (May 05, 2005) (11 pages) doi:10.1115/1.1776584 History: Received December 01, 2002; Revised March 01, 2003; Online May 05, 2005
Copyright © 2005 by ASME
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References

Figures

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Illustration of tip leakage flow rate reduction scheme
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Illustration of mixing enhancement scheme
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Illustration of streamwise momentum injection scheme
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Schematic of cascade wind tunnel test section
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Endwall blockage measured 5%C downstream of trailing edge plane versus tip clearance size. No actuation is applied.
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Schematic of the synthetic jet actuator used in the cascade rig. Configuration of the normal synthetic jet (NSJ) actuator with slit
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Schematic of the DSJ actuator mounted on the casing wall
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Schematic of the directed synthetic jet (DSJ) actuator mounted on the casing wall showing the direction of the jet
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Contours of ω measured 5%C downstream of trailing edge plane: (a) baseline without actuation, τ=3%C; (b) NSJ directly over blade tip (at 0% pitch), Cμ,τ=0.88,FC+=1.0; (c) NSJ over vortex core (at 25% pitch), Cμ,τ=0.88,FC+=1.0. Arrows indicate pitchwise locations of NSJ slits.
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Tip clearance-related blockage versus NSJ actuator amplitude. Actuator near the vortex core. FC+=1.0.
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Endwall blockage versus Cμ,τ with NSJ directly over blade tip. Data sets taken for two upstream velocities. τ=3%C,FC+=1.0.
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Frequency dependence of blockage reduction with NSJ actuator over the vortex core: (a) using clearance size τ ; (b) using blade chord C as length scale
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Endwall blockage versus pitchwise location of the NSJ actuator. τ/C=3%,Cμ,τ=0.88, and FC+=1.0.
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Endwall total pressure loss coefficient versus pitchwise location of NSJ actuator. τ/C=3%,Cμ,τ=0.88 and FC+=1.0: (a) mass-averaged ω; (b) stream thrust-averaged (or fully mixed-out) ω.
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Contours of ω measured 5%C downstream of trailing edge plane: (a) baseline without actuation, τ=3%C; (b) DSJ directly over blade PS (y=−0.04 pitch), Cμ,τ=0.88,FC+=1.0. Arrows indicate locations of DSJ holes.
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Comparison between DSJ (placed near the pressure surface of the blade) and NSJ (placed near the vortex core). τ=3%C. Both actuators at FC+=1.0.
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Endwall blockage versus pitchwise location of DSJ actuator. τ=3%C.
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Endwall total pressure loss coefficient versus pitchwise location of the DSJ actuator (τ=3%C): (a) mass-averaged ω; (b) stream thrust-averaged (or fully mixed-out) ω.
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Comparison between the DSJ and the SDJ (steady directed jet). Holes of both actuators are placed over the pressure surface of the blade. τ=3%C. DSJ at FC+=1.0.
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Ratio of endwall loss reduction to expended flow power of directed jet actuation at C̄μ,τ=0.25.
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Estimated recovery rate of expended flow power: (a) as function of relative angle between the jet and main flow; (b) as function of the velocity ratio for a fixed momentum injection

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