The Effect of Variable Chord Length on Transonic Axial Rotor Performance

[+] Author and Article Information
William B. Roberts, Albert Armin, George Kassaseya

Airfoil Management Co. and Airfoil Technologies International, Compton, CA 90220

Kenneth L. Suder, Scott A. Thorp, Anthony J. Strazisar

NASA Glenn Research Center, Cleveland, OH

J. Turbomach 124(3), 351-357 (Jul 10, 2002) (7 pages) doi:10.1115/1.1459734 History: Received January 18, 2001; Online July 10, 2002
Copyright © 2002 by ASME
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Static pressure distributions over the blade tip for three operating conditions at 100% design speed
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Schematic of blade leading edge—(a) Blunt leading edge due to erosion, (b) Recontoured leading edge
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NASA-Glenn single-stage transonic compressor test facility
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Location of aerodynamic survey stations
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Simulated erosion of 5% of chord over the outer 50% of span
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Schematic of tested blade installation configurations
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Rotor overall performance at 60, 80, and 100% speed for three blade installation configurations. Stalling massflow denoted by vertical bars. Crosses denote error bars. □, halves; ▵, quadrants; * alternating.
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Radial profiles of efficiency for 80% speed at a massflow rate of 17.5 kg/s
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Rotor performance at 100% speed, maximum massflow operating point—□, halves; ▵, quadrants; *, alternating
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Rotor performance at 100% speed, midway between maximum and near-stall operating points—□, halves; ▵, quadrants; *, alternating
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Rotor performance at 100% speed, near-stall operating point—□, halves; ▵, quadrants; *, alternating



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