Performance Degradation due to Blade Surface Roughness in a Single-Stage Axial Turbine

[+] Author and Article Information
Yong Il Yun

School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea   e-mail: yyoon1@snu.ac.kr

Il Young Park

Turbomachinery R&D Center, Samsung Techwin, Changwon 641-717, Korea   e-mail: ilyoung10.park@samsung.com

Seung Jin Song

School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Koreae-mail: sjsong@snu.ac.kr

J. Turbomach 127(1), 137-143 (Feb 09, 2005) (7 pages) doi:10.1115/1.1811097 History: Received October 01, 2003; Revised March 01, 2004; Online February 09, 2005
Copyright © 2005 by ASME
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Schematic of the test turbine rig
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Axial locations of instrumentation
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Blade roughening process
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Roughened test turbine blade set
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Normalized efficiency degradation with transitional and full roughnesses
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Suction side-pressure side differentiation with fully roughened stator (ks=400 μm)
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Stator-rotor differentiation with transitional roughness (ks=106 μm)
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Stator-rotor differentiation with full roughness (ks=400 μm)
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Measured stator pressure coefficient
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Stage velocity triangles
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Estimated stator loss coefficient
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Measured rotor pressure coefficient
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Estimated rotor loss coefficient




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