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Research Papers

Effects of Reynolds Number and Surface Roughness Magnitude and Location on Compressor Cascade Performance

[+] Author and Article Information
Seung Chul Back

Technology Development Center,  Samsung Engineering, Suwon 443-823, Korea

Garth V. Hobson, Knox T. Millsaps

Mechanical and Aerospace Engineering,  Naval Postgraduate School, Monterey, CA 93943

Seung Jin Song

Mechanical and Aerospace Engineering  Seoul National University, Seoul 151-744, Korea

J. Turbomach 134(5), 051013 (May 11, 2012) (6 pages) doi:10.1115/1.4003821 History: Received December 15, 2010; Revised March 03, 2011; Published May 10, 2012; Online May 11, 2012

An experimental investigation has been conducted to characterize the influence of Reynolds number and surface roughness magnitude and location on compressor cascade performance. Flow field surveys have been conducted in a low-speed, linear compressor cascade. Pressure, velocity, and loss have been measured via a five-hole probe, pitot probe, and pressure taps on the blades. Four different roughness magnitudes, Ra values of 0.38 μm (polished), 1.70 μm (baseline), 2.03 μm (rough 1), and 2.89 μm (rough 2), have been tested. Furthermore, various roughness locations have been examined. In addition to the as manufactured (baseline) and entirely rough blade cases, blades with roughness covering the leading edge, pressure side, and 5%, 20%, 35%, 50%, and 100% of suction side from the leading edge have been studied. All of the tests have been carried out for Reynolds numbers ranging from 300,000 to 640,000. For Reynolds numbers under 500,000, the tested roughnesses do not significantly degrade compressor blade loading or loss. However, loss and blade loading become sensitive to roughness at Reynolds numbers above 550,000. Cascade performance is more sensitive to roughness on the suction side than pressure side. Furthermore, roughness on the aft 2/3 of suction side surface has a greater influence on loss. For a given roughness location, there exists a Reynolds number at which loss begins to significantly increase. Finally, increasing the roughness area on the suction surface from the leading edge reduces the Reynolds number at which the loss begins to increase.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 2

Measurement locations

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Figure 3

Tested roughness locations on the baseline blade

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Figure 4

Picture of roughened blades (20% suction side of the baseline blade)

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Figure 5

Blade loading for Ra of 0.38, 1.70, 2.03, and 2.89 μm at Reynolds number 600,000

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Figure 7

Mass-averaged loss coefficient versus roughness magnitude for ks /c

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Figure 8

Blade loading for Ra of 0.38, 1.70, 2.03, and 2.89 μm at Reynolds number 400,000

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Figure 9

Mass averaged loss coefficient versus Reynolds number for Ra of 0.38, 1.70, 2.03, and 2.89 μm

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Figure 10

Static pressure coefficient for Reynolds number of 600,000 for baseline blade (Ra  = 1.70 μm)

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Figure 11

Loss coefficient versus pitch for Reynolds number of 600,000 for baseline blade (Ra  = 1.70 μm)

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Figure 12

Mass-averaged loss versus chordwise suction side roughened area for Reynolds number of 600,000

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Figure 13

Mass-averaged loss versus Reynolds number for each roughness location

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Figure 6

Loss coefficient versus pitch for Ra of 0.38, 1.70, 2.03, and 2.89 μm at Reynolds number 600,000

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