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

Download
Author
Back, Seung Chul
Hobson, Garth V.
Song, Seung Jin
Millsaps, Knox T.
Date
2012-09Metadata
Show full item recordAbstract
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 lm (polished), 1.70 lm (baseline), 2.03 lm (rough 1), and 2.89 lm (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.
Description
The article of record as published may be located at http://dx.doi.org/10.1115/1.4003821
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Collections
Related items
Showing items related by title, author, creator and subject.
-
Effect of Leading Edge Roughness and Reynolds Number on Compressor Profile Loss
Im, Ju Hyun; Shin, Ju Hyun; Hobson, Garth V.; Song, Seung Jin; Millsaps, Knox T. (ASME, 2013-06);An experimental investigation has been conducted to characterize the influence of leading edge roughness and Reynolds number on compressor cascade profile loss. Tests have been conducted in a low-speed linear compressor ... -
Determination of boundary layer transition and separation on double arc compressor blades in a large subsonic cascade.
McGuire, Alan G. (1983-09);The china clay technique for flow visualization was used to determine the surface flow on a double circular arc (DCA) compressor blade in a large rectilinear subsonic cascade wind tunnel. A calibration experiment using ... -
Inlet Turbulence Distortion and Viscous Flow Development in a Controlled-Diffusion Compressor Cascade at Very High Incidence
Hobson, G.V.; Shreeve, R.P. (AIAA, 1993);Detailed two-component laser Doppler velocimeter (LDV) measurements of the flow through a controlled-diffusion (CD) compressor cascade at a Reynolds number of about 700,000 and at a low Mach number are reported in this ...