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Technical Briefs

Impact of Surface Roughness on Compressor Cascade Performance

[+] Author and Article Information
Seung Chul Back, Seung Jin Song

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

June Hyuk Sohn

 Renault Samsung Motors, Yongin, 446-796 Gyunggi, Korea

J. Fluids Eng 132(6), 064502 (Jun 23, 2010) (6 pages) doi:10.1115/1.4001788 History: Received October 18, 2009; Revised May 11, 2010; Published June 23, 2010; Online June 23, 2010

This paper presents an experimental investigation of roughness effects on aerodynamic performance in a low-speed linear compressor cascade. Equivalent sandgrain roughnesses of 12μm, 180μm, 300μm, 425μm, and 850μm have been tested. In nondimensional terms, these roughnesses represent compressor blade roughnesses found in actual gas turbines. Downstream pressure, velocity, and angle have been measured with a five-hole probe at 0.3 chord downstream of the blade trailing edge. For the tested roughnesses of 180μm, 300μm, 425μm, and 850μm, the axial velocity ratio across the blade row decreases by 0.1%, 2.1%, 2.5%, and 5.4%, respectively. For the same cases, the exit flow angle deviation increases by 24%, 38%, 51%, and 70%, respectively. Finally, the mass-averaged total pressure loss increases by 12%, 44%, 132%, and 217%, respectively. Also, the loss increases more rapidly in the transitionally rough region. Thus, among the three parameters, the loss responds most sensitively to changes in compressor blade roughness.

Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic of the test facility

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Figure 2

Picture of the test section

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Figure 3

Measurement locations

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Figure 4

Pitchwise end wall static pressure distribution

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Figure 5

Nominal blade pressure distribution

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Figure 6

Deviation distribution of smooth blade at 0.3 chord downstream of the trailing edge

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Figure 7

Loss coefficient distribution of smooth blade at 0.3 chord downstream of the trailing edge

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Figure 8

Smooth and rough blades

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Figure 9

Axial velocity distribution at 0.3 chord downstream of the trailing edge

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Figure 10

Axial velocity ratio versus roughness

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Figure 11

Deviation distribution at 0.3 chord downstream of the trailing edge

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Figure 12

Mass-averaged deviation versus roughness

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Figure 13

Loss coefficient distribution at 0.3 chord downstream of the trailing edge

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Figure 14

Mass-averaged loss coefficient versus roughness

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Figure 15

Schematic of thickened wake due to roughness

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