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This paper investigated the roughness of NASA Stage 35 test compressor. Surface roughness can change the geometric line in the microcosm, which causes the compressor operation to deviate from the design point under working conditions. Wall function was used in this study to describe roughness. Roughness calculation model in non-uniform distribution was established along the chord and spanwise directions. Basing on certain rules, rotor blades were attached with roughness to determine the influence of blade roughness position distribution on the overall performance of the compressor and internal flow. Results show that when roughness was distributed from the blade leading edge to 40% of the chord, the compressor performance was greatly influenced; in severe performance, compressor efficiency decreased by more than 2%. Roughness position distribution in blade height direction exhibited a minimal effect on the entire compressor performance, which can be ignored.
ZhongYi Wang. 2018. \u201cNumerical Simulation of Non-Uniform Roughness Distribution on Compressor Performance\u201d. Global Journal of Science Frontier Research - I: Interdisciplinary GJSFR-I Volume 17 (GJSFR Volume 17 Issue I2): .
Crossref Journal DOI 10.17406/GJSFR
Print ISSN 0975-5896
e-ISSN 2249-4626
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Total Score: 134
Country: China
Subject: Global Journal of Science Frontier Research - I: Interdisciplinary
Authors: Sun-Haiou, Wang-Meng, Wang-Zhongyi, Ma-Jingyuan (PhD/Dr. count: 0)
View Count (all-time): 148
Total Views (Real + Logic): 3039
Total Downloads (simulated): 1621
Publish Date: 2018 03, Mon
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This paper investigated the roughness of NASA Stage 35 test compressor. Surface roughness can change the geometric line in the microcosm, which causes the compressor operation to deviate from the design point under working conditions. Wall function was used in this study to describe roughness. Roughness calculation model in non-uniform distribution was established along the chord and spanwise directions. Basing on certain rules, rotor blades were attached with roughness to determine the influence of blade roughness position distribution on the overall performance of the compressor and internal flow. Results show that when roughness was distributed from the blade leading edge to 40% of the chord, the compressor performance was greatly influenced; in severe performance, compressor efficiency decreased by more than 2%. Roughness position distribution in blade height direction exhibited a minimal effect on the entire compressor performance, which can be ignored.
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