Numerical Simulation of Non-Uniform Roughness Distribution on Compressor Performance

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ZhongYi Wang
ZhongYi Wang
σ
Sun-Haiou
Sun-Haiou
ρ
Wang-Meng
Wang-Meng
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Wang-Zhongyi
Wang-Zhongyi
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Ma-Jingyuan
Ma-Jingyuan
α Harbin Engineering University Harbin Engineering University

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Numerical Simulation of Non-Uniform Roughness Distribution on Compressor Performance

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Abstract

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.

References

26 Cites in Article
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Funding

No external funding was declared for this work.

Conflict of Interest

The authors declare no conflict of interest.

Ethical Approval

No ethics committee approval was required for this article type.

Data Availability

Not applicable for this article.

How to Cite This Article

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): .

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Issue Cover
GJSFR Volume 17 Issue I2
Pg. 25- 32
Journal Specifications

Crossref Journal DOI 10.17406/GJSFR

Print ISSN 0975-5896

e-ISSN 2249-4626

Keywords
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GJSFR-I Classification: FOR Code: 010301
Version of record

v1.2

Issue date

March 12, 2018

Language
en
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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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Numerical Simulation of Non-Uniform Roughness Distribution on Compressor Performance

Sun-Haiou
Sun-Haiou
Wang-Meng
Wang-Meng
Wang-Zhongyi
Wang-Zhongyi
Ma-Jingyuan
Ma-Jingyuan

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