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1단 천음속 축류압축기의 최적 설계 및 공력 성능 시험 평가
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논문 기본 정보

Type
Academic journal
Author
Tae Choon Park (한국항공우주연구원) Young-Seok Kang (한국항공우주연구원) Oh-Sik Hwang (한국항공우주연구원) Ji-Han Song (과학기술연합대학원대학교(UST)) Byeung Jun Lim (한국항공우주연구원)
Journal
Korean Society for Fluid Machinery The KSFM Journal of Fluid Machinery Vol.15 No.6 KCI Accredited Journals
Published
2012.12
Pages
77 - 84 (8page)

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Result
1단 천음속 축류압축기의 최적 설계 및 공력 성능 시험 평가
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Abstract· Keywords

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The aerodynamic performance of a single-stage transonic axial compressor was experimentally evaluated by measuring pressure and temperature distribution at the inlet and outlet of the compressor. The compressor was developed by Korea Aerospace Research Institute through multidisciplinary design optimization (MDO) method, especially integrating aerodynamic performance and structural stability. The test results show that the pressure ratio is 1.65 and the efficiency is 85.8 % at design point, where the corrected speed is 22,000 rpm and the corrected mass flow rate is 15.4 kg/s, and it has a good agreement with the design target and computational results. The distribution of pressure ratio is very steep at design speed, compared with the trend of other subsonic compressors. Also the static pressure distribution on the stator casing shows that the blade loading is gradually increasing through the stage as designed.

Contents

ABSTRACT
1. 서론
2. MDO 설계
3. 압축기 시제 및 시험 장치
4. 시험 결과
5. 결론
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UCI(KEPA) : I410-ECN-0101-2014-554-000473361