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- W2093004829 abstract "ABSTRACT 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. † 1. 서 론 축류압축기는 흔히 항공 추진용 가스터빈 엔진이나 전력 발전을 위한 가스터빈 엔진의 주요 구성품으로 사용되며, 최근에는 천연가스의 장거리 이송을 위해 유용한 수단으로 인식되고 있다.특히 항공 추진 분야에서는 소형 UAV 또는 PAV용 가스터빈 엔진의 국내 독자 개발을 위해 핵심 구성품에 대한 선행 기술 개발을 진행하고 있으며, 한국항공우주연구원(이하 항우연)의 3단 고압 압축기(COMP1-3A)와 1단 저압 압축기(COMP2-1A) 개발" @default.
- W2093004829 created "2016-06-24" @default.
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- W2093004829 date "2012-12-01" @default.
- W2093004829 modified "2023-10-12" @default.
- W2093004829 title "Design Optimization of a Single-Stage Transonic Axial Compressor and Test Evaluation of Its Aerodynamic Performance" @default.
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- W2093004829 doi "https://doi.org/10.5293/kfma.2012.15.6.077" @default.
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