机译:基于大涡模拟的Sharkskin启动压缩机级联的物理机制研究
Key Laboratory of Advanced Energy and Power Advanced Gas Turbine Laboratory Institute of Engineering Thermophysics Chinese Academy of Sciences Beijing 100190 China School of Engineering Science University of Chinese of Academy of Sciences Beijing 100049 China Jet Propulsion Laboratory School of Aerospace Engineering Beijing Institute of Technology Beijing 100081 China;
Center of Applied Space Technology and Microgravity (ZARM) Department of Production Engineering Universitat Bremen Bremen 28359 Germany;
Key Laboratory of Advanced Energy and Power Advanced Gas Turbine Laboratory Institute of Engineering Thermophysics Chinese Academy of Sciences Beijing 100190 China School of Engineering Science University of Chinese of Academy of Sciences Beijing 100049 China;
Key Laboratory of Advanced Energy and Power Advanced Gas Turbine Laboratory Institute of Engineering Thermophysics Chinese Academy of Sciences Beijing 100190 China School of Engineering Science University of Chinese of Academy of Sciences Beijing 100049 China;
Key Laboratory of Advanced Energy and Power Advanced Gas Turbine Laboratory Institute of Engineering Thermophysics Chinese Academy of Sciences Beijing 100190 China School of Engineering Science University of Chinese of Academy of Sciences Beijing 100049 China;
boundary layer development; computational fluid dynamics; fan; compressor; large eddy simulation; fluid dynamics and heat transfer phenomena in compressor and turbine components of gas turbine engines;
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机译:基于大涡模拟的Sharkskin启动压缩机级联的物理机制研究
机译:级联流模拟和测量,用于研究轴流压缩机的损失机理。
机译:工业压缩机流量的大涡模拟:2015年至2035年的路径
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