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以NASA Rotor67(美国国家航空航天局的转子67)跨音速压气机转子为研究对象,分别采用准二维和三维数值方法,研究稠度变化对跨音速压气机转子叶栅激波结构及流场性能的影响。结果表明,准二维和三维数值计算得到的稠度特性不完全相同,当前研究条件下准二维计算不能定性地反映三维研究结果,压气机转子通道内复杂的三维流动现象是造成两种方法差异的重要原因。
Taking the transonic compressor rotor of NASA Rotor67 (rotor 67 of NASA) as the research object, the quasi-2D and 3D numerical methods are respectively used to study the influence of the variation of consistency on the shock structure and flow field performance of a transonic compressor rotor cascade Impact. The results show that the quasi-two-dimensional and three-dimensional numerical calculation of the consistency properties are not exactly the same, under the current research conditions quasi-two-dimensional calculation can not qualitatively reflect the three-dimensional research results, the compressor rotor channel complex three-dimensional flow phenomenon is caused by two methods The important reason.