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采用数值方法模拟了低雷诺数条件下NASA Rotor 37跨声速压气机转子内部流场.结果表明,附面层径向涡是该压气机转子流动失稳的一个很重要的原因.通过在该压气机转子叶片吸力面上不同的叶高和轴向弦长处进行抽吸,发现都可以很好的抑制附面层径向涡的发展,压气机转子的稳定工作范围明显扩大.此外还比较了不同的抽吸量对压气机的性能的影响.
The flow field inside the rotor of NASA Rotor 37 transonic compressor at low Reynolds number is numerically simulated. The results show that the radial vortex at the interface layer is a very important reason for the flow instability of the compressor rotor. The different leaf height and axial chord at the suction side of the rotor blade were suctioned and found that the development of radial vortices in the coats was well suppressed and the stable working range of the compressor rotor was obviously enlarged. Of the amount of suction on the performance of the compressor.