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为了探究高空低雷诺数条件下跨声速压气机的流动规律,对NASA Rotor37进行单通道数值模拟,探索其在低雷诺数进气条件下二次流的旋涡结构.研究发现:马蹄涡压力面分支诱发压力面角区诱导涡,壁角涡形成了顺流和逆流的两段式结构,脱落涡由叶根角区发展起来后不断从尾缘脱落,泄漏涡近失速点仅局部破裂不是失稳触发的主要原因.通道中的激波系诱发了吸力面和压力面的两个径向涡,压力面径向涡构成闭合的气泡式分离,吸力面径向涡在叶顶的破碎诱导产生分离涡,触发了低雷诺数下压气机的失稳.流场旋涡结构由马蹄涡、壁角涡、径向涡、泄漏涡、分离涡、脱落涡6个大尺度旋涡以及其他小尺度旋涡组成.
In order to explore the flow law of transonic compressor at high altitude and low Reynolds number, single-channel numerical simulation of NASA Rotor37 was carried out to explore the vortex structure of secondary flow under low Reynolds number inlet condition. It was found that the pressure surface of the horseshoe vortex Induced pressure facet induced vortices and corner vortices formed a two-stage structure of forward and reverse flow. Vortex shedding continued to emerge from the trailing edge after being developed by the root zone of the root. Vortex vortices near the stall point were not triggered by instability . The shock wave in the channel induces two radial vortices on the suction side and the pressure side, and the radial vortex on the pressure side forms a closed bubble separation. The radial vortex at the suction side induces a separation vortex due to the crushing of the top of the blade. , Which triggered the instability of the compressor under low Reynolds number.The vortex structure of the flow field consists of horseshoe vortex, corner vortex, radial vortex, leakage vortex, separation vortex, shedding vortex and other small-scale vortices.