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采用数值计算和实验研究相结合的方法,研究了跨音速转子叶顶泄漏流与主流交界面轴向位置随流量的变化规律和机制。该跨音转子是美国圣母大学一级半跨音速压气机转子。研究发现机匣壁面脉线分布能够定性反映壁面轴向剪切应力分布,可用来识别叶顶泄漏流与主流的交界面位置。通过机匣壁面的脉线分布,可以看出机匣壁面存在两条零剪切应力线。第一条零剪切应力线表示来流与叶顶泄漏流之间交界面的时间和周向平均轴向位置,在小流量工况下交界面靠近顶部叶片的前缘。计算和实验结果都表明,随着质量流量的减小,叶顶泄漏流与主流交界面的轴向位置不断向叶片前缘移动。在近失速点,交界面到达叶片前缘,泄漏流即将溢出。泄漏流与主流的轴向动量比随流量减小不断增大的变化规律进一步说明,间隙区域泄漏流与主流的轴向动量平衡是导致交界面不断前移直至溢出的内在机制。
The numerical simulation and experimental research are combined to study the regularity and mechanism of the axial position of the transonic rotor tip leakage flow and the main interface. The transonic rotor is a first-class semi-transonic compressor rotor at the University of Notre Dame. It was found that the distribution of vessel wall veins can qualitatively reflect the distribution of axial shear stress on the wall. It can be used to identify the location of the interface between the leakage flow and the mainstream at the top of the blade. Through the casing wall of the pulse line distribution, we can see the casing wall there are two zero shear stress lines. The first zero-shear stress line represents the time and circumferential average axial position of the interface between the incoming flow and the tip leakage flow. At low flow rates, the interface approaches the leading edge of the top blade. Calculations and experimental results show that as the mass flow rate decreases, the axial position of the tip-leakage flow and the mainstream interface continue to move towards the leading edge of the blade. At near stalling points, the interface reaches the leading edge of the blade and the leakage flow is about to overflow. Leakage and the mainstream of the axial momentum ratio decreases with the increase of the flow rate further illustrates that the leakage gap flow gap with the mainstream of the axial momentum balance is the interface leading to continue to move forward until the overflow of the internal mechanism.