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Aerodynamics of swept and leaned transonic compressor-rotors

机译：扫频和倾斜跨音速压缩机转子的空气动力学

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A systematic investigation to understand the impact of axially swept and tangentially leaned blades on the aerodynamic behaviour of transonic axial-flow compressor rotors was undertaken. Effects of axial and tangential blade curvature were analyzed separately. A commercial CFD package, which solves the Reynolds-averaged Navier-Stokes equations, was used to compute the complex flow field of transonic compressor-rotors. It was validated against NASA Rotor 37 existing experimental data. Computed performance maps and downstream profiles showed a good agreement with measured ones. Furthermore, comparisons with experimental data indicated that the overall features of three-dimensional shock structure, shock-boundary layer interaction, and wake development are calculated well by the numerical solution. Next, quite a large number of new transonic swept rotors (26) were modelled from the original Rotor 37, by changing the meridional curvature of the original stacking line through three previously defined control points (located at 33%, 67% and 100% of span). Similarly, 26 new transonic leaned rotors were modelled by changing the circumferential position of the same control points. All the new transonic rotors were simulated and the results revealed many interesting aspects which are believed to be very helpful to better understand the blade curvature effects on shock structure and secondary losses within a transonic rotor.
机译：进行了系统研究，以了解轴向扫过和切向倾斜的叶片对跨音速轴流式压缩机转子的空气动力学行为的影响。分别分析了轴向和切向叶片曲率的影响。使用商业CFD软件包解决了雷诺平均Navier-Stokes方程，用于计算跨音速压气机转子的复杂流场。已根据NASA转子37现有实验数据进行了验证。计算的性能图和下游曲线与测得的曲线吻合良好。此外，与实验数据的比较表明，通过数值解可以很好地计算三维激波结构，激波边界层相互作用和尾流发展的总体特征。接下来，通过通过三个预先定义的控制点（分别位于33％，67％和100％的控制点）改变原始堆叠线的子午曲率，从原始转子37建模了大量新的跨音速扫掠转子（26）。跨度）。同样，通过更改相同控制点的圆周位置，对26个新的跨音速倾斜转子进行了建模。所有新的跨音速转子都经过了仿真，结果揭示了许多有趣的方面，这些方面被认为对更好地了解叶片曲率对跨音速转子中冲击结构和次级损失的影响非常有用。

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