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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.6 pt.A; 20050606-09; Reno-Tahoe,NV(US) >ON THE AERODYNAMICS OF SWEPT AND LEANED TRANSONIC COMPRESSOR ROTORS
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ON THE AERODYNAMICS OF SWEPT AND LEANED TRANSONIC COMPRESSOR ROTORS

机译：斜齿和斜齿超音速压缩机转子的空气动力学研究

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摘要

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 separately analyzed. A commercial CFD package which solves the Reynolds-average Navier-Stokes equations was used to compute the complex flow field of transonic compressor rotors. The code was validated against NASA Rotor 37 existing experimental data. Computed performance maps and downstream profiles showed a very good agreement with measured ones. Furthermore, comparisons with experimental data indicated that the overall features of the three-dimensional shock structure, the shock-boundary layer interaction, and the wake development are calculated very well in the numerical solution. Next, a quite large number of new transonic swept rotors (26) were modeled 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 the span). An attempt was made to not modify any other design parameter. In particular, in order to isolate the influence of sweep on the aerodynamic behaviour of the new rotors, the meridional position of the tip blade profiles was not changed. Similarly, 26 new transonic leaned rotors were modeled from the same Rotor 37 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 the shock 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压气机转子空气动力学性能的影响。分别分析了轴向和切向叶片曲率的影响。解决了雷诺平均Navier-Stokes方程的商业CFD软件包用于计算跨音速压缩机转子的复杂流场。该代码已根据NASA转子37现有实验数据进行了验证。计算出的性能图和下游曲线与测量值非常吻合。此外，与实验数据的比较表明，在数值解中很好地计算了三维激波结构的整体特征，激波边界层相互作用和尾流发展。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建模出大量新的跨音速扫掠转子（26）。跨度）。试图不修改任何其他设计参数。特别地，为了隔离扫掠对新转子的空气动力学行为的影响，叶尖叶片轮廓的子午线位置没有改变。类似地，通过改变相同控制点的圆周位置，从同一转子37建模了26个新的跨音速倾斜转子。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的冲击和次级损失的影响非常有帮助。

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