Abstract Adjoint aerodynamic optimization of a transonic fan rotor blade with a localized two-level mesh deformation method
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Adjoint aerodynamic optimization of a transonic fan rotor blade with a localized two-level mesh deformation method

机译：跨音速风扇转子叶片的局部空气动力学优化与局部二级网格变形方法

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AbstractWe present an optimization platform for turbomachinery with complex mesh configuration in a parallel computation environment. A continuous adjoint solver for 3-D viscous internal flow is coded under the same parallel framework as the flow solver. To meet the various permitted extents of reshaping on blade surface and to cut down the computational cost in grid perturbation, a localized two-level mesh deformation method is developed based on Gaussian radial basis function (RBF). This method works efficiently for both the O mesh surrounding the blade and the O–H mesh inside tip gap. In the optimization of the transonic NASA Rotor 67 for high adiabatic efficiency with a mass flow rate constraint, an adjoint sensitivity analysis is conducted. The relations between the design sensitive regions and physical phenomena in internal flow are discussed. Flow fields before and after the adjoint optimization are investigated, including shock system, tip leakage flow, and flow separation.
机译： 摘要 我们为并行计算环境中具有复杂网格配置的涡轮机械提供了一个优化平台。用于3-D粘性内部流动的连续伴随求解器在与流动求解器相同的并行框架下进行编码。为了满足叶片表面重塑的各种允许程度并降低网格扰动的计算成本，基于高斯径向基函数（RBF）开发了一种局部两级网格变形方法。该方法对于刀片周围的O网格和尖端间隙内的OH网格均有效。为了优化具有质量流量约束的高绝热效率的跨音速NASA转子67，进行了伴随灵敏度分析。讨论了设计敏感区域与内部流动中物理现象之间的关系。研究了伴随优化前后的流场，包括冲击系统，尖端泄漏流和流分离。

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