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Turbine blade temperature transfer using the load surface method

机译：使用负荷面法进行涡轮叶片温度传递

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Temperature transfer is important to MDA (multidisciplinary analysis) of turbine blades, for the separation of aerodynamics and structure analysis codes. To re-couple these codes, a load surface method is provided here to transfer temperature across the interface of arbitrarily meshed CFD (Computational Fluid Dynamics) and CSM (Computational Structural Mechanics) models. The idea of the method is to transfer temperature by a Bi-cubic B-spline surface, fitted from the CFD temperature results of interfaces in parametric space. The temperature of the CSM nodes of the interface is calculated from the load surface in the same parametric space. An important step in this transfer method is to map the CFD and CSM nodes into the same parametric space. The mapping surface method is detailed for this purpose. In the mapping method, the nodes are mapped onto a structured quad mesh, called a mapping surface, which is additionally generated on the interface surface. Then, the nodes are mapped into the parametric space, which is defined by a parameterization of the mapping surface. To evaluate the accuracy of the method, the temperature of a turbine blade is transferred experimentally. The result indicates that the method is accurate even for coarse meshes.
机译：温度传递对于涡轮机叶片的MDA（多学科分析）很重要，对于分离空气动力学和结构分析代码而言。为了重新耦合这些代码，此处提供了一种载荷面方法，可在任意啮合的CFD（计算流体力学）和CSM（计算结构力学）模型的界面上传递温度。该方法的思想是通过双三次B样条曲面传递温度，该曲面由参数空间中界面的CFD温度结果拟合而成。接口的CSM节点的温度是从相同参数空间中的载荷面计算得出的。这种传输方法的重要一步是将CFD和CSM节点映射到相同的参数空间。为此，详细介绍了映射表面方法。在映射方法中，将节点映射到结构化的四边形网格（称为映射表面）上，该网格在界面表面上另外生成。然后，将节点映射到参数空间，该空间由映射表面的参数化定义。为了评估该方法的准确性，通过实验传递了涡轮叶片的温度。结果表明，该方法即使对于粗糙的网格也是正确的。

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