【作者】 李鹏飞；

【导师】 杨金广；

【作者基本信息】 大连理工大学 ， 动力工程（专业学位）， 2022， 硕士

【摘要】 网格变形技术是近几年研究的热点话题,其具有操作简单、灵活性高、不需要重新网格划分等优势。本文基于网格变形的参数化方法对某型方转圆进气道、S型进气道和某型径流涡轮等内流部件进行外形优化,实现了各自性能的提升;还进一步采用该技术完成了压气机叶片的冷热态转换。论文主要研究内容包括:1.基于网格变形技术,对某方转圆进气道、某型S型进气道和某径流涡轮进行了气动分析和性能优化。通过对模型设置合理的控制点和变形组,并耦合合适的优化方法,可以实现气动性能的自动优化。对于方转圆进气道,优化后总压恢复系数、出口均匀度等参数均有改善。对于S型进气道,优化后流场分离区明显减少,出口马赫数分布更加均匀,总压恢复系数、总压畸变指数和出口垂直度等性能均有不同程度的提升。对于径流涡轮,优化后设计和非设计点的等熵效率均有增加。2.基于网格变形技术搭建了一套叶片冷热态转换流程。以NASA Rotor 37叶片为研究对象,对其进行流场模拟和载荷分析,得到了叶片在多载荷作用下的应力和应变结果。通过形状匹配的方法实现网格变形,取合适的偏差加载到原始模型即可得到近似冷态模型。经过迭代计算,由冷态模型得到的热态模型与原始模型之间的节点偏差最大值为6.3e-6m。经验证,热态模型与原始模型气动性能基本相同。更多还原

【Abstract】 Mesh morphing is a hot topic in recent years.It has the advantages of simple operation,high flexibility,and no need to re-mesh.In this paper,the parametric method based on mesh morphing is used to optimize a square-to-circle inlet,an S-duct inlet,and a radial flow turbine,and achieve the improvement of performance respectively.This technology is further used to complete hot and cold state conversion of a compressor blade.The main research contents of the paper include:1.Based on the mesh morphing,aerodynamic analysis and performance optimization of a square-to-circle inlet,a S-duct inlet and a radial turbine are carried out.Automatic optimization of aerodynamic performance can be achieved by setting reasonable control points and deformation groups for the model and coupling with appropriate optimization methods.For the square-to-circle inlet,the parameters such as total pressure recovery coefficient and outlet uniformity are improved after optimization.For the S-duct inlet,the optimized flow field separation area is significantly reduced,the outlet Mach number distribution is more uniform,and the performance of total pressure recovery coefficient,total pressure distortion index and outlet verticality are improved to varying degrees.For radial flow turbines,the isentropic efficiency increases at both the design and off-design points after optimization.2.Based on the mesh morphing,a process of cold and hot state conversion is built.Taking the NASA Rotor 37 blade as the research object,the flow field simulation and load analysis were carried out,and the stress and strain results of the blade under multiple loads were obtained.The mesh deformation is realized by shape matching,and the approximate cold state model can be obtained by loading the original model with the appropriate deviation.After iterative calculation,the maximum node deviation between hot model obtained from the cold model and original model is 0.0064 mm.It has been verified that the hot model has basically the same aerodynamic performance as the original model.更多还原