航改燃气轮机机匣安装边的性能受多个结构参数和载荷参数的影响，为了在给定的结构参数和载荷参数范围内设计性能最优的安装边结构，提出一种机匣安装边结构参数优化设计方法。首先，采用拉丁超立方抽样方法进行实验设计，构建仿真算例样本空间；其次，采用有限元分析方法分析了螺栓孔中心距、螺栓孔直径、安装边厚度等结构参数和机匣内介质压力、介质温度、单个螺栓预紧力等载荷参数对安装边最大等效弹性应力、接触面平均间隙和接触面最大接触压强等特性的影响规律；然后，构建了机匣安装边密封性能计算的代理模型，并对给定工况下燃气轮机机匣安装边结构进行了参数优化设计；最后，针对安装边结构优化设计结果，试验验证了其密封性能以及代理模型的计算精度。结果表明：基于代理模型计算得到的机匣安装边结构密封性能与试验结果误差在10%以内，该方法可用于航改燃气轮机机匣安装边结构的工程优化设计与性能评估。

The performance of the mounting edge of the gas turbine casing modified for aviation was influenced by multiple structural and load parameters. In order to design an optimal mounting edge structure within a given range of structural and load parameters, a structural parameter optimization design method for the mounting edge of the gas turbine casing was proposed. Firstly, this paper adopted the Latin hypercube sampling method for experimental design and constructed a simulation case sample space; secondly, the finite element analysis method was used to analyze the influence of structural parameters such as bolt hole center distance, bolt hole diameter and mounting edge thickness, as well as load parameters such as medium pressure inside the casing, medium temperature and preload of a single bolt, on the characteristics of the mounting edge, including the maximum equivalent elastic stress, average gap of the contact surface and maximum contact pressure of the contact surface; thirdly, a surrogate model for calculating the sealing performance of the mounting edge of the gas turbine casing was constructed, and the structural parameters of the mounting edge of the gas turbine casing under given working conditions were optimized; finally, experimental verification was conducted on the optimized design results of the mounting edge structure to test its sealing performance and the calculation accuracy of the surrogate model. The results show that the error between the sealing performance of the mounting edge structure calculated based on the surrogate model and the experimental results is within 10%. This method can be used for engineering optimization design and performance evaluation of the mounting edge structure of the gas turbine casing modified for aviation.

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