Grid Generation and Domain Decomposition Method for Compressor Blade Deformation

A multi-functional grid generation system is established which integrates blade geometric parameterization, multi-block structured grid generation, automatic domain decomposition and blade free form deformation, in order to meet the urgent demand of compressor optimal design and multi-disciplinary analysis for the automatic reliable high-quality grid generation. The grid generation method uses a combination of elliptic partial differential equation solver and O4H topology to obtain smooth meshes for the compressor single passage. The free deformation method is revised for the deformed blades and meshes. The developed method and codes are tested with the NASA Stage35. The results shows that the mesh quality of NASA Stage35 is good with improved mesh orthogonality and smoothness at the near solid wall regions. The revised free deformation method maintains both the mesh periodicity and geometry consistence. The flow calculation results are in good agreement with the experimental data. This work is of important reference value for developing design optimization and multidisciplinary analysis system of multi-stage high-speed axial compressor. © 2021, Science Press. All right reserved.