Janus, J. Mark
Date of Degree
Graduate Thesis - Open Access
Master of Science
A generalized grid based technique was developed for handling the relative motion of grids in CFD simulations involving rotating machineries. In the present method, the relative motion between the grid blocks is handled by splitting the cellaces at the interface and updating the grid data structure appropriately. The resulting grid will have cells and cellaces with an arbitrary number of nodes and which are stored in a cellace based data structure. The current methodology is developed for cells with any number of nodes. However, the present work supports only tetrahedral elements at the interface of the rotating grid-blocks at the beginning of the simulation. Also the present approach can handle multiple objects in the domain of interest which are rotating in arbitrary directions. The current approach was tested by rotating a generalized grid for a single un-ducted SR7 propeller with eight blades designed with 41 degrees of sweep at the tip. This was also tested for two counter rotating SR7 propellers. After every rotation the new grid was tested for negative volumes, folded cellaces, proper connectivity of nodes forming the cellaces, and for gaps. Preliminary work has been conducted to couple the grid generation strategy to a generalized grid based flow solver.
Singh, Rajkeshar, "Application of Generalized Grids to Turbomachinery CFD Simulations" (2002). Theses and Dissertations MSU. 705.