A Geometric Modeller for Turbomachinery Applications
The creation and the modification of a model; the designer can “edit” the model by means of commands whose basic entities are points, profiles, blades,the hub and the shroud.
The refinement of the model by the distribution of points over each profile defining the blade, and then by the interpolation of new intermediate profiles between the hub and the shroud.
The construction of surfaces delimiting the blade-to-blade channel boundaries (the computational domain).
The calculation of a body-fitted coordinate system, inside the channel, by the solution of a system of differential equations.
A set of modeled turbines is shown to illustrate the results of each step.
KeywordsCurvilinear Coordinate System Basic Entity Fluid Dynamic Calculation Inlet Plane Refined Profile
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