Open AccessMesh Generation for Turbomachinery Blade Passages with Three-Dimensional Endwall Features
Author(s) -
Feng Wang,
Luca di Mare
Publication year - 2017
Publication title -
journal of propulsion and power
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.913
H-Index - 101
eISSN - 1533-3876
pISSN - 0748-4658
DOI - 10.2514/1.b36356
Subject(s) - turbomachinery , shroud , polygon mesh , robustness (evolution) , gas compressor , computational fluid dynamics , mesh generation , computer science , blade (archaeology) , gas turbines , axial compressor , turbine blade , turbine , aerospace engineering , mechanics , mechanical engineering , engineering , structural engineering , physics , finite element method , computer graphics (images) , biochemistry , chemistry , gene
Turbomachinery blade passages are conventionally meshed by sweeping a meshfrom a reference stream surface to other stream surfaces along the blade span. Thisapproach is widely used in the gas turbine industry but it becomes problematic forsimulations where the flow close to the endwall region is important. This is due to thefact that this approach has to make geometrical approximations for endwall features.This paper presents a method that overcomes this difficulty and generates optimalmeshes for blade passages without geometrical approximations. The robustness of themethod is demonstrated by meshing a multi-stage compressor with shroud cavities.Simulations of the compressor show the penalty of using meshes with approximatedendwall features and the benefit of using meshes generated by the current method.These demonstrate that the proposed method contributes to the improvement of computationalfluid dynamics as a reliable design tool for turbo-machines
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