Semi-structured meshes for axial turbomachinery blades

DOI<link itemprop=identifier href="https://doi.org/10.1002/(SICI)1097-0363(20000315)32:5<569::AID-FLD975>3.0.CO;2-V" /><569::AID-FLD975>3.0.CO;2-V 10.1002/(SICI)1097-0363(20000315)32:5<569::AID-FLD975>3.0.CO;2-VzbMath0981.76064OpenAlexW2051027383MaRDI QIDQ4494662

A. I. Sayma, L. Sbardella, M. Imregun

Publication date: 7 August 2000

Full work available at URL: https://doi.org/10.1002/(sici)1097-0363(20000315)32:5<569::aid-fld975>3.0.co;2-v

zbMATH Keywords

turbomachinery bladesmesh generatortransonic fan bladesemi-structured meshestotally unstructured mesh

Mathematics Subject Classification ID

Transonic flows (76H05) Finite difference methods applied to problems in fluid mechanics (76M20) Mesh generation, refinement, and adaptive methods for boundary value problems involving PDEs (65N50)

Related Items (2)

Whole-annulus aeroelasticity analysis of a 17-bladerow WRF compressor using an unstructured Navier–Stokes solver ⋮ Transonic Rotor/Stator Interaction Using a 3-D Linearised Unsteady Viscous Flow Model

Cites Work

• Approximate Riemann solvers, parameter vectors, and difference schemes
• On central-difference and upwind schemes
• Automatic numerical generation of body-fitted curvilinear coordinate system for field containing any number of arbitrary two-dimensional bodies
• Unnamed Item

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