Composite Grid and Finite-Volume LU (Lower-Upper) Implicit Scheme for Turbine Flow Analysis.

Abstract

A composite grid was generated in an attempt to improve grid quality for a typical turbine blade with large camber in terms of mesh control, smoothness, and orthogonality. This grid consists of the C-grid in the immediate vicinity of the blade and the H-grid in the upstream region and in the middle of the blade passage between the C-grids. It provides good boundary layer resolution around the leading-edge region for viscous calculation, has orthogonality at the blade surface and slope continuity at the C-H interface, and has flexibility in controlling mesh distribution in the upstream region without using excessive grid points. This composite grid eliminates the undesirable qualities of a single grid when generated for a typical turbine geometry. A finite-volume lower-upper (LU) implicit scheme can be used in solving for the turbine flows on the composite grid. This scheme was demonstrated to be robust and efficient for both external and internal flows in a broad flow regime.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1987
Accession Number
ADA180145

Entities

People

  • Kestutis C. Civinskas
  • Seokkwan Yoon
  • Yung K. Choo

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aeronautics
  • Army Aviation
  • Boundaries
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer Programs
  • Equations
  • Euler Equations
  • Flow
  • Fluid Dynamics
  • Geometry
  • Grids
  • Leading Edges
  • Three Dimensional
  • Turbine Blades
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)