A Simulation of Viscous Incompressible Flow Through a Multiple-Blade-Row Turbomachinery with a High-Resolution Upwind Finite-Differencing Scheme.

Abstract

This report investigates the feasibility of a numerical solution for a incompressible viscous flow through a multiple-blade-row turbomachinery. The numerical method used is a three-dimensional incompressible Navier-Stokes solver based on flux-difference splitting, and an implicit high-resolution scheme. In order to validate the numerical predictions, the measurements from a preswirl High Reynolds Number Pump (HIREP) experiment are selected for the purpose of comparisons. Comparisons between predictions and measurements are presented. The comparisons include the surface pressure distribution, the wake behind the trailing edge, and flow visualization on the hub and blade surfaces.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1994
Accession Number
ADA294309

Entities

People

  • Cheng-i. Yang

Organizations

  • Naval Surface Warfare Center Carderock Division

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Differential Equations
  • Equations Of Motion
  • Flow
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • High Resolution
  • Measurement
  • Navier Stokes Equations
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Static Pressure
  • Three Dimensional
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)