Application of Finite Element Code Q3DFLO-81 to Turbomachinery Flow Fields.

Abstract

Through flow and blade to blade calculations were made. The Q3DFLO-81 code was operated on an IBM 370-3033 mainframe computer. The flow through a single stage axial research compressor was computed and compared with both probe survey and stage performance map measurements. Swirling flow produced by a vaned out flow generator for a radial diffuser test facility was calculated for both large low speed and small scale high speed versions of the device. Flow through a two dimensional compressor cascade of controlled diffusion blade shapes was calculated and the results compared with experimental data, and with predictions obtained using the NASA code QSONIC. Keywords: Finite Element Code; Turbomachinery Flow Fields; and Through-Flow Calculations.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1984
Accession Number
ADA168773

Entities

People

  • Ch. Hirsh
  • F. Neuhoff
  • H. D. Schulz
  • R. P. Shreeve

Organizations

  • Naval Postgraduate School

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Compressors
  • Computational Fluid Dynamics
  • Computers
  • Diffusers
  • Eddies (Fluid Mechanics)
  • Flow
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Measurement
  • Mechanical Engineering
  • Pressure Distribution
  • Test Facilities
  • Three Dimensional
  • Turbines
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.