Non-Uniform Flow in Multistage Axial Compressors.

Abstract

This paper examines a specific example of distorted inlet flow through the two-dimensional annulus of a multistage compressor which can be solved completely. It is shown that the essential features of this exact solution, including stall, may be described by a two-parameter family of profiles and that an integral technique, utilizing these elementary profiles, will yield essentially the same results. While it is not clear that comparable success would hold for the three-diminsional problem, the results confirm the contention that the two-dimensional problem may be treated with acceptable accuracy by an integral technique.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1977
Accession Number
ADA039133

Entities

People

  • Frank E. Marble

Organizations

  • California Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Complex Variables
  • Compressors
  • Computational Science
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Flow
  • Flow Fields
  • Geometry
  • Integrals
  • Linear Differential Equations
  • Scientific Research
  • Steady Flow
  • Three Dimensional
  • Two Dimensional

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Systems Analysis and Design