Inlet Distortion, Vorticity, and Stall in an Axial-Flow Compressor

Abstract

A new approach to defining inlet distortion factors for axial-flow compressors is presented. A summary of past analyses of inlet distortion, along with a brief review of flow-distortion definition and compressor performance, provides a background for the proposed theory. Inlet flow-distortion in terms of total-pressure fluctuations at the compressor face is vonverted to vorticity. The effects of vorticity on the internal aerodynamics of the compressor are investigated with some approximate calculations included to indicate the validity of this approach. Refinements and alternate solutions to the theory which could lead to definition of a more comprehensive and reliable definition of stall-inducing inlet distortion are included.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1972
Accession Number
AD0743725

Entities

People

  • Clinton J. Farmer

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Axial Flow
  • Axial Flow Compressors
  • Boundary Layer
  • Computational Fluid Dynamics
  • Distortion
  • Fluid Dynamics
  • Fluid Mechanics
  • Hydrodynamics
  • Jet Aircraft
  • Maps
  • Three Dimensional Flow
  • Turbofan Engines
  • Turbojet Engines
  • Two Dimensional
  • United States Naval Academy

Readers

  • Aerodynamics.
  • Systems Analysis and Design