Test of an Axial Compressor Stage Designed for a Total Pressure Ratio of Three to One

Abstract

Complete experimental results are presented from tests of a supersonic axial-compressor stage designed for a tip speed of 1600 ft/sec, a stage total pressure ratio of 3.0 and an inlet hub/tip radius ratio of 0.75. At design speed, the compressor passed 70 percent of design flow, achieved a stage total pressure ratio of 2.25, and achieved isentropic efficiencies of 0.74 for the rotor and 0.61 for the stage. This poor performance was attributed to an excessive increase of rotor deviation angle as rotor incidence increased at part speed. A proposed solution to this problem is described.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1974
Accession Number
AD0778844

Entities

People

  • Arthur J. Wennerstrom
  • George R. Frost
  • Robert D. Derose

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Barometric Pressure
  • Computer Programming
  • Computer Programs
  • Fluid Dynamics
  • Measurement
  • Metacentric Height
  • Molecular Orbital Theory
  • Plastic Explosives
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Test Facilities
  • Three Dimensional
  • Turbines
  • Two Dimensional

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.

Technology Areas

  • Hypersonics