Single-Stage Axial Compressor Component Development for Small Gas Turbines. Volume 3. Supersonic Compressor Stage Development

Abstract

The report describes the development of the complete stage for the 2. 8:1 supersonic axial compressor design. The performance of the overall stage including the exit stators and interconnecting duct was evaluated through experimental testing with the rotor and inlet guide vanes developed under the previous phase of this program. The experimental results are analyzed and compared with the design data and criteria for each of the blade rows as well as the overall stage.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0857498

Entities

People

  • Charles H. Muller
  • Leslie R. Cox

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Army Aviation
  • Compressor Components
  • Compressor Rotors
  • Compressors
  • Efficiency
  • Fabrication
  • Gas Turbines
  • Geometry
  • Guide Vanes
  • Inlet Guide Vanes
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Test Equipment
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Test and Evaluation

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow