Turbojet Thrust Augmentation by Sudden Expansion Type Afterburner.

Abstract

An axisymmetric sudden expansion afterburner coupled to a small turbojet engine in various configurations, has been studied. The effects of length to diameter ratio variation on performance were investigated. The maximum thrust achieved was 62 pounds without afterburner augmentation, and 92 pounds with afterburner augmentation, each with turbine inlet temperature of 1700F. Various methods of air injection into the combustion zone of the afterburner were examined, and found to be ineffective for purpose of thrust augmentation. An eccentrically mounted afterburner with an eccentricity of 1.25 inch has been operated successfully. The performance of the propulson system decreased in this configuration onlyby a negligible amount. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1978
Accession Number
ADA081901

Entities

People

  • Rami Dotan

Organizations

  • Air Force Institute of Technology

Tags

DTIC Thesaurus Topics

  • Afterburners
  • Afterburning
  • Air Flow
  • Combustion
  • Combustion Chambers
  • Engineering
  • Engines
  • Ignition Lag
  • Jet Engines
  • Measurement
  • Mechanical Engineering
  • Propulsion Systems
  • Thermal Efficiency
  • Thermal Propulsion Systems
  • Thrust Augmentation
  • Turbines
  • Turbojet Engines

Readers

  • Aerospace Engineering