Combustor Design for Low Cost Expendable Turbojets

Abstract

The development of two experimental burners was completed as part of a project to evaluate the suitability of the use of converted reciprocating engine turbochargers as expendable jet engines for remotely piloted vehicles. As a result of analytic studies, Burner 'A' was constructed as a reverse flow burner and was designed to accept a mass flow up to 0.75 lbm/sec. Burner 'B' was also reverse and designed for a mass flow up to 1.5 lbm/sec. Both burners operated successfully on their respective turbochargers.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1976
Accession Number
ADA024541

Entities

People

  • Raymond L. Greene

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Air Force
  • Aircrafts
  • Combustion
  • Combustion Chambers
  • Combustors
  • Engineering
  • Fuel Nozzles
  • Fuel Systems
  • Jet Aircraft
  • Jet Engines
  • Mach Number
  • Numbers
  • Pressure Measurement
  • Remotely Piloted Vehicles
  • Turbines
  • Turbojet Engines

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerospace Engineering.
  • Combustion and Flow Dynamics.