Conceptual Study of a Low Cost Turbojet Engine

Abstract

One candidate for an inexpensive engine is a turbojet constructed by adding a combustion chamber and nozzle to a commercial turbocharger for a reciprocating engine. Two turbocharger-engines were produced in this way capable of handling approximately .6 lb/sec and 1.5 lb/sec airflow. A performance analysis using thermodynamic cycle analysis techniques was done to predict the thrust that could be generated by these engines. The maximum thrust predicted was 27 lb and 67 lb dry; with an afterburner, 36 lb and 96 lb was expected. A combustion chamber and nozzle were added to the turbochargers and both were mounted on a test stand and successfully operated. Thrust was increased by various improvements to 60 lb. The performance parameters of possible interest were studied with particular emphasis placed on thrust, weight flow of the air, specific fuel consumption, compressor pressure ratio, and temperature of the gases at the compressor, turbine, and nozzle.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1976
Accession Number
ADA025652

Entities

People

  • Tommy J. Kent

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Flow
  • Air Force
  • Combustion Chambers
  • Engine Components
  • Engineering
  • Equations
  • Flow Rate
  • Fuel Nozzles
  • Fuel Systems
  • Ignition
  • Measurement
  • Mechanical Engineering
  • Pressure Measurement
  • Remotely Piloted Vehicles
  • Static Pressure
  • Test Equipment
  • Turbines

Readers

  • Aerospace Engineering
  • Combustion and Flow Dynamics.
  • Internal Combustion Engine (ICE) Technology.