Accession Number:

ADA025652

Title:

Conceptual Study of a Low Cost Turbojet Engine

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1976-03-01

Pagination or Media Count:

87.0

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 lbsec and 1.5 lbsec 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.

Subject Categories:

  • Pilotless Aircraft
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE