Improvement of the Performance of a Turbo-Ramjet Engine for UAV and Missile Applications

Abstract

An existing turbo-ramjet engine was modified in order to increase the produced thrust and sustain combustion at increased freejet Mach numbers. The engine's afterburner fuel system was redesigned to improve the vaporization and atomization of the fuel. The engine performed satisfactorily at speeds up to Mach 0.3, producing 100% more thrust over the baseline turbojet. The data acquisition system of the turbo-ramjet engine's performance measurement in a freejet facility was also updated. Various Computational Fluid Dynamics models of the flow through the turbo-ramjet engine were developed to visualize the flow and to predict the engine performance at different Mach numbers.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 2003
Accession Number
ADA420553

Entities

People

  • Dimitrios Krikellas

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Carburetors
  • Computational Fluid Dynamics
  • Computational Science
  • Fluid Dynamics
  • Fuel Systems
  • Heat Transfer
  • Ignition Lag
  • Jet Aircraft
  • Measurement
  • Pressure Distribution
  • Ramjet Engines
  • Turbine Components
  • Turbines
  • Turbofan Engines
  • Turbojet Engines
  • Unmanned Aerial Vehicles

Fields of Study

  • Physics

Readers

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