Afterburning Suppression Kinetics in Rocket Exhaust

Abstract

The exhaust gases from the nozzle of a rocket motor usually contain significant proportions of unburned fuel. This fuel mixes turbulently with ambient air as the exhaust jet expands and may burn causing a substantial elevation of temperature in the exhaust plume. The secondary combustion is affected by factors such as velocity and altitude of the missile, motor thrust level, pressure, temperature at the nozzle exit plane. The addition of certain species such as HBR, K2SO4 etc. have been observed to inhibit the afterburning process. The inhibition of afterburning process is of great significance to the Air Force. However, the kinetic mechanism for the afterburning suppression is not understood. A research program has been initiated at the Rocket Propulsion Laboratory to investigate the afterburning suppression kinetics by Dr. Jay Eversole. The fundamental research objective will be to determine the chemical reaction mechanisms that are critical to this afterburning suppression phenomena. Keywords: Combustion inhibition.

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Document Details

Document Type
Technical Report
Publication Date
Jun 30, 1983
Accession Number
ADA217597

Entities

People

  • Trilochan Singh

Organizations

  • Wayne State University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Adiabatic Flames
  • Afterburning
  • Air Force
  • Chemical Reactions
  • Combustion
  • Differential Equations
  • Equations
  • Exhaust Gases
  • Exothermic Reactions
  • Experimental Data
  • Gases
  • Mechanical Engineering
  • Reaction Mechanisms
  • Rocket Exhaust
  • Rocket Propulsion
  • Surface Temperature

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.