Fundamentals of Acoustic Instabilities in Liquid Propellant Rockets Under Transcritical Conditions.

Abstract

The objective of this research was to improve understanding of the mechanisms by which flow, mixing and combustion processes are coupled to acoustic fields in liquid-propellant rocket motors. Particular attention was focused on analyses of amplification mechanisms coupled with finite-rate chemical reactions by use of numerical and analytical methods. Special attention was focused on LOX/GH2 systems and suggested a possible explanation of threshold phenomena found in liquid-propellant rockets. Reduced chemistry was developed for describing LOX combustion in GH2. and approaches towards explaining droplet burning-time minima in the transcritical regime were completed. The results can be helpful in improving knowledge of combustion mechanisms and combustion instability in liquid-propellant rocket motors at high pressures.

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Document Details

Document Type
Technical Report
Publication Date
Dec 29, 1999
Accession Number
ADA372407

Entities

People

  • Forman A. Williams

Organizations

  • University of California, San Diego

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemical Reactions
  • Chemistry
  • Combustion
  • Computational Science
  • Engines
  • Equations
  • Heat Transfer
  • High Pressure
  • Instability
  • Liquid Oxygen
  • Liquid Propellant Rocket Engines
  • Liquid Propellants
  • Materials Science
  • Propellants
  • Propulsion Systems
  • Rocket Engines
  • Rockets

Fields of Study

  • Physics

Readers

  • Ocean-Atmosphere Mesoscale Modeling, Data Assimilation, and Flux Boundary Layers
  • Rocket Propulsion.
  • Systems Analysis and Design