Combustion Characteristics of Sprays

Abstract

This report provides a general description of the results of research studies aimed at providing a basic understanding of turbulent spray combustion. The environment in a liquid rocket engine can lead to complex flow/flame/droplet interactions which can substantially modify the droplet evaporation and combustion processes which can affect the stability characteristics of the rocket engine. The various studies conducted during this research project were: spray combustion in stagnation-point flow, thermo-diffusive flame instabilities, the influence of vorticity on flame stability/stabilization, non-planar flame configurations. Areas of future research are presented along with a discussion as to how the results of the investigation can be applied to liquid rocket engine combustion.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1989
Accession Number
ADA213651

Entities

People

  • Siavashi H. Sohrab

Organizations

  • Northwestern University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Acoustic Waves
  • Boundary Layer
  • Burning Rate
  • Chemical Reaction Properties
  • Chemical Reactions
  • Combustion
  • Computational Fluid Dynamics
  • Convection
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Mechanical Engineering
  • Photographs
  • Physics Laboratories
  • Rocket Engines
  • Space Systems
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.