FLAME-PILOTING MECHANISMS IN LIQUID PROPELLANT ROCKET ENGINES

Abstract

A program was directed toward the systematic investigation of flame- piloting mechanisms in liquid rocket engines and their role in combustion instability. The mechanism which gained the most attention was recirculation. The program included experimental analysis of rocket engine performance as affected by external disturbances, minor geometry changes, and propellant state changes; and theoretical analysis of mixing in chemically reacting systems. Principal conclusions drawn from the results of the program are: (1) Characteristics of the injector and of the propellants are principal factors in the chemical kinetics and fluid dynamics within rocket engine combustors. (2) For the rocket engine and perturbation technique used, engine stability is unaffected by perturbations of the recirculation zone. This does not necessarily eliminate the process of recirculation as a factor in engine stability.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1966
Accession Number
AD0655792

Entities

People

  • Aubrey C. Tobey
  • E. Karl Bastress

Organizations

  • Arthur D. Little

Tags

DTIC Thesaurus Topics

  • Burning Rate
  • Chemical Kinetics
  • Chemical Reactions
  • Combustion
  • Combustion Chambers
  • Combustors
  • Continuous Chemical Reactors
  • Fluid Dynamics
  • Ignition
  • Liquid Oxygen
  • Liquid Propellant Rocket Engines
  • Liquid Propellants
  • Measurement
  • Pressure Measurement
  • Propellants
  • Rocket Engines
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Rocket Propulsion.
  • Theoretical Analysis.