Film Behavior in Gas-Centered Swirl-Coaxial Injectors

Abstract

Gas-centered swirl-coaxial (GCSC) injectors have enjoyed much recent interest for use in LOX-hydrocarbon rocket engines in the US. (Prior to injection, the LOX is vaporized and combusted in a preburner and is introduced to the combustion chamber as gas.) Many GCSC injectors feature a dividing plate between the initial liquid fuel flow and the gaseous oxidizer flow. Generally this plate terminates with some thickness producing separated gas flow just prior to contact with the liquid. This recirculation zone and other flow factors cause the film and spray to be nonuniform in space and time. These nonuniformities are discussed in detail and suggestions are given for producing more uniform and predictable sprays. In addition to the influence of geometry, the impact of operating conditions is included in these studies.

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Document Details

Document Type
Technical Report
Publication Date
Oct 14, 2008
Accession Number
ADA502467

Entities

People

  • Douglas G. Talley
  • Hsin-yuan Simon Lyu
  • Kristen A. Clark
  • Malissa D. Lightfoot
  • Stephen A. Danczyk

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Chambers
  • Combustion
  • Combustion Chambers
  • Engines
  • Flow
  • Flow Rate
  • Fluid Mechanics
  • Gas Flow
  • Geometry
  • Injectors
  • Mass Flow
  • Nonuniform
  • Orientation (Direction)
  • Rocket Engines
  • Rockets
  • Thickness

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Space
  • Space - Hall-Effect Thruster