Laser Schlieren and Ultraviolet Diagnostics of Rocket Combustion,

Abstract

A low pressure oxygen/hydrogen turbine drive combustor hot-fire test series was conducted on the Turbine Drive Combustor Technology Program. The first objective of the test series was to gather data on an axisymmetric combustion system to support anchoring of a new combustion/fluid dynamics computer code under development on the same contract. The second objective was to gain insight into low mixture ratio combustion characteristics of coaxial injector elements. This paper discusses the diagnostic test setup used in the hot-fire test program and the results obtained. Most of the data collected is in the form of high-speed laser Schlieren cinematography and ultraviolet cinematography of the actual ignition and combustion process inside a combustion chamber system. Details of the 9000 frames/sec laser Schlieren system and the ultraviolet cinematography system are described. The combustion model utilized in the program was designed to simulate the Space Shuttle Main Engine (SSME) oxidizer preburner ignition conditions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1984
Accession Number
ADP200296

Entities

People

  • S. C. Fisher

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Chambers
  • Cinematography
  • Combustion
  • Combustion Chambers
  • Combustors
  • Computational Fluid Dynamics
  • Engines
  • Fires
  • Fluid Dynamics
  • Ignition
  • Ignition Lag
  • Space Shuttles

Fields of Study

  • Engineering
  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computer Science/Computer Engineering/Data Science/Digital Signal Processing.
  • Pulsed Power and Plasma Physics.

Technology Areas

  • Directed Energy
  • Space
  • Space - Hall-Effect Thruster