The Effects of Pressure and an Acoustic Field on a Cryogenic Coaxial Jet

Abstract

OBJECTIVES: Document the nature of the acoustic wave/coaxial-jet injector interaction * Map a range of input variables * Explore application of the data and the findings for rocket combustion instability. MOTIVATION: Combustion instability has always been one of the most complex phenomena in liquid rocket engines * High amplitude and high frequency acoustic instabilities (screaming), can lead to local burnout of the combustion chamber walls and injector plates * APPROACH: Using the AFRL supercritical facility * Span sub and supercritical pressures * Cryogenic temperatures * Acoustic Field. A coaxial injector design based on the single-jet cryogenic injector used in all previous studies (well characterized) * A specially-designed acoustic driver * Single-shot shadowgraph.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 22, 2004
Accession Number
ADA446452

Entities

People

  • Bruce Chehroudi
  • Doug Talley
  • Dustin Davis

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Acoustic Fields
  • Acoustic Impedance
  • Acoustic Waves
  • Air Force Research Laboratories
  • Chambers
  • Combustion
  • Combustion Chambers
  • Engines
  • Flow
  • Flow Rate
  • Fluid Mechanics
  • Frequency
  • High Pressure
  • Liquid Oxygen
  • Mass Flow
  • Measurement
  • Rocket Engines

Fields of Study

  • Physics

Readers

  • Acoustical Oceanography.
  • Combustion and Flow Dynamics.
  • International Relations, focusing on Korea-Africa and North Korea-South Korea relations, and Nigeria-Latin American Relations.