A Physical Hypothesis for the Combustion Instability in Cryogenic Liquid Rocket Engines (Preprint)

Abstract

In this work, the author would like to portray a sketch of a unified physical picture to describe the coupling nature/strength between the chamber acoustics and the injectors. This new perspective is achieved through a physically intuitive argument combined with previously published test results for two popular injector designs, namely, coaxial and impinging jets. For the impinging-jets injectors, it is shown that the dynamic behavior of the dark-core (or breakup) zone for each jet, their lengths and thicknesses, has a profound impact on injector "sensitivity" to disturbances in its surrounding. This information is used to offer a possible explanation for the trends seen on the Hewitt stability plot in impinging-jet injectors.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Apr 21, 2008
Accession Number
ADA493559

Entities

People

  • Bruce Chehroudi

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Acoustic Fields
  • Acoustics
  • Air Force
  • Air Force Research Laboratories
  • Chambers
  • Combustion
  • Combustion Chambers
  • Energy Transfer
  • Engines
  • Frequency
  • Heat Transfer
  • High Pressure
  • Injectors
  • Liquid Oxygen
  • Measurement
  • Rocket Engines
  • Sensitivity

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Theoretical Analysis.