Accession Number:

ADA615844

Title:

A Computational Study of Transverse Combustion Instability Mechanisms

Descriptive Note:

Technical paper, May-Jul 2014

Corporate Author:

AIR FORCE RESEARCH LAB EDWARDS AFB CA ROCKET PROPULSION DIV

Report Date:

2014-07-01

Pagination or Media Count:

16.0

Abstract:

Computational fluid dynamics simulations are used to study spontaneous combustion instabilities in a rectangular chamber that contains seven coaxial injector elements. The simulation predicts self-excited transverse oscillations that have variable amplitudes, similar to what is seen in a companion experiment. Several processes are identified in the simulation that may promote the rise of instability by increased heat release during a local compression, including the interaction between vortices shed from adjacent injectors and interactions between flames and the combustor walls.

Subject Categories:

  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE