Accession Number:

ADA158559

Title:

Investigation of the Flame-Acoustic Wave Interaction during Axial Solid Rocket Instabilities.

Descriptive Note:

Interim scientific rept.,

Corporate Author:

GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING

Personal Author(s):

Report Date:

1985-04-01

Pagination or Media Count:

19.0

Abstract:

The primary objective of this study is the determination of the fundamental mechanisms responsible for the driving of axial instabilities by solid propellant flames. During the report period, the behavior of a premixed flame stabilized on the side wall of a duct in the presence of an axial acoustic field was investigated both theoretically and experimentally. The developed model solutions show that driving occurs due to the combustion process heat addition while outside the reaction zone the waves are damped by viscous processes. This damping increases as the thickness of the acoustic boundary layer increases. Experimental facilities for studying oscillating duct flow sin the presence and absence of flames were developed. Cold flow studies verified the presence of an excess velocity region within the acoustic boundary layer i.e., the Richardson Effect and the dependence of the boundary layer thickness upon the frequency and wall injection velocity. Reactive flow studies showed that the behavior of the flame depends upon its location relative to the standing acoustic wave. When the flame was positioned next to a velocity antinode, unexpected instabilities appeared on its surface eventually resulting in severe flame distortion. Also, the measured C-C and C-H radiation signals were periodic and they oscillated with the same frequency as the acoustic wave. Keywords Flame-Acoustic interactions and Flame driving.

Subject Categories:

  • Acoustics
  • Combustion and Ignition
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE