The Influence of Mean Flow on Rocket Motor Combustion Instability. Volume I. Basic Analysis, Mean Flow Application to the T-Burner. Volume II. Effect of Turbulence on Acoustic Waves in a Cavity. Volume III. Vortex Generated Sound in Solid Propellant.
Abstract
The report consists of two problems related to acoustic combustion instability in solid propellant rockets. In the first problem, coupled acoustic cavities with mass flux across a common boundary are studied. Since the propellant grain in a solid rocket motor may assume various configurations to meet specific performance criteria, physical models considering two or more wave-carrying systems coupled together so that acoustic motion of each is affected by the other are required in the study of acoustic instability in some motor designs. In the second problem, linear analyses employing both one-dimensional and three-dimensional flow models of the T-burner are studied to resolve which is the more appropriate representation of the growth of acoustic models yield an identical expression for the acoustic growth rate of dominant longitudinal modes in the T-burner if properly formulated. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1972
- Accession Number
- AD0752205
Entities
People
- David L. Boyd
- Gary A. Flandro
- L. King Isaacson
- Phillip T. Linn
Organizations
- University of Utah