Accession Number : AD0752205
Title : 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.
Descriptive Note : Final rept.,
Corporate Author : UTAH UNIV SALT LAKE CITY DEPT OF MECHANICAL ENGINEERING
Personal Author(s) : Flandro,Gary A. ; Isaacson,L. King ; Boyd,David L. ; Linn,Phillip T.
Report Date : AUG 1972
Pagination or Media Count : 354
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)
Descriptors : (*SOLID ROCKET PROPELLANTS, *COMBUSTION), ACOUSTICS, TURBULENCE, FLOW FIELDS, INTERIOR BALLISTICS, VORTICES, VORTEX GENERATORS, SCREAMING COMBUSTION, BOUNDARY VALUE PROBLEMS, ONE DIMENSIONAL FLOW, THREE DIMENSIONAL FLOW
Subject Categories : Combustion and Ignition
Solid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE