Accession Number : ADA258005
Title : Oscillatory Internal Flow Fields Studies
Descriptive Note : Final rept.
Corporate Author : UNITED TECHNOLOGIES CORP SAN JOSE CA CHEMICAL SYSTEMS DIV
Personal Author(s) : Shaeffer, C W ; Brown, R S
Report Date : Aug 1992
Pagination or Media Count : 91
Abstract : Experimental studies have been conducted to measure the structure of oscillatory waves in the presence of the rotational flow field which characterizes the internal ballistics of solid propellant rockets. Cold flow results demonstrated that extensive rotational behavior of oscillatory flows are associated with the types of flows. These rotational effects extend over significant portions of the chamber volume, both radially and axially. Radial variations in the amplitude of the axial oscillatory velocity appear to be related to radial momentum effects. The distance between the peaks correlates with approximate solutions of the radial momentum equation. Further downstream, convection effects from the mean flow distorts these radial variations at low surface Mach numbers. Significant nonlinear behavior was observed near the wall at three axial stations. At lower surface mach numbers, this behavior extended all the way across the chamber at the downstream location (5.46 diameters). This nonlinear behavior occurred at a much lower oscillatory pressure than previously expected. From the observed effect of surface Mach number, it appears the nonlinearities are associated with interactions between the mean and oscillatory flows.
Descriptors : *COMBUSTION , *FLOW FIELDS , *AMPLITUDE , *OSCILLATION , VELOCITY , STATIONS , DIAMETERS , VOLUME , INTERACTIONS , INTERNAL , BEHAVIOR , ROCKETS , MOMENTUM , CHAMBERS , INSTABILITY , BALLISTICS , NUMBERS , EQUATIONS , MEAN , MACH NUMBER , COLD FLOW , SOLID PROPELLANTS , PRESSURE , STRUCTURES , CONVECTION , SOLIDS , VARIATIONS , SURFACES , PROPELLANTS
Subject Categories : Fluid Mechanics
Combustion and Ignition
Distribution Statement : APPROVED FOR PUBLIC RELEASE