Title: Study of the Flow Turning Loss in a Simulated Solid Rocket Motor
Abstract: The flow turning loss, one of the processes that damp instabilities in solid rockets, is caused by the interaction of the axial acoustic field in an unstable motor with the flow of combustion products from the propellant surface. While state-of-the-art stability models generally account for the flow turning loss, its characteristics have never been fully investigated. In order to study the contribution of the flow turning loss to acoustic stability, a onedimensional acoustic stability equation that includes the flow turning loss term was derived, providing the theoretical background and expressions needed to guide an experimental study. Experiments were performed to determine the dependence of the flow turning loss upon the injection and mean-flow Mach numbers and the location of the flow turning region relative to the standing acoustic wave. These studies showed that the flow turning loss strongly depends upon the magnitude of the gas velocity at the propellant surface and the location of the flow turning region relative to the standing pressure wave. A simple numerical simulation of the experimental setup was developed and its predictions were found to agree well with the measured data. Nomenclature a = speed of sound E~ = quantity representative of the total acoustic energy in the cavity H = height of two-dimension al duct used in analysis hT = total specific enthalpy i = unit vector in the axial x direction j = unit vector in the transverse y direction L = length of duct m = mass flux rate u = axial, x direction, component of velocity V = velocity vector v = transverse, y direction, component of velocity Subscripts b = value at side wall t = average over time y = average over the y direction 0,1,2 = acoustic order
Publication Year: 1995
Publication Date: 1995-03-01
Language: en
Type: article
Indexed In: ['crossref']
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