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Stability analysis of a liquid fuel annular combustion chamberThe problems of combustion instability in an annular combustion chamber are investigated. A modified Galerkin method was used to produce a set of modal amplitude equations from the general nonlinear partial differential acoustic wave equation. From these modal amplitude equations, the two variable perturbation method was used to develop a set of approximate equations of a given order of magnitude. These equations were modeled to show the effects of velocity sensitive combustion instabilities by evaluating the effects of certain parameters in the given set of equations. By evaluating these effects, parameters which cause instabilities to occur in the combustion chamber can be ascertained. It is assumed that in the annular combustion chamber, the liquid propellants are injected uniformly across the injector face, the combustion processes are distributed throughout the combustion chamber, and that no time delay occurs in the combustion processes.
Document ID
19790021056
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Mcdonald, G. H. (Tennessee Technological Univ. Cookeville, TN, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1979
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-158885
Accession Number
79N29227
Funding Number(s)
CONTRACT_GRANT: NGR-43-003-015
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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