This paper deals with the analysis of liquid fuel spray combustion in an idealized gas turbine combustor. The flow, which is assumed to be one dimensional, is divided into two regions: (i) the heat up region and (ii) the combustion region. Appropriate nondimensional equations have been solved for each region and the solutions matched at the common boundary. Analytical expressions have been developed for the burning velocity eigenvalue as well as for the solution in the combustion region. The effects of the properties of the fuel and the air as well as effects of the conditions prevalent within the combustor on the solution are discussed. Typical results for JP-4 fuel are presented. The research gas turbine combustor designed and built at The University of Michigan comes very close to satisfying the assumptions made in this analysis.
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