A Study on Straight Flow Annular Combustor for Small Scale Turbojet Engine

Abstract

A combustor of a small scale turbojet engine for the a flight vehicle was studied and appropriateness for design requirements were evaluated through the cold test and the hot test. For the purpose of studying flame stability of a pilot atomizer under ignition, firing tests were carried out at various fuel supply pressures. As the result of the experiment and design revision, optimal combination of the air blast type the main fuel nozzle by design requirements was obtained without fuel splash phenomenon and unstable flame. The combustor was designed and evaluated with detailed investigation and experiments. As the result of the hot test, it was confirmed that the combustor in this study had proper profile factor, pattern factor, flammability limit, total pressure loss and combustor efficiency.