• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.207-210
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• 2005

The results of combustion performance test of fuel-rich gas generator with dual swirl injectors are described. By changing simulating duct and recess number(RN) of the injectors, we inspected whether the combustion instability took place. When the injectors of RN = 0.5 were used, combustion instabilities could be reduced using the simulating duct. However, the effect of the simulating duct on the gas generator with the injectors of RN = 1.5 was not significant.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.129-132
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• 2008

Combustion characteristics of a gas generator for a 30 ton-class liquid rocket engine were studied. At the early stage of development, the combustion tests of the gas generator were performed by only using the nozzle which substitute for a turbine manifold exit. Then, the extension tube was applied between the gas generator and the nozzle for imitating the resonant mode of gas generator and turbine manifold. Finally, the hot-firing tests were performed on the condition of connecting the gas generator with the turbine manifold. In the paper, the step-by-step results such as temperature distribution and pressure fluctuations were analyzed.