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http://dx.doi.org/10.6108/KSPE.2015.19.5.022

Hot Firing Tests of a Gas Generator for Liquid Rocket Engine using a Turbine Manifold Simulator  

Lim, Byoungjik (Combustion Chamber Team, Korea Aerospace Research Institute)
Kim, Munki (Combustion Chamber Team, Korea Aerospace Research Institute)
Kim, Jonggyu (Combustion Chamber Team, Korea Aerospace Research Institute)
Choi, Hwan-Seok (Combustion Chamber Team, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.19, no.5, 2015 , pp. 22-30 More about this Journal
Abstract
A gas generator which generates turbine driving gas by burning a part of propellants is used in an open cycle liquid rocket engine and as a main component of an open cycle liquid rocket engine autonomous hot firing tests are required to investigate the combustion performance and characteristics of the gas generator. However, since the combustion gas generated by a gas generator is choked at the turbine nozzle in the turbine manifold, it is necessary to consider the internal volume of turbine manifold as well as that of the gas generator for correct investigation of the combustion performance, characteristics, and acoustic characteristics of the gas generator. Therefore, in the paper hot firing test results of a gas generator with a turbine manifold simulator are described and characteristic prediction using the autonomous test of a gas generator is explained.
Keywords
Gas Generator; Liquid Rocket Engine; Turbine Manifold; Pressure Fluctuation; Choking Nozzle;
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