• 한국연소학회:학술대회논문집
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• 2003.12a
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• pp.139-143
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• 2003

Study on the ignition characteristics of combustor and gas generator for LOx-kerosene liquid rocket engine was performed experimentally through a series of combustion tests of sub-scale engine combustor and gas generator. Characteristic of gas-torch ignitor based on gaseous methane and gaseous oxygen was compared with hypergolic ignition using propellant tri-ethyl-aluminium. Gas-torch ignitor showed good performance on igniting sub-scale liquid rocket engine combustor and gas generator. It was observed that the ignition delay is also affected by the extent of nitrogen in the combustion chamber.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.56-64
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• 2010

A system design has been conducted of the liquid rocket engine for Korean launch vehicle (KSLV-II, Korea Space Launch Vehicle II). The present turbopump-fed liquid rocket engine of vacuum thrust 76 ton and vacuum specific impulse 297 sec adopts gas generator cycle. The combustion pressure of the regeneratively cooled combustor is 60 bar. The propellant is LOx/kerosene. The engine is started by pyrostarter and the combustor is ignited by TEA (TriEthylAluminium). The engine system performance and the subsystems performance requirements are given through energy balance analysis. The combustion pressure, specific impulse and the engine mass are analyzed to be reasonable comparing with the published data. The startup analysis method which will be used in the future has been validated against the turbopump-gas generator coupled test. The tuning method for performance variation of the engine which is not actively controled has been prepared by mode analysis and performance deviation analysis.

• Proceedings of the KSME Conference
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• 2001.06d
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• pp.846-851
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• 2001

For the successful development of the main engine of KSR(Korea Sounding Rocket)-III, Korea Aerospace Research Institute(KARI) carried out the experimental study on the subscale model engines. Several types of engines were tested on the Small Liquid Rocket Engine Test Facility. One of the typical test results of a Sub. engine(Sub. Mod.3) is presented here. It uses the Jet A-1 as fuel, liquid oxygen as oxidizer, and Tri-Ethyl Aluminium(TEA1) as ignition agent. The gas pressure feed system is adopted as a feeding mechanism and the design chamber pressure is 200psia. The physical phenomena are described in three regimes(ignition, transient, and steady state) with the pressure, thrust, flowrate and image data. And the pressure oscillation is analyzed in Fourier domain (<500Hz). Then we conclude that in this experiment, the engine shows the characteristic low frequency of 80Hz and it is stable for that frequency of pressure oscillation.