• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.67-72
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• 2015

The analysis has been performed on the blockage effect at the propellant flow passage in a liquid rocket engine. This simulates an example of emergency situation where flow passage is partially blocked. The analysis method has been validated by predicting the pump head and flow rate within 1% precision against the measured data of turbopump-gas generator coupled test. When the oxidizer passage is reduced it is predicted that the mixture ratio decreases, the oxidizer pump head increases and the gas generator pressure increases. When the fuel passage is reduced it is predicted that the mixture ratio increases, fuel flow rate decreases and the fuel pump head increases.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2006.06a
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• pp.237-238
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• 2006

Vibration incidents hardly happen when a turbine generator usually installed in LNG carrier is operated, different from diesel engine generator. The purpose of this paper is to introduce an actual vibration incident, which hardly occurred in case of turbine generator, and describe all possible countermeasures to prevent from vibrations during operation.

• Proceedings of KOSOMES biannual meeting
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• 2018.06a
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• pp.175-175
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• 2018

• Proceedings of the KIPE Conference
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• 1999.07a
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• pp.423-426
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• 1999

This paper describes a driving scheme of the series hybrid electric vehicle that we have developed. Both series HEV and parallel HEV are well known. We chose series HEV because it provides good energy efficiency in urban driving and operates in all-electric mode in performance. And engine-Generator is driven at constant speed with constant load to maintain the low emission. And the battery supplies power during high-load and receive energy during low-load

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.99-103
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• 2017

As a development test of the 75-tonf LOx/Kerosene liquid rocket engine for KSLV-II first Stage Engine, hot firing test of 75-tonf engine are performed. The current status of development test on first stage 75-tonf engine system including combustion chamber, turbopump, gas generator, propellant supply system are presented. During the 75tonf engine test campaign, the development of startup sequence of LOx-Kerosene engine system, engine startup using pyrostarter, ignition of gas generator, steady operation and engine shutdown is successfully performed. As a passenger test during engine hot firing tests, Thrust Vector Control system (TVC) of the engine are also evaluated during engine hot firing test. The results of hot firing test of 75-tonf thrust engine system will be used for the design confirmation and performance evaluation of 75 tonf engine system for KSLV-II first Stage.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.55-65
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• 2020

In this paper, development and acceptance test results of 75-tonf class liquid rocket engine gas generators are described. Up to now, more than 330 times and cumulative time of 7,000 seconds gas generator autonomous tests have been carried out with 44 gas generator models. Through the tests it was verified that 75 tonf gas generator shows very reliable and reproducible characteristics in terms of chamber pressure, combustion efficiency, pressure loss, combustion stability, burnt gas temperature, and etc. 5 gas generators which are the last series of 75 tonf gas generator for the Korea Space Launch Vehicle II, will be manufactured until end of 2019 and their acceptance tests will be executed at the first half of 2020.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.5
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• pp.91-97
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• 2015

After-burner test facility for gas generators of 75 tonf class liquid rocket engines was designed, which was verified by the facility certification test of the Combustion Chamber Test Facility(CCTF). The purpose of the certification test of the after-burner test facility is to verify the combustion stability of gas torches equipped in the gas generator and the after-burner test facility by using methane and oxygen gases. In the case of the autonomous test, the supply system provided steadily methane and oxygen gases to the after-burner system without pressure drop. The combustion pressure of the gas torch approached the design requirement. In the case of the coupled test, the gas generator ignition and the fuel-rich exhaust gas combustion were successfully carried out, leading to the verification of the test facility.

• Journal of Energy Engineering
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• v.25 no.4
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• pp.133-140
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• 2016

Thermoelectric generator, which is known as using Seebeck effect, have been widely applied in many industrial parts, for instance, from submarine to equipments capable of producing hot or cooling water. Its usefulness was verified in terms of producing electric power using temperature difference and vice versa. Application on thermoelectric generator has been mainly forced on exhaust gas of automotive engine so far. In this study, the possibility was investigated whether electric power could be produced by using cooling water in automotive engine. As the result, it showed that electric power had differences depending on shapes of power auxiliary apparatus and, in this experiment, maximum of electric power was 1.5 voltage.

• Journal of Hydrogen and New Energy
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• v.23 no.3
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• pp.236-242
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• 2012

This study has been carried out the experiment for the possibility of biogas reforming using waste heat. The source of this waste heat is the exhaust gas from a small-sized gas engine generator. For recovering the waste heat, Two-stage heat exchanger is manufactured. The two-stage heat exchanger is composed of a heat exchanger for the exhaust gas and a heat exchanger for the water. This two-stage heat exchanger is used for reforming the biogas by means of on-site hydrogen production at the small-sized gas engine generator. The two-stage heat exchanger is coupled with the biogas reformer which is a kind of catalytic reformer. To confirm a heat recovery efficiency of the two-stage heat exchanger, temperature differences of inlet and outlet locations are measured. Also, the variations of syngas concentrations with various biogas flow rates are investigated. As a result using manufactured two-stage heat exchanger, the biogas can be reformed from waste heat recovery. This experiment suggests that the exhaust gas heat exchanger is available for reforming the biogas.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.93-96
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• 2011

A genetic algorithm (GA) has been employed to optimize the major design variables of the liquid rocket engine. Mass flow rate to the main thrust chamber, mass flow rate to the gas generator and chamber pressure have been selected as design variables. The target engine is the open gas generator cycle using the LO2/RP-1 propellant. The objective function of design optimization is to maximize the specific impulse with condition of energy balance between the pump and the turbine. The properties of the combustion chamber have been obtained from CEA2. Pump & turbine efficiencies and properties of the gas generator have been modeled mathematically from reference data. The result shows 3~4% errors for the specific impulse and 2~6% errors for the pump power of the gas generator cycle compared to references.