• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.358-362
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• 2005

An effective control of the axial thrust of a turbopump is one of the critical issues for its operational stability. In order to assure the stability of a turbopump-type fuel pump for a liquid rocket engine, an axial thrust measurement system was developed and a series of axial thrust tests were performed in water environment. In the tests, the axial thrust of the fuel pump at the design flowrate satisfied the axial force condition of the bearing of the pump. Also, it was found that by using orifices with different geometries in the secondary flow passage the overall axial thrust of the pump could be controlled.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.273-277
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• 2009

An oxidizer tunnel-type pipe, which shall transport oxidizer from an oxidizer tank to a turbo-pump of an engine, studied is installed through a fuel tank located under an oxidizer tank. A tunnel-type pipe can save weight compared to a detour-type pipe, however may vary the temperature of fuel stored in a fuel tank because of a broad heat transfer area. Hence in this study the characteristics of main oxidizer pipe and thermal propagation from oxidizer to a fuel tank are monitored by a cryogenic performance test with a tunnel-type pipe. In addition, the possibility of adaptation of an oxidizer tunnel-type pipe to launcher system is also analyzed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.78-81
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• 2009

A series of hydraulic tests of a fuel pump are performed using water at a room temperature. The pump is under development for 75-ton class liquid rocket engines of the open-loop gas generator type. According to the test results, the fuel pump satisfies its design requirement and its head and efficiency at the design flowrate are higher than the expected value by the computational analysis. Also, it is found that the pressure at the rear bearing outlet is higher than expected because the inlet of bypass pipe line is narrow. Furthermore, the flowrate of the secondary flow is estimated using the pressure difference of the elbow of the bypass pipe line.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.198-204
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• 2004

Using liquefied natural gas as a fuel, water, natural gas and liquefied natural gas-cooled firing tests were conducted. With the viewpoint of characteristic velocity, and specific impulse, the effect of OF mixture ratio and fuel inlet temperature into a combustion chamber were analyzed. OF mixture ratio and fuel inlet temperature into a combustion chamber have great influence on the performance. Characteristic velocity and theoretical specific impulse attain the maximum value at 0.72~0.75 and 0.75 of OF mixture ratio, respectively. Engine performance has a tendency to increase, proportional to fuel inlet temperature into a combustion chamber affected by the regenerative cooling.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.201-208
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• 2007

A fuel pump and turbine rotordynamic design is performed for a 75 ton thrust liquid rocket engine. A distance from the rear bearing to the turbine was considered as a design parameter for load distribution of the bearings. Asynchronous eigenvalue analysis was performed as a function of rotating speeds, turbine mass and bearing stiffness to investigate critical speed of the fuel pump and turbine. From the numerical analysis, it is found that the effect of the front bearing stiffness is negligible in the critical speed due to the large mass moment of inertia of the turbine. With the rear bearing stiffness over $2{\times}10^{8}N/m$ and the turbine mass below 20 kg, the critical speed of the fuel pump and turbine in long shaft case is at least 70 % higher than the operating speed 11,000 rpm.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.1
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• pp.17-25
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• 2017

An experimental study was performed for the combustion-field visualization of the burner which burns the liquid hydrocarbon fuel atomized by an ultrasonic oscillator. Configurations of the flame and temperature gradient were caught by both high-speed camera and thermo-graphic camera, and those images were analyzed in detail through a post-processing. In addition, the fuel consumption was measured using the balance during the combustion reaction. As a result, the consumption of atomized fuel increased with the increasing flow-rate of carrier-gas, but any correlation between the air/fuel ratio and carrier-gas flow-rate was not found at the low flow-rate condition. Also, the combustion-field grew and reaction-temperature rose due to the strengthening of combustion reaction with the increasing flow-rate of carrier-gas and power consumption of ultrasonic oscillator.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.198-202
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• 2005

Gas generator is the equipment to produce high enthalpy gas used to generate sufficient power to operate turbine and pump system for propellant feeding in liquid rocket engine. Since the limit in operating temperature is imposed due to turbine blade, the gas generator has to be operated at the temperature far below stoichiometric maintaining fuel rich combustion. In this research, fundamental study was performed to understand the non-equilibrium combustion process with in-house code and CFD-ACE as well.

• Journal of Biosystems Engineering
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• v.9 no.2
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• pp.58-64
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• 1984

디이젤엔진의 대체연료(代替燃料)로서 대두유(大豆油)는 대두유(大豆油)의 높은 점성(粘性)에 기인(起因)하는 문제점이 지적되고 있다. 이외 해결방법으로 대두유(大豆油)와 디이젤유(油)의 혼합(混合), 대두유(大豆油)의 에스테르화(化) 그리고 디이젤유(油) 첨가제(添加劑)의 첨가(添加) 등이 제시되고 있다. 본(本) 연구(硏究)는, 대두유(大豆油), 그의 에틸 에스테르 그리고 이러한 대체연료(代替燃料)의 디이젤유(油)와 혼합물(混合物) 또는 그 혼합물(混合物)의 첨가제(添加劑)와의 혼합물(混合物)의 점성학적 성질(性質)과 그 크기를 실험적 방법(方法)으로 구하였다. 그 결과 상기의 액체는 모두 뉴톤니안 액체이고, 첨가제(添加劑)는 상기 혼합물(混合物)의 점성(粘性)을 낮추는데 별로 효과가 없는 것으로 판단되었다.

• Fire Science and Engineering
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• v.12 no.3
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• pp.31-37
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• 1998

The heat release rate of liquid fuels is estimated by oxygen consumption technique. This method is based on the generalization that the heat release rate of combustion per unit of oxygen consumed are approximately the same for most fuels commonly encountered in fires. The oxygen concentration is measured by analyzer of paramagnetic type. The concentrations of CO2 and CO gas are measured by analyzed of Infra-Rad type. Time delays of analyzers are ignored. Results acqired from measuring techniques of exhaust gas concentrations are compared with each other.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.3-3
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• 1999

액체로켓에 대한 연구에서 가장 중요한 분야 중의 하나는 인젝터에 관한 것이다. 인젝터는 적정량의 산화제와 연료를 미립화 및 혼합시켜 연소실로 공급하는 것으로서, 액체로켓의 안정적 연소와 성능에 많은 영향을 미치는 요소이다. 기존의 F-O-F형 injector의 경우 산화제 오리피스가 연료쪽에 비해 면적이 크기 때문에 미립화 및 혼합이 좋지 못하다. 본 연구에 사용된 injector는 F-O-F형 injector의 산화제 오리피스 면적과 동일하게 두 개의 오리피스로 만들어 줌으로써 연료 오리피스와의 면적비를 적정수준으로 유지할 수 있다. 이는 동일한 조건하에서 Doublet injector나 Triplet injector의 경우 커지는 산화제의 오리피스를 제한시켜 주는 장점이 된다. 결과적으로 이러한 장점은 기존의 Doublet injector나 Triplet injector보다 높은 연소효율을 보이게 된다.