• Journal of the Korean Institute of Gas
• /
• v.28 no.2
• /
• pp.32-37
• /
• 2024

Recently, transportations using hydrogen energy is being researched for the alternative energy of fossil fuels. To use them, processes of producing, storing and transferring are required. When carrying them in liquid under 90 MPa pressure, it costs less than in a gas status. Thus, a hydrogen pump is necessary and in this research we predicted the flow in the chamber using finite element methods (FEM) program ANSYS. As a result, when the valve was opened by 3 mm, between the 1^st chamber and the 2^nd chamber, the maximum velocity was decreased to 8.111 m/s by 10.6% (without valve, 9.075 m/s). In addition, pressure was also increased to 0.63 MPa by 1.6% (without valve, 0.62 MPa). When using these results, more efficient processes would be possible in designing them in detail.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.42 no.5
• /
• pp.437-443
• /
• 2014

Engine is one of the most important parts in a rocket for completing its mission successfully. In this paper, we provide a methodology for estimating reliability and development cost of a liquid rocket engine newly developed. To estimate reliability, a baseline engine is selected considering factors whose effects on reliability are unquantifiable. Then reliability of a baseline engine is adjusted to reflect the effect of factors that can be modeled quantitatively. Using the previous Transcost engine cost expressed in terms of mass and the number of hot firing tests, the engine development cost is reexpressed in reliability and thrust requirements. Finally, a numerical example is given to illustrate the application of the methodology to a turbopump rocket engine using staged combustion cycle with LOX/LH2 propellant.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.3
• /
• pp.66-73
• /
• 2004

As a rocket propellent of hydrocarbon fuels, the characteristics of liquefied natural gas was evaluated with the viewpoint of the constituents and content, the cooling performance as a coolant, and characteristic velocity and specific impulse as parameters of the engine performance. Content of methane was a principal factor to determine the characteristics as a rocket propellant and more than 90% of it was needed as a fuel and coolant in the regenerative cooled liquid rocket engine. Some constituents of the liquefied natural gas can be frozen by the pre-cooling of the pipe lines, therefore they can be a factor disturbing the normal working of engine. In case the content of methane is around 90% in the liquefied natural gas, a normalized stoichiometric O/F mixture ratio of 0.75 is suggested for a nominal operation condition to get the maximum specific impulse and characteristic velocity.

• Journal of Energy Engineering
• /
• v.5 no.2
• /
• pp.176-182
• /
• 1996

The effects of some additives (black liquor, NaOH, water and wood) on the conversion of coal and product were investigated in the lab-scale, high pressure reacting system around 375$^{\circ}C$. The addition of black liquor enhances the coal conversion yield about 38.6%, which is mainly due to NaOH in black liquor. Also, sulfur of the black liquor in coal liquefaction process evolved hydrogen sulfide, which causes the odor problem. Addition of water in coal liquefaction increased CO$_2$content in the gas phase, and low boiling range components in liquid products. Coprocessing of wood and coal at 400$^{\circ}C$ increased yield of liquid product about 8%, but higher temperature above 400$^{\circ}C$ reduced liquid product due to increase of gas products.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.9 no.3
• /
• pp.133-144
• /
• 2005

Enhancements to propellants provide an opportunity to either increase performance of an existing launch vehicle. One of the promising technologies is the use of densified cryogenic propellants such as liquid hydrogen and liquid oxygen. The main advantage of densified cryogenic propellants is the increase in propellant mass fraction. Increased propellant mass fraction means increased payload mass to orbit. This paper reviews the basic principles and current technology trends for cryogenic propellant densification technologies. Several promising densification methods are presented focused on liquid oxygen densification. Engine and vehicle performance analyses are also presented to quantify the potential performance benefits of densified propellants in an overall system. And suggestions of application scheme for satellite launch vehicle is made.

• Analytical Science and Technology
• /
• v.5 no.4
• /
• pp.381-387
• /
• 1992

Optimum counting condition of a low level liquid scintillation counter for radiocarbon dating has been determined to minimize the contribution of tritium activity and get the highest FOM by the variation of scintillation solutions, scintillation solution to benzene ratio, and ${\beta}$-ray spectrum counting ranges. Under the condition, background count rate has been reduced to $2.26{\pm}0.03cpm$, and the maximum measurable age reached to about 40,000 years. And the practicality of counting system has been verified by the analysis of shell and peat samples.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.601-604
• /
• 2010

An experimental study was carried out to investigate the effect of film cooling in a liquid rocket engine using Hydrogen peroxide/Kerosene as propellants. The heat fluxes were calculated by the measured wall temperatures on the axial direction of thrust chamber for mass flow rate of coolant and different type of film cooling rings. The flow rate of coolant was 0~20 percent of the total propellant.

• Journal of Advanced Marine Engineering and Technology
• /
• v.31 no.4
• /
• pp.363-369
• /
• 2007

Probably the most significant heat transfer in the cryogenic liquid hydrogen storage tank from the atmosphere may occur through its support system. In this paper the efficient support system for the cryogenic storage vessel was newly developed and analysed. The support system was composed of a spherical ball as a supporter to reduce the contact area. which is located between two supporting SUS tubes inserted SUS and PTFE blocks. Numerical analyses for temperature distribution, and the thermal stress and strain of the support system were performed by the commercial codes FLUENT and ANSYS. The heat transfer rate of the supporter was evaluated by the thermal boundary potential method which can consider the variation of thermal conductivity with temperature. The results showed that the heat transfer rate through the developed supporter compared with the common SUS tube supporter was significantly reduced. The thermal stress and strain were obtained well below the limited values. It was found that the developed supporter can be one of the most efficient support systems for cryogenic liquid storage vessel.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2000.04a
• /
• pp.11-11
• /
• 2000

액체렘제트 엔진에서는 고온·고속의 공기가 공기흡입구로 유입되기 때문에 고성능 램제트 연소기의 설계를 위하여 실제 비행조건을 모사할 수 있는 고온 고속의 공기 발샐장치가 필요하다. 본 연구에서는 수소연소에 의해 Vitiated Air를 발생시키도록 설계된 Vitiated Air Heater(VAH)를 제작하였으며, VAH의 성능평가를 통하여 80∼120m/s 와 400∼800K 범위에서 손쉽게 속도와 온도의 조절이 가능하고 균일한 속도 및 온도분포로 대기공기와 같은 Vitiated Air를 얻을 수 있었다. 그리고 VAH을 연결하여 Dump형 연소기의 특성을 실험하였다. 액체 램제트 엔진에 있어서 공기흡입구가 하나인 Dump형 연소기에 주요변수로서 흡입공기의 온도와 공연비를 변화시키면서 연소기내의 화염형상을 관찰하고, 온도분포를 계측하였으며 Injection 위치에 따른 화염현상을 관찰하였다. 각 경우의 연소효율을 계산하여 실험범위에서의 최적 연소조건을 제시하였다.

• Mineral and Industry
• /
• v.15 no.2
• /
• pp.35-47
• /
• 2002

석탄자원이 사용되는 분야는 에너지원료 분야(연료)와 석탄화학원료 분야(비연료)로 대별된다. 에너지원료분야는 석탄의 대표적 이용분야로서 직접 연료로 사용되거나 발전에 의한 전기에너지로 변환 이용되는 경우이고 석탄화학원료분야는 석탄을 하나의 화학물질로 취급하여 고체. 액체, 기체 형태로거 이용되는 경우로서 연료의 경우보다 이용될 수 있는 조건과 과정이 까다로우며 그 소비량도 연료의 경우보다는 소규모이다. 석탄자원을 비 연료분야로 이용할 때 , 즉 석탄을 하나의 원료소재로서 이용할 때의 이용가능 분야에 대하여 알아보자 석탄은 유기질의 고체이므로 석유와 마찬가지로 탄화수소원으로서 여러 가지 용도로 사용될 수 있다. 현재까지 연구개발 또는 공업화된 석탄이용계통을 종합하여 나타내면 그림 1과 같다. 그림 1은 석탄이용의 관련기술을 합친 여러 가지 분류법 중에서 고체 기체, 액체로서의 이용을 중심으로 체계화한 것이다.