• Journal of ILASS-Korea
• /
• v.4 no.3
• /
• pp.24-31
• /
• 1999

The engine performance and combustion characteristics of methanol blended fuel of spark ignition engine were discussed on the basics of experimental investigation. The effects of methanol blending fuel on combustion in cylinder were investigated under various conditions of engine cycle and blending fuel on combustion in cylinder were investigated tinder various conditions of engine cycle and blending ratios. The results showed thai the engine performance was influenced by the methanol blending ratio and the variations of operating conditions test engine. The increase of fuel temperature brought on the improvement of combustion characteristics such as cylinder pressure. the rate of pressure rise and heat release in an engine. The burning rate of fuel-air mixture, the exhaust emissions and the other characteristics of performance were discussed also.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.125-129
• /
• 2009

The basic design of liquid rocket engine combustion chamber for a large space launch vehicle was described. It has vacuum thrust of 74.8 ton, vacuum specific impulse of 306.9 sec, chamber pressure of 60 bar, mass flow rate of 243.6 kg/s and combustion characteristic velocity of 1730 m/sec. The details of combustion performance and geometrical parameter were also given. The 75 ton combustion chamber consists of the combustor head with injector and the chamber/nozzle with regenerative cooling channels.

• 한국신재생에너지학회:학술대회논문집
• /
• 2006.06a
• /
• pp.527-530
• /
• 2006

Because price of fossil fuel rises, necessity about alternative energy was risen. Studied co-combustion of RPF to coal fluid bed boiler by necessity of these althernative energy. Purpose of this study to coal fluid bed bioler RPF when did co-combustion, change operating condition and characteristic of air pollutant examine according to change of fuel characteristic, operating condition examined about combustion chamber temperature, oxygen content etc. and air pollutant examined about material that is included to allowable exhaust standard and dioxin. Co-combustion condition was 5%. It was no peculiar under test result operating condition. Concentration of Co and HCl rose according as do RPF co-combustion and the other pollutants had hardly changed. Dioxin is low concentration level more than $0.1ng-TEQ/Sm^3$. There was no pollutant that exceed akllowable exhaust standard for boiler but $SO_x,\;NO_x$ were exceeded about allowable exhaust standard for incinerating facility.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.6
• /
• pp.28-36
• /
• 2018

A study was conducted to apply open-loop control to the combustion instability in a dump combustor using gaseous hydrocarbon fuels. Control power and frequency were varied by employing a loudspeaker under combustion conditions with similar characteristic chemistry times of the fuels. In the case of open-loop control where the frequency was identical to the combustion instability frequency, the open-loop control power affected the control performance. Results obtained from conducted open-loop control tests, where the frequency was different from the combustion instability frequency, show that setting the open-loop control frequency similar to the combustion instability frequency is effective.

• Journal of Acupuncture Research
• /
• v.20 no.6
• /
• pp.63-79
• /
• 2003

Objective: It makes a through study on the popularization and usefulness paln of Moxa Combustion, therefore popularizing practical use of that. Methods: It was based on the established treatises and books, in order to studying about the literature of Moxa Combustion Results & Conclusions: It makes a through study on the whole of Moxa Combustion, the results as follows. 1. We explained(illustrated) the origin, history, classification and mechanism(effect) of Moxa Combustion 2. The study of standardization plan of Moxa Combustion for popularization - The thermal stimulation of Moxa Combustion was decided the characteristic pattern of combustion temperature by moxa burning and that makes a measure to grasp the effective action of Moxa Combustion upon human body. Thereupon it is necessary to continue further studies by analysing the characteristic pattern of combustion temperature by moxa burning and there clinical effects in practice. 3. The usefulness of Moxa Combustion - The therapeutic effect of Moxa Combustion are hematopoiesis(increase the blood), analgesic function, increase the immunity, antioxidant activity, diuretic action, control of hormone(endocrine gland), supression of carcinogenesis, increase the self involution(natural healing), decrease of GOT/GPT, Glucose, Cholesterol level.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.21 no.1
• /
• pp.36-43
• /
• 2017

In this study, a pintle injector rocket engine which uses kerosene and liquid oxygen as propellants was manufactured by collecting basic design data and establishing a design procedure. Combustion performance of the liquid rocket engine was investigated by characteristic velocity efficiency with characteristic length of the combustion chamber and total momentum ratio. As a result of hot fire tests, it showed that the engine had shorter characteristic length comparing to those of other type injectors, which was known as recommended value with the propellant combination. Also, the characteristic velocity efficiency was greatly affected by total momentum ratio and almost constant within 1.0~1.5.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.31 no.6 s.261
• /
• pp.547-557
• /
• 2007

This study was conducted to investigate the flow and combustion characteristic of the experimental burner which was manufactured for the reflection of the oven and broil burner features. As slot shape, spacing between slots, and slot arrangement of the exit area which emits the mixing gas are different in case of oven burners and broil turners, the purpose of this study is to know the affection of the flame interaction and combustion characteristic according to the change of shape factors such as slot shape, slot arrangement, and slot-to-slot spacing. With no relation of the slot shape, as the spacing between slots became narrow, the occurrence of a lift-flame was delayed. So the combustion was possible in the leaner region, but the appearance of yellow-tip became a little fast. Slit slot port had the broadest operating range among the other slot shapes. Specially, from the side of lift-flame, as the jet that spreads downstream in the longitudinal slot was nearly circular just a few slot lengths away from the orifice, slot-to-slot spacing of the Slit port was closer than the other ports. These results could be expected through the computer numerical method and had a good agreement. As the spacing between slots increased, in case of Slit and Mix port, NOx emission rate was constant or decreased, but the NOx emission of Hole port was increased. CO emission rate of Slit and Hole port was increased as the slot-to-slot spacing was broadened.

• 한국연소학회:학술대회논문집
• /
• 2004.11a
• /
• pp.213-216
• /
• 2004

The results of combustion performance test of fuel-rich gas generator(GG) using LOx and kerosene as propellant at design and off-design point are described. The parameters used in this analysis are the average exit temperature($T_{GG}$) and the characteristic velocity($C^{\ast}$). The average gas temperature at the exit of gas generator is found to be a function of propellant O/F ratio. For the gas generator having residence time of 4msec or more, the effect of flame residence time and combustion chamber pressure on the exit temperature is not significant. The exit characteristic velocity is found to be linearly proportional to the gas temperature at the exit of gas generator.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.28 no.10
• /
• pp.1264-1270
• /
• 2004

In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and the effect of geometry was evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.19 no.1
• /
• pp.7-14
• /
• 2011

In this study, the measurement uncertainty of combustion experimental system and experimental parameters for hybrid rocket were evaluated by B type evaluation method. The measurement uncertainty of all experimental parameters was lower than 3%. The highest value of expanded uncertainty was characteristic velocity efficiency with 2.83% and the expanded uncertainty of regression rate which is the design and performance parameter was indicated to 0.03%. These results shown that the reliability of hybrid combustion system was located within allowed limits.