• Journal of the korean Society of Automotive Engineers
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• 제15권6호
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• pp.23-32
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• 1993

스파크 점화기관의 연소과정 해석은 엔진성능분석 및 예측의 핵심이며 배기가스 배출과도 밀접히 연관된다. 스파크 점화기관의 연소해석을 수행하기 위해 연소실 압력 측정, 유사 차원 해석, 3차원 유동 및 연소 해석을 수행하여 결과를 비교하였다. 이들 방법은 서로 일치하는 경향을 보이며 상호간의 장단점을 보완하는 역할을 할 수 있음을 알 수 있다. 본 연구는 이러한 시도의 첫번째 결과로서 계속적인 비교 연구가 수행될 예정이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 한국추진공학회 2002년도 제18회 학술발표대회 논문초록집
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• pp.72-72
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• 2002

건국대학교 연소추진 실험실에서 수행할 하이브리드 로켓 모터 연소특성 연구를 위한 실험장치를 설계하고 구성하였다. 실험장치를 제작하기 전에 기본적인 설계요구사항을 바탕으로 모터의 제작을 위한 수치코드를 작성하였다. 연소실 압력과 그레인의 형상, 산화제와 고체연료의 종류를 바탕으로 작성한 수치코드를 사용하여 로켓 모터를 설계하였다. 모터 설계코드를 통하여 세부적인 로켓모터와 노즐의 크기, 특성속도. 연소시간과 공급산화제의 유량 등을 계산하였고, 설계 전에 문헌연구와 이론을 바탕으로 일반적으로 실험실에서 사용되는 하이브리드 로켓 모터에 근접하게 설계를 진행하여 시행착오를 최소화하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 한국추진공학회 2000년도 제15회 학술강연회논문초록집
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• pp.32-32
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• 2000

3단형 과학로켓의 고체모타의 내부 유동을 추진제의 연소에 따라 내부형상이 변화하는 과정에 대해 수치해석 하였다. 추진제는 표면에서 균일하게 연소된다고 가정하였으며 연소거리가 0.1mm, 30mm, 60mm, 90mm인 경우의 고체모타 내부 물리량 변화를 관찰하였다. 연소가 진행되며 잠입형 노즐의 위 부분에 큰 재순환 영역이 생기는 것이 관찰되었으며 노즐에 작용하는 압력 힘을 구하여 본 결과 노즐부의 모멘트 힘은 크지 않은 것으로 판명되었다.(중략)

• Journal of the Korean Society of Propulsion Engineers
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• 제18권2호
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• pp.16-26
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• 2014

T-Burner tests of an Al/HTPB propellant in conjunction with a Pulsed DB/AB Method were conducted to find an acoustic amplification factor. Aluminum-free and aluminum-heavy propellants were examined. Instant surface ignition was successfully made by the use of a supplementary propellant of fractionally higher reaction rate. With the presence of higher aluminum concentration in the propellants, the pressure perturbations were promptly damped down and the pressure fluctuations were no longer dispersive. Addition of aluminum particles into the propellant was advantageous for stabilizing pressure-coupled unstable waves.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.225-228
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• 2009

Hot-firing tests were performed on the gas generator which is a technology development/demonstration model for a 75 ton-class liquid rocket engine. A heat-sink type combustion chamber was used for initial performance examination of the injector and mixing head. This paper explains not only preparation works for hot-firing tests but also the acquired results such as pressure, temperature distribution, and pressure fluctuation.

• Journal of the Korean Society of Propulsion Engineers
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• 제12권4호
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• pp.1-6
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• 2008

The burning characteristics of HTPB/AP solid propellants were measured by closed bomb of internal volume of 200 cc and 700 cc up to 30,000 psia. The burning rates of closed bomb method showed good agreement with those of strand burner method between 1,000 psia and 5,000 psia, and the sharp increment of pressure exponent(n) around 6,000 psia as a result of testing in accordance with loading densities. The burning rate measured in 200 cc and 700 cc of internal volume of closed bomb agreed well without the relation of internal volume size.

• Journal of the Korea Academia-Industrial cooperation Society
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• 제12권5호
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• pp.2054-2060
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• 2011

The purpose of this paper is to investigate spray characteristics of GDI injector that is economic and environment-friendly. Injector characteristics such as penetration length, spray angle and mixture formation were measured using experimental visualization technique. Especially, it has been analyzed that the influences of ambient pressure and injection pressure on penetration length and spray angle. To visualize the spray, a constant volume combustion chamber and fuel supply system have been manufactured. A high-speed camera and LED light source have been applied to obtain spray images. The experimental and visualization result shows that the penetration length is increased as decreasing ambient pressure and/or increasing injection pressure. Also, ambient pressure and injection pressure have minor effect on the spray angle variation.

• Journal of the korean Society of Automotive Engineers
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• 제10권2호
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• pp.2-8
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• 1988

중대형 상용차에 널리 사용되어온 디젤엔진은 오일 쇼크 이후로 소형 상용차에까지 널리 탑재되고 있는 세계적인 추세이다. 디젤엔진은 높은 연소 압력 및 압력 상승율(Rate of Pressure Rice)로 운전되기 때문에 연소소음(Combustion Noise) 및 기계소음(Mechanical Noise)이 매우 크다. 차량 개발 개념에 있어 소음제어는 법적 규제와 소비자의 요구수준을 만족시키는 측면에서 고려되어야 한다. 차량 전체 소음에서 엔진 소음의 기여도는 약 40-50%정도이며 당연히 엔진소음 저감 대책의 필요성은 높다. 본고에서는 2.4리터 간접 분사식(IDI)디젤 엔진의 소음 저감을 위한 소음 저감 대책을 기술한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• 제38권5호
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• pp.456-466
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• 2010

Typical combustion instability such as DC-Shift found in the hybrid rocket motor is characterized by non-linearity. DC-Shift can occur in two different realizations. One is so-called a positive shift of measured DC voltage where the pressure increase suddenly. The other is a negative shift where the pressure drops abruptly. In the present work, specifically the negative DC-Shift was investigated to analyze the effect of oxidizer flow condition and the resonance between fundamental frequency and other ones, such as Helmholtz frequency, and acoustic frequency. Results show a peak frequency of several hundreds HZ shifts as combustion proceeds. A negative DC-shift was found as the result of phase cancellation between two dominant frequency, combustion frequency and flow related frequency. Still is it required to study further to identify the change of dominance of frequency during the combustion.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• 제33권6호
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• pp.64-70
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• 2005

The overall results of hot firing tests of fuel-rich gas generator with impinging injector at design and off-design points are described. The gas generator consists of an injector head with impinging injector, a water cooled combustor wall, a turbulence ring to enhance mixing, an instrument ring measuring temperature and pressure and a nozzle. The combustion tests were successfully performed without damage of gas generator. Test results show that the outlet temperature is not dependent on residence time of hot gas within 4～6msec but dependent on chamber pressure. The relation between outlet temperature and combustion efficiency resulting from measured pressure, mass flow rate and area of nozzle throat is shown. The overall O/F ratio is the critical parameter to determine the outlet temperature and the linear correlation between two parameters is established.