• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
• /
• pp.232-235
• /
• 2017

Scramjet combustor materials are exposed at ultra high temperature over 2000K and severe erosion environment. Inconel alloys are usually applied for combustor material however its mechanical properties are decreased beyond temperature of 1000K so that is impossible for long term operation and reuse. In this study, fiber reinforced ceramic material was used as scramjet combustor material and its feasibility studied. To increase combustion efficiency, regenerative combustor system developed and channel fabrication in composite material also studied.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
• /
• pp.68-77
• /
• 2017

High-frequency combustion instability results from a feedback coupling between the unsteady heat release rate and the acoustic waves formed resonantly in the combustion chamber. It can be modeled as thermoacoustic problems with various degrees of the assumptions and simplifications. This paper presents numerical analysis of self-excited combustion instabilities in a variable-length lean-premixed combustor and designs of passive control devices such as baffle and acoustic resonators in a framework of 3-D FEM Helmholtz solver. Nonlinear behaviors such as steep-fronted shock waves and a finite amplitude limit cycle are also investigated with a compressible flow simulation technique.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
• /
• pp.498-501
• /
• 2012

The Model Rocket Engine Test Facility has been improved to develop the Korea Space Launch Vehicle II(KSLV-II). The modified Model Rocket Engine Test Facility will be used to develop 7-tonf class liquid rocket engine combustor. The test result and test technique acquired from this facility will be used to develop the high performance liquid rocket engine combustor. This paper describes the modified Model Rocket Engine Test Facility for a Sub-scale model test of the 7-tonf class combustor.

• Aerospace Engineering and Technology
• /
• 제4권2호
• /
• pp.135-141
• /
• 2005

The procedure of conceptual and detailed design of sub-scale combustor using bipropellant swirl or impinging injector with external or internal mixing for a liquid rocket engine are described in this paper. The sub-scale combustor uses liquid oxygen(LOx) and kerosene as propellants and has a injector head, an ablative material combustor wall and a water cooled nozzle. The injector head has LOx manifold, fuel manifold, fire face plate, one center swirl or impinging injector and 18 main swirl or impinging injectors.

• Clean Technology
• /
• 제22권3호
• /
• pp.161-167
• /
• 2016

Catalytic combustion of benzene over various metal cation-exchanged zeolites has been investigated. Y(4.8)-type zeolite showed the highest activity among the used zeolites and Cu/Y(4.8) catalyst also showed the highest activity among metal cation/ Y(4.8) zeolites. The catalytic activity increased according to the amount of adsorbed oxygen acquired from O₂ TPD results. The catalytic activity also increased with an increase of Cu cation concentration on Cu/Y(4.8) catalysts. The conversion of benzene on the combustion reaction depended on not benzene concentration but the oxygen concentration. In addition, the introduction of water into reactants decreased the catalytic activity.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 한국추진공학회 2000년도 제14회 학술강연논문집
• /
• pp.32-32
• /
• 2000

잠입노즐은 로케트 추진기관의 길이 및 중량을 감소시켜 체계설계의 관점에서 볼 때 많은 이점을 제공한다. 본 연구에서는 3단형 과학로케트 원지점 차넣기 모타(apogee kick motor)에 적용하기위한 잠입노즐의 기초기술 개발에 주안점을 두었다. 고고도에서 저속으로 회전하며 비행하는 원지점 차넣기 모타를 제작하기위해서 체계 요구성능에 의해 예상된 실물형의 50% 크기에 해당하는 축소형 잠입노즐을 제작하였다. 잠입노즐은 잠입부의 내외부가 고온의 추진제 연소가스에 노출된 상태에서 노즐 내부 압력 외에 연소실압에 의한 외부압력이 작용하므로 이를 고려한 열 및 구조설계가 중요하다. 본 연구에서는 노즐 수렴부와 목부에 일체형 그라파이트 소재를 적용하고 확장부 내열재 및 잠입부 배면내열재에 탄소/페놀 복합재를 노즐 내열재로 사용하였다. 그리고 이들의 구조적 지지를 위해 스틸구조물을 적용하였다. 적용된 스틸구조물에는 K형 열전쌍을 이용해 내열재와 구조물 온도를 측정할 수 있는 관통구멍 및 나사부를 구조물 외변에 가공하였다. 열전쌍은 노즐 목직경의 2, 4배 되는 확장부 내열재 단면위치의 2mm와 4mm 깊이와 구조물 내면 및 외면의 4개소에 열전쌍을 부착하여 지상연소시험시 노즐 내열재와 구조물의 온도분포를 관찰한다. 그리고 노즐 조립시 확장부 내열재와 구조물에 각 각 반원형 홈을 내어 여분의 접착제가 원형 홈에 밀려들어가 경화되어 노즐 기밀유지와 체결력을 향상시킬 수 있는 원형공간 접착제 충전 공법을 적용하여 실제모타에 대한 적용가능성을 지상연소시험을 통해 확인한다.

• Journal of the Korean Society of Fisheries and Ocean Technology
• /
• 제25권2호
• /
• pp.82-86
• /
• 1989

This paper is concerned with the effects of temperature of diesel fuel on combustion characteristics and engine performance in a home-made precombustion diesel engine for small-sized fishing boat. The results may be summarized as follows: 1. The fuel injection timing was delayed with increase in temperature for diesel fuel, and remarkably delayed at low load. 2. The point of maximum pressure was delayed with increase in temperature for diesel fuel, the maximum pressure decreased with increase in temperature for diesel fuel but increased with increase in load. 3. The brake specific fuel comsumption (BSFC) decreased with increase in load, the optimum temperature of the heated fuel was about 15$0^{\circ}C$. 4. The smoke emissions increased with increase in load and temperature for diesel fuel.

• Aerospace Engineering and Technology
• /
• 제11권2호
• /
• pp.57-64
• /
• 2012

Although the APU combustors were developed successfully, it could face many unexpected hardships in an engine or a system operating under the severe environments. But, it is not easy to change the combustion field or combustor structure at the engine/system development stage. So we must suggest practical ways to optimize the value quantitatively by engine test and flow analysis, and verify those by the cyclic test. This paper describes reverse-annular type combustor troubleshooting processes for verifying and settling of the problems and issues occurred in various engine and system operation tests by experiment and analysis.

• Journal of the Korean Society of Propulsion Engineers
• /
• 제6권3호
• /
• pp.19-27
• /
• 2002

The sequence of the propellant supply for ignition of a liquid rocket engine combustor is very important in the reliable and safe operation of the engine. The ignition sequence of KSR-III main engine was briefly described and the measuring parameters and their reliability determining ignition sequence were examined in this paper. The filling time of the engine propellant manifolds and the valve open/close time were reviewed to obtain the exact and reliable time of the propellant supply to the combustor. The combustion characteristics of the engine at starting were discussed at different supply lead of propellant. Finally, the hot firing test results with cyclogram determined by measuring parameters were presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 한국추진공학회 2010년도 제34회 춘계학술대회논문집
• /
• pp.25-28
• /
• 2010

The Cold flow and ignition tests have been performed for a technology demonstration model of 75-tonf liquid rocket engine thrust chamber which was designed and manufactured on the basis of the previous development experience of a 30-tonf liquid rocket engine thrust chamber. The hydrodynamic characteristics of the facility supply pipelines and the filling time of the cooling kerosene were obtained through the cold flow tests. The ignition cyclogram was determinded using the results and the ignition test was successfully carried out. The acquired data and test technique of present ignition test will be used in hot firing tests.