• Title/Summary/Keyword: combustion characteristic

Search Result 461, Processing Time 0.04 seconds

Ignition and Extinction Characteristics of a Low Thrust Combustion Chamber using Green Propellant according to Sequence of the Combustion Test (친환경 추진제를 사용하는 저추력 액체로켓엔진의 연소시험 시퀀스에 따른 점화 및 소염 특성)

  • Kim, Young-Mun;Jeon, Jun-Su;Choi, Yu-Ri;Ko, Young-Sung;Kim, Yoo;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2009.11a
    • /
    • pp.130-133
    • /
    • 2009
  • The sequence of the propellant supply is very important for the reliable and safe operation of a LRE combustion test. So combustion performance tests were performed to find an optimum test sequence by changing supply time of propellants and purge gas in the moment of ignition and extinction. The liquid rocket engine consisted of a catalytic ignitor and six swirl-coaxial injectors which used hydrogen peroxide and kerosene. Conclusively, an optimum sequence was found for stable combustion in the moment of ignition and extinction.

  • PDF

A Study on Combustion Characteristics of a Multi Injector Rocket Engine using $H_2O_2$/Kerosene as propellants (과산화수소/케로신 다중 인젝터의 혼합비에 따른 연소 특성 연구)

  • Yu, I-Sang;Jeon, Jun-Su;kim, Jai-Ho;Kim, Wan-Chan;Ko, Yung-Sung;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2012.05a
    • /
    • pp.129-132
    • /
    • 2012
  • In this study, combustion performance tests of a multi coaxial-swirl injector engine using hydrogen peroxide and kerosene as propellants were performed to evaluate combustion characteristic according to mixture ratio between 6.0 and 9.0 by criterion of designed(7.6). Combustion characteristics were evaluated by calculated characteristic exhaust velocity($c^*$) and pressure fluctuation. Test results showed that the combustion efficiency was over 90% and the pressure fluctuation was within 1%.

  • PDF

Comparison of Combustion Efficiency of Multi Hole Pintle Injector and Continuous Pintle Injector (다중 홀 핀틀 인젝터와 연속형 핀틀 인젝터의 연소성능 비교)

  • Nam, JeongSoo;Lee, KeonWoong;Koo, JaYe
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.50 no.3
    • /
    • pp.165-172
    • /
    • 2022
  • Pintle injector is the most suitable injector for thrust control because it can control the area of propellant injection. Accordingly, the combustion test of multiple hole pintle injector and continuous type pintle injector was carried out in this paper using liquid oxygen and gas methane. The combustion performance of the two pintles was verified with the characteristic speed efficiency, and the experimental results were compared according to the O/F and combustion chamber pressure and under similar conditions. The efficiency of the multi hole pintle was generally somewhat higher than continuous pintle when pintle opening distance(the area of dispensing oxidizer) was in a 100% thrust condition.

Fuel Injection System on Combustion and Exhaust Emissions Characteristics in Compression Ignition Engines (압축착화 엔진에서 디젤-가솔린 Dual Fuel이 연소 및 배기 특성에 미치는 영향)

  • Kwon, Seok-Joo;Cha, June-Pyo;Sung, Ki-An;Park, Sung-Wook
    • Journal of the Korean Society of Combustion
    • /
    • v.16 no.1
    • /
    • pp.52-57
    • /
    • 2011
  • The present study describes the characteristics of combustion and exhaust emissions in compression ignition engines using diesel-gasoline dual fuel. For investigating combustion characteristics, diesel fuel was injected directly in a single-cylinder compression ignition engine with a common-rail injection system and gasoline fuel was injected into a premixed chamber installed in an intake port. In order to investigate exhaust emission characteristics, exhaust gas was measured by emission analyzer and smoke meter. The experimental results showed that cases of diesel-gasoline dual fuel combustion exhibited extended ignition delay and reduced peak combustion pressure compared to those of directly injected diesel fuel cases. Furthermore, premixed gasoline-air mixture reduced NOx emissions due to low peak of rate of heat release(ROHR).

Research and Development Status of Combustion Chamber of Liquid Rocket Engine for KSLV-II (한국형발사체 액체로켓엔진 연소기 연구 개발 현황)

  • Han, Yeoung-Min;Lee, Kwang-Jin;Kim, Jong-Gyu
    • 한국연소학회:학술대회논문집
    • /
    • 2012.11a
    • /
    • pp.291-294
    • /
    • 2012
  • The research and development status of combustion chamber of liquid rocjet engine for Korea Space Launch Vehicle(KSLV-II) are briefly described. The cold and hot firing tests of uni-element injector, the performance/heat flux measurement/hot firing tests of subscale combustion chamber and the performance/stability rating/regenerative cooling/hot fire tests of 30ton-class combustion chamber were successfully performed. Based on these results, the research and development of combustion chamber for 75ton-class liquid rocket engine are underway.

  • PDF

Solid Fuel in the Highly Preheated Air Combustion (고체 연료의 고온 공기 연소 특성에 관한 연구)

  • Jin, Hong-Jong;Choi, Sang-Min
    • 한국연소학회:학술대회논문집
    • /
    • 2002.11a
    • /
    • pp.185-192
    • /
    • 2002
  • A laboratory scale thermogravimetric analyser was developed to investigate the combustion characteristics of selected solid fuel(wood) in the highly preheated air. The aims are to introduce in the means of experimental determination of the solid fuel particle characteristics through the combustion process in the environment of highly preheated air. A nearly single particle combustion condition was reproduced in a thermogravimetric analyser and regenerating combustor. For a fuel particle whose characteristic length was a few centimeter, the sub-processes of fuel drying, pyrolysis as well as the combustion of residual carbon were identified. Fluidized environment of carrier gas was selected as the major parameter which affect the combustion process.

  • PDF

The investigation of Diesel Spray Combustion in DME HCCI (DME 예혼합기를 분위기로 하는 디젤 분무의 연소에 관한 연구)

  • Lim, Ock-Taeck;Iida, Norimasa
    • Proceedings of the KSME Conference
    • /
    • 2007.05b
    • /
    • pp.3329-3334
    • /
    • 2007
  • The purpose of the research is to investigate of diesel spray combustion for simultaneously reduce way NOx and PM. The pressure diesel injection were done into intermediates that are generated by very lean DME HCCI combustion using a RCM. The concentration of intermediate could not be directly measured; we estimated it by CHEMKIN calculation. DME HCCI characteristic is surveyed. Validations of the CHEMKIN calculation were confirmed pressure rise of an experiment and pressure rise of a calculation. Using a framing streak camera captured two dimensional spontaneous luminescence images from chemical species at low temperature reaction(LTR) and high temperature reaction (HTR). Also, the combustion events were observed by high-speed direct photography, the ignition and combustion were analyzed by the combustion chamber pressure profiles.

  • PDF

A Study on the Transient Combustion Characteristic in PE-GOX Hybrid Rocket (PE-GOX 하이브리드 로켓에서의 과도 연소 특성 연구)

  • Cho, Sung-Bong;Lee, Jung-Pyo;Song, Na-Young;Kim, Soo-Jong;Kim, Jin-Kon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2006.11a
    • /
    • pp.228-231
    • /
    • 2006
  • In general, burning time is not considered with a factor of an empirical relation on the combustion characteristic in hybrid propulsion system. So, The effect of burning time on hybrid combustion characteristics and propulsion characteristics was studied. As results, regression rate is decrease with burning time, but fuel mass flux is maintained nearly constant with burning time at given oxidizer mass flux.

  • PDF

Study on Combustion Characteristic of GOx/PE Hybrid Rocket According to Port Diameter (GOx/PE 하이브리드 로켓의 포트 직경에 따른 연소특성 연구)

  • Choi, Jae-Sung;Huh, Hwan-Il
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2010.11a
    • /
    • pp.692-693
    • /
    • 2010
  • In this study, we analyze the combustion characteristic of GOx/PE hybrid rocket, by changing port diameter of the propellant. To study combustion characteristics of hybrid rocket, GOx is used for oxidizer and PolyEthylene is used for solid propellant. Regression rate and O/F ratio of the rocket is measured and presented.

  • PDF

Combustion Characteristics of the Paraffin-Based Hybrid Rocket Fuel (파라핀계 하이브리드 로켓 연료의 연소 특성)

  • Kim, Soo-Jong;Cho, Jung-Tae;Kim, Gi-Hun;Kim, Hak-Chul;Woo, Kyong-Jin;Lee, Jung-Pyo;Moon, Hee-Jang;Sung, Hong-Gye;Kim, Jin-Kon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2009.05a
    • /
    • pp.225-228
    • /
    • 2009
  • Combustion characteristics of the paraffin-based hybrid rocket fuel were compared with HDPE fuel. Regression rate of the pure paraffin wax was increased 12.1 times, but characteristic velocity was lower than HDPE. In case of paraffin fuel with 10%wt LDPE, regression rate was lower than pure paraffin wax, but regression rate compare with HDPE was increased 3.5 times and characteristic velocity was increased. According to these results, it was confirmed that blending of polymeric fuel improves combustion efficiency.

  • PDF