• Title/Summary/Keyword: 연소실 압력

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Characteristics of the inlet with pressure perturbation in the ramjet engine (램젯 엔진의 압력파 섭동에 따른 흡입구 거동 특성 해석)

  • 신동신;강호철
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2003.05a
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    • pp.94-97
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    • 2003
  • The effect of pressure perturbation in the ramjet engine on the characteristics of the inlet is studied via numerical simulation. The frequency and amplitude of the pressure perturbation are assumed to be 500Hz and 20% of the exit back pressure, respectively. The simulation shows the characteristics of the normal shock in the inlet according to the pressure perturbations. The relation between the captured mass flow rate and downstream pressure perturbation is studied. The mass flow rate decreases when the downstream pressure perturbation starts.

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Study for combustion characteristic according to the O/F ratio of low thrust rocket engine using green propellant (친환경 추진제를 사용하는 저추력 엑체로켓엔진의 혼합비에 따른 연소 특성)

  • Jeon, Jun-Su;Kim, Young-Mun;Hwang, O-Sik;Ko, Young-Sung;Kim, Yoo;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.134-137
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    • 2009
  • Combustion tests of a low thrust rocket engine was performed to get combustion characteristics, which used a high concentrated hydrogen peroxide and kerosene as the oxidizer and fuel. The engine consisted of multi injector(six coaxial swirl injectors), chamber, nozzle and catalyst ignition system. The test was carried out by changing O/F ratio from 3.8 to 11.0. The experimental results showed that combustion efficiency was highest at O/F ratio from 5 to 6 and pressure fluctuations of all the range were lower than 5%.

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Domestic and Foreign Research Trends in Rocket Combustor Instability (국내외 로켓연소기의 연소불안정 연구동향 분석)

  • Bae, Jinhyun;Jeong, Seokgyu;Yoon, Youngbin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.47-53
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    • 2017
  • One of the most common causes of failure of space launch vehicles is combustion instability. Combustion instability is a phenomenon that the pressure perturbation inside the combustion chamber is greatly amplified due to the interaction of the pressure perturbation inside the combustion chamber and the heat release perturbation. When this phenomenon becomes worse, an engine failure or launch vehicle crash occurs. In order to predict and avoid such combustion instability, understanding of the phenomenon is indispensable, and numerical, theoretical, and experimental approaches to combustion instability have been carried out worldwidely.

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Unsteady Internal Ballistic Analysis of Solid Rocket Motors with Erosive Burning (침식연소를 고려한 고체로켓의 비정상 내타도 해석 기법)

  • Cho, Min-Gyung;Heo, Jun-Young;Sung, Hong-Gye
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.221-226
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    • 2008
  • A typical unsteady internal ballistic analysis model was proposed to take account the erosive burning with the variance of local velocity and pressure along grain surface to the axis of a solid rocket combustor. The model introduced in this study showed good agreements with the results of previous research. It was investigated that the combustion pressure, grain length, initial temperature, and vaporization temperature of propellant affect on the erosive burning.

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Unsteady Internal Ballistic Analysis for Solid Rocket Motors with Erosive Burning (침식연소를 고려한 고체로켓의 비정상 내탄도 해석 기법)

  • Cho, Min-Gyung;Heo, Jun-Young;Sung, Hong-Gye
    • Journal of the Korean Society of Propulsion Engineers
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    • v.13 no.2
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    • pp.17-25
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    • 2009
  • A typical unsteady internal ballistic analysis model was proposed to take account of the erosive burning with the variance of local velocity and pressure along the grain surface of a solid rocket combustor. To validate the model of concern in the study, both cases of non-erosive and erosive burning were compared with the previous researches with marginal accuracy. It was quantitatively investigated that the combustion pressure, grain length, initial temperature, and vaporization temperature of propellant affect the erosive burning characteristics.

Study on Pressure Fluctuations Observed in Combustion of Oxygen-Rich Preburners (산화제 과잉 예연소기 연소에서 관찰되는 압력섭동에 대한 연구)

  • Seo, Seonghyeon;Kang, Sang Hun;Lee, Soo-Yong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.2
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    • pp.122-127
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    • 2013
  • The paper includes the analytic results of pressure fluctuation data from the combustion of an oxidizer-rich preburner applicable to high-performance, closed-cycle liquid rocket engine systems. The combustion experiments went through two different steps of a chamber pressure during single run. Self-excited pressure fluctuations with a frequency of 78 Hz were observed only at the relatively low chamber pressure condition. These pressure fluctuations are regarded as a bulk mode. The intensity of pressure fluctuations by a root-mean-square value is 13.3% normalized by the chamber static pressure and no pressure excitation was observed at the design pressure condition. The bulk mode has an identical phase across the inside of the chamber and reveals the similar characteristics to the Helmholtz resonator.

Combustion Dynamics of a Gas Generator Assembled with a Turbine Manifold (터빈 결합 환경의 가스발생기 동적 연소 특성)

  • Seo, Seong-Hyeon;Lim, Byung-Jik;Ahn, Kyu-Bok;Lee, Kwang-Jin;Kim, Jong-Gyu;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.121-124
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    • 2008
  • This paper presents experimental results of dynamic characteristics of fuel-rich gas generators. Pressure fluctuation measurements in the chamber and manifolds have been analyzed. Gas-generator-alone tests revealed stable combustion regardless of a chamber pressure but low-frequency combustion instabilities occurred for cases of turbine-manifold tests at chamber pressure conditions below 50 bar. The instabilities are considered as an axial resonant mode and acoustic intensity increases along with a chamber pressure.

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Analysis of Pressure Fluctuations in 1/2.5-scale Thrust Chamber for 75 tonf-class Engine (75톤급 엔진 1/2.5-scale 연소기 압력 섭동 분석)

  • Ahn, Kyu-Bok;Kang, Dong-Hyuk;Kim, Mun-Ki;Lim, Byoung-Jik;Kim, Jong-Gyu;Lee, Kwang-Jin;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.5-9
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    • 2010
  • In the paper, the dynamic characteristics obtained from hot-firing tests of 1/2.5-scale thrust chamber for 75 tonf-class liquid rocket engine were described. To investigate the dynamic characteristics by engine start transient period and chamber pressure variation, hot-firing tests were performed in the chamber pressures of 30 bar and 60 bar. According to these variations, combustion stability in the combustion chamber was examined.

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Development and use of PC based combustion analyzer (PC를 사용하는 연소해석장치의 개발에 관한 연구)

  • Lim, B. J.
    • Journal of the korean Society of Automotive Engineers
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    • v.15 no.3
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    • pp.75-80
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    • 1993
  • 널리 사용되는 IBM-PC를 기본으로 하여 고속도 데이터 처리가 가능한 연소 해석 장치를 개발 였다. 본 시스템은 상용의 A/D변환기와 C언어를 사용한 소프트웨어 및 PC 인터페이스 보드로 구성되어 있다. 본 연소 해석 장치의 특징은 모든 기능이 모니터 상에서 마우스로 지원되며, P 상에서 타 프로그램을 위한 데이터 변환이 용이하고 메모리의 확장이 기존의 상용 연소 해석 치에 비해 간편하다. 연구용 단기통 기관실험을 통하여 본 시스템을 검증하였다. 연소실 내의 력은 크랭크 각도로 0.1.deg.에서 1.deg.의 해상도로 분석할 수 있다.

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Linear Acoustic Waves in Baffled Rocket Combustion Chambers (배플이 달린 로켁 연소실내의 음향 효과)

  • Yoon, Myong-Won
    • The Journal of the Acoustical Society of Korea
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    • v.15 no.4
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    • pp.105-112
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    • 1996
  • A linear acoustic analysis for baffled rocket combustion chambers has been developed. This study provides the comprehensive theoretical background for the baffle as one of the stabilizing devices in a liquid rocket propulsion system. Several specific effects of baffles are presented as mechanisms by which baffles eliminate instability. Included are longitudinalization of transverse waves inside baffle compartments, severe restriction of velocity fluctuations near the injector face, and decreased normal mode frequency of the chamber.

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