• Title/Summary/Keyword: 초음속 연소기

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Shock-Wave Effects on the Mixing and the Stabilization of Supersonic H$_2$-Air Flames for SCRamjet Applications (스크램제트 모델 연소기 내에서 초음속 수소-공기화염의 혼합과 연소안정성에 대찬 충격파의 영향)

  • 허환일
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1998.10a
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    • pp.15-15
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    • 1998
  • 마하 수 6 이상인 극초음속 비행에는 스크램제트(SCRamjet : Supersonic Combustion Ramjet) 엔진이 가장 적합한 엔진으로 알려져 있고 현재 미국을 중심으로 이 엔진의 개발에 많은 노력을 기울이고 있다. 스크램제트 엔진의 성공적인 개발을 위해서는 초음속 공기 내에서 연료의 분사를 통한 가장 효율적인 연소를 유도할 수 있어야 한다. 초음속 상태의 공기와 연료의 혼합을 증대시키고 연소안정성을 향상시키는 방법으로 연소기 내에 인위적으로 경사충격파를 발생시키는 방안이 Marble 등에 의해 최초로 도입되었다. 본 연구에서는 스크램제트엔진 내의 연소기를 모델링하여 마하수 2.5의 초음속공기 유동 중앙에 수소 제트를 분사하여 초음속 수소-공기 화염을 만들고 연소기의 측면에 동일한 모양과 크기의 쐐기를 각각 부착시켜 평면 경사충격파를 발생시켰다 본 실험은 충격파가 초음속 화염에 미치는 영향을 연구한 최초의 실험연구이다.

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Numerical Study on the Process of Supersonic Flow Formation in a Direct-Connect Supersonic Combustor (Direct-Connect 초음속 연소기 내 초음속 유동 형성과정에 대한 수치해석)

  • Jeong, Seong-Min;Han, Hyunh-Seok;Sung, Bu-Kyeng;Lee, Eun-Sung;Choi, Jeong-Yoel
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.48 no.11
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    • pp.889-902
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    • 2020
  • In this study, a numerical analysis was performed to confirm the formation of supersonic flow and the stabilization time satisfying the design condition in a Direct-connect supersonic combustor. The process was examined in which the high-pressure gas of vitiation air heater propagates downstream to the supersonic combustor and forms a supersonic flow field. It was confirmed through the analysis of pressure and temperature that the supersonic flow field satisfies the design points of Mach number 2.0 and 1,000 K, and requires a minimum of 4.0 ms for stabilization. These results indicate that the time required for the supersonic flow field stabilization should be taken into account when testing for the supersonic combustion experiment.

Determination of Thrust Distribution in the Supersonic Combustor (초음속 연소기 내부의 추력 분포 계산)

  • Heo, Hwan Il
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.31 no.4
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    • pp.69-75
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    • 2003
  • The ideal thrust function is used to determine the local thrust of supersonic combustor. Method of thrust determination from measured pressures are applied to the Mach 2.5 model supersonic combustor. In this application, measured pressures from the experiments in the University of Michigan are used to determine the local thrust of supersonic combustor. Marginal results of local thrust are obtained and discussed. Combustion and wedge affect thrust distributions in the upstream region significantly. The thrust determination from pressure measurements can be a simple, feasible and applicable method, especially when thrust stand is not available.

Supersonic Combustion Experiments of Dual Combustors (이중 연소기의 초음속 연소 실험)

  • Byun, Jong-Ryul;Lee, Sang-Yeon;Moon, Kwan-Ho;Hwang, Ki-Young;Lim, Jin-Shik
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.386-387
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    • 2012
  • This experimental study is the supersonic combustion of dual combustors in dual combustion ramjet engine. Through the preliminary performance analysis of DCR, the configuration of dual combustors was determined and constructed, supersonic experiments were accomplished.

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Numerical Study of Flame Stability of Turbulent Combustion in a Dual Combustion Ramjet (이중연소 램제트 엔진의 난류 연소 현상과 화염 안정성)

  • Choi, Jeong-Yeol;Han, Sang-Hoon;Kim, Kyu-Hong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.371-374
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    • 2011
  • High-resolution numerical study is carried out to investigate the flame stability of the turbulent supersonic combustion in a Dual-Combustion Ramjet (DCR). The auto-ignition in a shear layer between hydrogen/carbon-monoxide syngas and air was studied at elevated enthalpy condition. Comparison of a constant area combustor and a combustor with a small divergence angle shows that the supersonic combustion has a characteristics of the lifted flame and its stability is influenced significantly by the compressibility.

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Performance Analysis Method for Dual Combustion Ramjet Engines (이중연소 램제트엔진의 성능해석 기법)

  • Seo, Bong-Gyun;Yeom, Hyo-Won;Sung, Hong-Gye;Gil, Hyun-Yong;Yoon, Hyun-Gull
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.326-330
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    • 2011
  • Development and validation of performance analysis model for dual combustion ramjet engines has been performed. A typical performance model for hypersonic intake flow and supersonic mixing and combustion was demonstrated; Taylor-Maccoll equation for coaxial intakes and a quasi-one dimensional reacting flow analysis with CEA chemical equilibrium for supersonic combustion. The results, thermodynamic data of intake and supersonic combustor were validated with CFD numerical results.

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Combustion Test for a Supersonic Combustor Using a Direct-Connected Facility (직결형 설비를 이용한 초음속 연소기 연소 시험)

  • Yang, Inyoung;Lee, Kyung-Jae;Lee, Yang-Ji;Lee, Sanghoon;Kim, Hyungmo;Park, Poomin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.3
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    • pp.1-7
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    • 2018
  • A combustion test for a supersonic combustor was conducted using a direct-connected type supersonic combustor test facility. The facility was verified for the capability of simulating required flow conditions. The test condition was maintained at Mach 2.0, $915^{\circ}C$ and 496 kPa for 15 s. Using gaseous hydrogen as the fuel, the combustor model was also tested for its ignition and flame holding capability at the fuel equivalence ratio of 0.12. Combustion efficiency was 71%, and the supersonic flow regime was obtained at this test condition.

Effects of Combustor Configuration on the Stability of Supersonic Turbulent Lifted Flame in a DCR Engine (이중 연소 램제트 엔진에서 연소기 형상에 따른 초음속 난류 부상 화염의 안정성 연구)

  • Choi, Jeong-Yeol
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.595-598
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    • 2011
  • Supersonic combustion phenomena in the main combustor of a dual combustion ramjet (DCR) engine are studied numerically. Since the supersonic combustion is affected significantly by the compressibility effects parametric studies have been carried out for the constant are length and the divergence angle. Numerical studies with fixed inflow condition for different geometric configurations reveals that the supersonic combustion in DCR combustor has the characteristics of lifting flame, where the lifting flame is maintained near the injector tip for the case of long combustor length with small divergence angle, but the lifting height is significantly increase for large divergence angle resulting flame blow-out of the combustor. Therefore, it is concluded that flame stability should be considered sufficiently in the design o DCR combustor.

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Experimental Study of Combustion Characteristic for Dual Mode Ramjet Combustor (이중모드 램제트 연소기 연소특성 실험적 연구)

  • Shim, ChangYeul;Namkoung, HyuckJoon;Kim, SunYong;Lee, MinSoo;Park, JooHyon;Kim, DongHwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.325-329
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    • 2017
  • In this study, the combustion experiment of hydrocarbon-kerosene fueled dual mode ramjet combustor was performed at mach number 3.5~6.0 conditions. Through the experiment, the temperature and the pressure distribution inside the combustion chamber were measured and the combustion characteristics inside the combustion chamber were investigated. In the mach number 3.5~5.0 range, it was able to identify subsonic combustion in the downstream combustion chamber. In the mach number 6.0 condition, the injected fuel from the injectors was naturally fired, and it was possible to confirm that supersonic combustion was successful in the upper chamber.

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Forced Ignition Characteristics with a Plasma Jet Torch in Supersonic Flow (초음속 유동장 내 플라즈마 토치를 사용한 강제 점화 특성)

  • Kim, Chae-Hyoung;Jeung, In-Secuk;Choi, Byoung-Il;Kouchi, Toshinori;Masuya, Goro
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.363-366
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    • 2011
  • Mixing and combustion experiments with a vent slot mixer were performed in Mach 2 supersonic wind tunnel. Helium and hydrogen gases each were used for the mixing and the combustion experiment with a plasma jet (PJ) torch. The vent slot mixer holds plenty of fuel in the downstream mixing region, even though the fuel is transversely injected. In case of the combustion, the injected fuel is ignited by the PJ torch, and then unburned mixture is burned by shock-induced combustion downstream. Thermal choking in the combustor leads to shock trains in the isolator, causing the unstable combustion.

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