• Proceedings of the KSME Conference
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• 2002.08a
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• pp.271-274
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• 2002

This paper is investigated construction of the Scramjet test facility and test method of Scramjet engine combustor model. Scramiet engine combustor model test was performed at Lab C-16BK CIAM (Central Institute of Aviation Motors) at Tyraevo in Moscow. The velocity of flow in the combustion chamber equal to Mach number 2.49 with single hole fuel spray nozzle injector and test duration equal to 7 seconds. Therefore In this paper is showed high altitude test method of Scramjet combustor model and the proper structure of combustor with single hole fuel spray nozzle.

• Journal of the Korean Society of Combustion
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• v.12 no.2
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• pp.1-9
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• 2007

This paper describes numerical efforts to investigate combustion characteristics of HyShot scramjet combustor, where gaseous hydrogen is transversely injected into a supersonic cross flow. The corresponding altitude, angle of attack, and equivalence ratio are 35-23 km, $0^{\circ}$, and 0.426 respectively. Two-dimensional simulation reasonably predicts combustor inner pressure distribution and reveals periodic combustion characteristics of HyShot scramjet combustor. Altitude effects are also investigated and the strength of flow instability and subsonic boundary layer thickness affect the combustion efficiency according to altitudes. Frequency analyses provide the flow instability effects on the turbulent combustion in HyShot scramjet combustor.

• 한국연소학회:학술대회논문집
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• 2007.05a
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• pp.79-85
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• 2007

This paper describes numerical efforts to investigate combustion characteristics of HyShot scramjet combustor, where gaseous hydrogen is transversely injected into a supersonic cross flow. The corresponding altitude, angle of attack, and equivalence ratio are 35-23 km, $0^{\circ}$, and 0.426 respectively. Two-dimensional simulation reasonably predicts combustor inner pressure distribution and reveals periodic combustion characteristics of HyShot scramjet combustor. Altitude effects are also investigated and the strength of flow instability and subsonic boundary layer thickness affect the combustion efficiency according to altitudes. Frequency analyses provide the flow instability effects on the turbulent combustion in HyShot scramjet combustor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.232-235
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• 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.29-41
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• 2021

The PID controller with fin angle and thrust as control input was designed based on the aerodynamic data of scramjet system. Flight simulation following a given trajectory which strike the target point after climb and cruise with constant dynamic pressure was conducted. After that, the required thrust for the climb and cruise was calculated and the required fuel flow rate for the hydrogen fuel dual mode scramjet combustor was analyzed. The combustor analysis of this study which conducted on integrated model of independently developed inlet, combustor, nozzles and external aerodynamic models, laying the foundation for the integrated design of the air breathing hypersonic system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.277-284
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• 2017

This study is the results of the analytical research for a dual-model scramjet engine flowpath which is included inlet, isolator, combustor, and nozzle. To design a dual-mode scramjet engine and to investigate its performance, the performance analysis models and tools are required to develope for aerodynamic, thermodynamic characteristics, propulsion, and total system. Therefore, analysis models for air inlet, isolator, supersonic combustor, and nozzle of a dual-mode scramjet engine were accomplished, the performance characteristics of a dual-mode scramjet engine is investigated with using the developed analysis tools.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.367-370
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• 2011

A high-resolution numerical study is carried out to investigate the transient process of the combustion and the shock-train developments in an ethylene-fueled direct-connect dual-mode scramjet combustor. Air-throttling is then applied at the expansion part of the combustor to provide mass addition to block the flow to subsonic speed, hence to enhance the fuel-air mixing and ignition. Present simulation shows the detailed results for the better understanding of transient processes of the operation regimes in the dual-mode scramjet combustor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.304-309
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• 2017

This paper studies a nonpremixed turbulent flame in a model scramjet combustor using zonal hybrid RANS/LES method. The numerical domain is divided into two region, RANS and LES region. The interface between the two regions is treated with synthetic eddy method. A model scramjet combustor experimented at German aerospace center is selected for the comparative study. The fuel injection of cracked kerosene surrogate which is composed of ethylene and methane is considered. Turbulent combustion of cracked kerosene surrogate is achieved using flamelet approach.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.569-572
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• 2009

The numerical simulations of hydrocarbon fueled scramjet engine have been studied less than them of hydrogen fueled scramjet engine. Ethylene is selected in hydrocarbon because of its good thermochemical properties and a direct-connect scramjet combustor at the American Air Force Research laboratory is taken to a two-dimensional simulation model. Ignition time delay of ethylene was monitored and air throttling was imposed to generate ignition inside the model scramjet.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.364-367
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• 2005

A series of computational simulations have been carried out for non-reacting and reacting flows in channel-type and divergent scramjet combustor configurations with and without a cavity. Transverse injection of hydrogen is considered with the injection pressure varying from 0.5 to 1.5 MPa. The detailed resolution of the oscillatory flow and flame dynamics are captured at sufficient scale to identify the underlying physical mechanisms, and the role of combustor configuration, cavity and amount of heat addition could be understood.