• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.255-258
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• 2004

In order to provide a useful data for combustion chamber design, a numerical analysis for spray combustion of liquid fuel and oxidizer in combustion chamber has been conducted. High temperature nitrogen gas in low speed has been conveyed for the ignition of the liquid fuel and oxidizer mixture. Temperature and velocity distributions affected by characteristics of liquid fuel and oxidizer combustion have been investigated.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.3
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• pp.309-314
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• 2012

Flame flickering occurs mainly because of the buoyancy force for pool fires under ambient air. The cup-burner flame was used for experimental investigation of the effect of the oxidizer velocity on the gravitational instability. The results showed that the flickering frequency decreased with increasing oxidizer velocity. The frequency-buoyancy relation with nondimensional variables coincided with that of the buoyant flume and pool fires when the characteristic velocity was defined as the difference between the fuel and oxidizer velocities, which implies that the origin of the gravitational instability is the Kelvin-Helmholtz instability in the shear layer. The effect of the oxidizer composition on the instability was also examined through nitrogen dilution in the oxidizer stream. As the concentration of inert gas increased, the length of the blue flame increased and lift-off behavior was observed. The oscillation frequency was independent of the dilution ratio, but was related to the local flame structure.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.2
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• pp.48-56
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• 2008

In the rocket preburner, oxidizer-rich combustion with liquid oxygen and kerosene is very challenging work. The key factor of stable flame is good mixing and that is controlled by the injector performance. We have studied spray characteristics of the oxidizer-rich rocket preburner injector in high pressure environments. The injector is composed of fuel orifices, oxidizer orifices and cooling skirt with liquid oxygen. By using this apparatus, we have taken photographs and measured Sauter mean diameter with changing ambient pressure from 0 to 30 kgf/cm2[g]. Droplet diameter is measured by the image processing technique. From the test results, we could understand spray characteristics of the oxidizer-rich preburner injector and this result could be applied to the development of the oxidizer rich preburner system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.243-247
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• 2007

Fuel mass flux was experienced with a function of the oxidizer mass flux using initial port area of solid fuel, in stead of regression rate correlation which shows combustion characteristic in hybrid propulsion. The burning rate could be easily obtained by using the oxidizer mass flux of initial port area without iteration, and fuel configuration could be designed simply. In this experiments PE was used as fuel, COX was used as oxidizer. A variation of mass flux of solid fuel with port area is considered by changing the burning time. In the case of approximate 0.5 for an exponent of oxidizer mass flux, using the fuel mass flux correlation is more suitable than regression rate correlation in hybrid propulsion.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.92-97
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• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The oxidizer supply system modeling using AMESim was performed based on the results of the detailed design, and the oxidizer supply characteristics was analyzed in this paper.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.2
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• pp.78-88
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• 2005

The combustion characteristics of End-Burning hybrid combustor using different types of injector system are numerically investigated to visualize the temperature fields in the combustion chamber The basic characteristics of combustion with different O/F ratio is also analyzed in order to capture the main behavior of diffusion flame inside the swirl induced hybrid combustion chamber It was found that the arrangement of oxidizer injectors give strong effect on the temperature field dominating mixing between fuel and oxidizer. The results show that among five different oxidizer injectors arrangement, the counter flow injector has the highest mixing efficiency. However, the observed high wall temperature presence near the oxidizer injectors remains to be solved.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.106-109
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• 2012

It was designed and tested ignition that an oxidizer rich preburner for a staged combustion cycle liquid rocket engine propelled by kerosene and LOx. Operation conditions of the preburner are about 60 of OF ratio and 20 MPa of combustion pressure. Ignition characteristics were compared by propellants flowrate. As the results, the higher propellants flowrate, the shorter the ignition delay time and the higher ignition stiffness. The ignition delay time was affected by incoming the oxidizer flowrate through the refrigerative cooling channels. The oxidizer flowrate from the cooling channels decreased by inflow of combustion gas during initial ignition. The oxidizer flowrate of the cooling channels increases, it is rapid recovery by cooling effect, eventually the ignition delay time decreases.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.502-506
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• 2012

The propulsion system of space launch vehicle generates thrust by supplying oxidizer and fuel to combustion chamber. KSLV-II 2nd stage engine, currently under development by KARI, is to use liquid oxygen as a oxidizer and JET-A1 as a fuel. The 2nd stage pump-fed engine is mainly composed of combustion chamber, turbo-pump and engine supply system. To develop liquid propulsion engine, the development of combustion chamber must be preceded. For performance validation of the combustion chamber, the designed and manufactured combustion chamber should be tested in combustion chamber test facility (CCTF). The detailed design for the planned CCTF in Naro Space Center was conducted. The oxidizer supply system modeling using AMESim was performed based on the results of the detailed design, and the oxidizer supply characteristics was analyzed in this paper.

• Fire Science and Engineering
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• v.32 no.6
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• pp.22-27
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• 2018

The flame length in coaxial diffusion flame configurations was investigated when the kerosene fuel flow rate, temperature of the oxidizer stream, and inert gas concentrations in the oxidizer stream were varied. The diffusion flame was photographed using a Schlieren camera under each of the experimental conditions and the obtained images were then digitized to measure the flame length. The measured flame lengths were proportional to the kerosene fuel flow rate and increased with increasing temperature of the oxidizer stream. In addition, increases in the inert gas concentration in the oxidizer stream resulted in stretching of the flame. In particular, the flame was further elongated in the oxidizer steam diluted with helium gas. Inert substitutions in the oxidizer stream that can adjust the viscous drag are believed to be one of the important mechanisms that affect the length of the coaxial diffusion flames.

• Fire Science and Engineering
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• v.15 no.1
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• pp.16-22
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• 2001

Thermal properties of PP and LLDPE dusts from chemical plant and their risks of coexisting with oxidizer were investigated by a pressure vessel. The thermal decomposition of PP and LLDPE dusts with temperature using DSC and the weight loss with temperature using TGA were also investigated to find the thermal hazard of PP and LLDPE dusts. Using the pressure vessel which can estimate ignition and explosion of PP and LLDPE dusts coexisting with oxidizer, a series of bursting of a rupture disc, experiments has been conducted by varying the orifice diameters the weight ratio of the sample coexisting with oxidizers and the species of oxidizer. And fire gases was measured by gas analyser ($ECOM-A^+$). According to the results of the thermal analysis of PP and LLDPE dusts, the decomposition temperature range of PP and LLDPE dusts was 200 to 350 and 300 to $500^{\circ}c$, respectively. The risk of PP and LLDPE dusts coexisting with oxidizer was increased as the orifice diameter was decreased. On the other hand, it was increased as the weight ratio of the sample to the oxidizer were increased. In addition, the risk of PP and LLDPE dusts coexisting with oxidizer was affected by the decomposition temperature of the sample and oxidizer. It is found that the risk of fire becomes high when the decomposition temperature of the sample is about same as that of oxidizer. Also, the fire gases was occurred carbon monoxide and carbon dioxide. The amount of carbon monoxide generated was found to be much higher in PP decomposition than in LLDPE due to incomplete combustion of PP which has high content of carbon in chemical compound.