• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.1
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• pp.47-54
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• 2002

This paper presents the results of an experimental investigation on the combustion of single droplets and 1-D droplet arrays of jet A-1 fuel droplets in atmospheric pressure. Experimental results indicate that burning rate constants$({\kappa}_c)$ of jet A-1 fuel droplets were independent of initial droplet size as $0.915{mm}^2$/sec. It was acquired a general relationship expressing the variation of $d^2$ with time for droplet burning For 1-D droplet arrays $(l/d_o$=1.208{\sim}2.922)$/TEX>, the burning rate constant ${\kappa}_c$ decreased with decreasing droplet spacing $l/d_o$ and, The effect on combustion rate constant ${\kappa}_c$ was stronger to second fuel droplet than third fuel droplet with uniform droplet distance

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.3
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• pp.53-60
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• 2002

This paper presents the results of the experimental investigation on the effect of acoustic wave on the combustion of suspended A-1 jet fuel droplets in atmospheric pressure. Experimental results indicate that A-1 jet fuel droplet burning rate constants $k_c$ were independent of initial droplet size and the relative evaporation/burning-rate constant $k_{e'}k_c$(ratio of the acoustically disturbed evaporation/burning-rate constant to the undisturbed evaporation/burning-rate constant) increased remarkably 1.2~1.51times, 1.04~1.42times, for frequency below 100Hz, and sound pressure level above 80dB.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.70-75
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• 2012

In this paper, the regression rate of the End-Burning Hybrid Rocket with variation of swirl intensity was investigated experimentally with the variation of fuel diameter, injector shape and angle. When fuel grain diameter is large, fuel mass flow rate increases. And the injector diameter increase, fuel regression rate decrease. The impinging effect of oxidizer flow on fuel surface for fuel combustion efficiency is stronger than swril effect in this End-burning propulsion system. The relation between the regression rate, oxidizer mass flux and swirl intensity was obtained.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.3
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• pp.264-270
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• 2008

Most of burning rate models used in hybrid combustion depend solely on oxidizer flux. But this empirical relation can not represent well the important effect of the thermo-chemical properties of solid fuel and thereby requires different value of empirical exponent and constant for each fuel considered. In this study, a new burning rate correlation was proposed using the mass transfer number(B number) which encompasses the thermochemistry effect of solid fuel and the aerodynamic effect caused by the combustion on the solid fuel surface where the effect of aerodynamic property in the mass transfer number was studied. The PMMA, PP, and PE were chosen as fuel, and gas oxygen as oxidizer. The new empirical burning rate expression depending on both the oxidizer flux and the mass transfer number was able to predict the burning rate of each fuel with just a single exponent value and constant, and it was found that the aerodynamic effect on the blowing effect did show a minor effect on the burning rate correlation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.520-526
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• 2012

The appearance of the negative differential pressure(NDP), in which the shot base pressure is higher than the breech pressure, indicates that a potential damage on the gun system is increased. In order to safeguard the gun system, the igniter must be designed to minimize the NDP during the firing process. From this reason, the effect of igniter's burning rate on the NDP of the interior ballistics has been investigated through the numerical simulations. The NDP has been increased with increment of the coefficient in the burning rate of the igniter. A sudden change of the chamber pressure has been shown in case of using a singular coefficient.

• Proceedings of the Materials Research Society of Korea Conference
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• 2003.11a
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• pp.239-239
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• 2003

탄소재료의 산화반응을 설명한 대부분의 논문은 TGA(Thermo Gravimetric Analysis)를 이용한 연구이다. TGA 장치는 가열이 필요한 물질의 반응연구에 다양하게 이용되고 있는데, 온도에 대한 무게 변화를 간편하게 알 수 있다는 장점과 함께 보편적으로 편리한 Arrhenius형태의 속도식으로 해석된다. 많은 연구자들은 TGA를 이용하여 다양한 탄소재료에 대한 반응속도상수를 구하였으며, 반응기체, 반응온도 및 원료물질에 따라 다른 속도를 나타내는 실험결과를 표준화된 속도식으로 표현하고자 하는 노력이 있었다. 그러나 이런 대부분의 연구는 coal 등과 같은 탄소재료의 연소특성을 이용하려는 에너지 변환 연구가 주를 이루어 왔으며, 탄소섬유의 산화반응에 대한 표준화 식으로 해석한 보고는 거의 없는 실정이다. 이 연구에서는 내부구조가 현격하게 차이나는 다른 두 종류의 피치계 탄소섬유를 TGA를 이용하여 등온 산화반응 시켰다. 반응기체의 종류와 반응온도를 변화시켜 산화반응조건에 따른 중량변화를 관찰하였고, 여러 산화조건에서 얻어진 산화속도를 Kasaoka 등에 의해 제안된 표준화식을 이용하여 산화반응의 평균 속도상수 K와 전환율이 0.5일 때의 속도상수 $k_{f=0.5}$ 결과를 비교하여 산화 반응속도를 정량적으로 해석하고자 하였다.다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.13-13
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• 1998

램가속기의 발진 과정에서 유동장 내에는 수백 기압 이상의 고압 영역이 존재하며 이러한 영역에서는 이상기체 가정이 더 이상 유효하지 않게 된다. 따라서 램가속기 작동조건에 적용 가능한 적절한 형태의 실제 기체 상태 방정식이 요구된다 또한 기존의 온도에 종속적인 Arrhenius 형태의 기초 반응들로 이루어진 축소 화학 반응 모델은 상압 조건하에서 적용 가능하므로 고압 화경에서 적용하기 위해서는 온도뿐 아니라 압력에 종속적인 형태의 반응율 상수가 도입되어야 한다.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2008.11a
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• pp.68-75
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• 2008

화재시뮬레이션용 소프트웨어인 FDS (Fire Dynamics Simulator)의 수직벽 화재 시뮬레이션에 있어서의 문제점을 파악하기 위해, 수직벽 프로필렌 화재에 대한 시뮬레이션을 수행하였다. 성능기반설계 등에 널리 사용되고 있는 이 전산유체역학 모델에 포함되어있는 주요 매개변수의 기본값을 사용한 경우, 수직벽 화재에서는 정확도가 매우 낮음을 확인하였다. 프로필렌 연소율 $10.08g/m^2$-s과 $29.29g/m^2$-s에 대한 주요 매개변수의 조사를 수행한 결과, 스마고린스키 상수(Smagorinsky constant)가 기본값인 0.2에서 수직벽에 형성된 경계층이 층류로 예측되었다. 스마고린스키 상수가 0.1일 때 온도분포가 실험과 비교적 잘 일치하였으나 벽면에서의 열유속에는 큰 오차가 있음을 확인하였다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.10 no.7
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• pp.1465-1472
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• 2009

The effect of heat loss rate on NOx formation of $CH_4/air$premixed flame were examined numerically in a perfectly stirred reactor. The following conclusions were drawn. Under the adiabatic wall condition, an increase in the residence time causes a remarkable increases in NOx emission. Under the heat loss conditions, however, NOx decreases significantly as the heat transfer coefficient and residence time increase. As the heat loss rate increases, Thermal NO mechanism and Re-burning NO mechanism play an important role in the NOx reduction, but Prompt NO mechanism and $N_2O$-intermediate NO mechanism lead to the increase in NOx production. Although the NOx formation is actually related to complex NOx mechanism with the changes in the heat transfer coefficient and residence time, it was found that NOx concentration can be represented by independent Thermal NO mechanism. From these results, new NOx correlation combined with the heat loss rate and residence time was suggested for predicting the NOx concentration in a practical $CH_4/air$premixed combustor.

• Korean Chemical Engineering Research
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• v.50 no.5
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• pp.843-849
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• 2012

When we use NiO based particle as an oxygen carrier in a chemical looping combustion system, the fuel conversion and the $CO_2$ selectivity decreased with increasing reaction temperature within high temperature range (> $900^{\circ}C$) due to the increment of exhaust CO concentration from reduction reactor. To improve reduction reactivity at high temperature, the applicable metal oxide component was selected by calculation of the equilibrium CO concentration of metal oxide components. After that, feasibility of reduction reactivity improvement at high temperature was checked by using solid mixture of the selected metal oxide particle and NiO based oxygen carrier. The reactivity was measured and investigated using batch type fluidized bed. The solid mixture of $Co_3O_4/CoAl_2O_4$(10%) and OCN706-1100(90%) showed higher fuel conversion, higher $CO_2$ selectivity and lower CO concentration than OCN706-1100(100%) cases. Consequently, we could conclude that improvement of reduction reactivity at high temperature range by adding some $Co_3O_4$ based oxygen carrier was feasible.