• Journal of the Korean Society of Propulsion Engineers
• /
• v.19 no.2
• /
• pp.1-8
• /
• 2015

Dual pulse rocket motor is a variant of solid rocket motor with two propellant grain separated by a pulse separation device. The major performance of such a rocket motor is influenced by the change in the hole area of pulse separation device to nozzle throat area ratio. In this study, we performed flow analysis to investigate the internal flow characteristics according to the pulse separation device hole area to nozzle throat area ratio change. Gases used flow analysis were used combustion gas of HTPB/AP composite propellant and nitrogen gas. Flow analysis results of the dual pulse rocket motor were validated by comparison with experimental results of pneumatics. Commercial CFD code ANSYS FLUENT 14.5 is used in this study to simulate flow analysis.

• 한국전산유체공학회:학술대회논문집
• /
• 2002.10a
• /
• pp.41-46
• /
• 2002

A numerical simulation was made to determine the motion of particles in the fluid. The simulation is based on the Eulerian-Lagrangian method. The fluid motion was solved using a PISO-based finite-element method and a $\kappa-\epsilon$ model of turbulence. In the Lagrangian method for the solid phase, the trajectories of particles are calculated by integrating the equations of motion of a single Particle, and the collision between particles are taken into account. The influence of particles on the fluid phase is taken into account by introducing source terms in the Eulerian equations govering the fluid flow. It is known as the particle-source-in-cell (PSIC) method. Also, the turbulent effect in the particles and fluid notion is considered. The numerical results were compared with the experiment for a two-phase flow in a vertical pipe.

• KEPCO Journal on Electric Power and Energy
• /
• v.8 no.2
• /
• pp.97-101
• /
• 2022

In this study we investigated the gas to solid heat transfer of bubbling fluidized bed bottom ash cooler installed at the Donghae power plant in South Korea. Several different analyses are done through 1-D calculations and 3-D CFD simulation to predict the bottom ash exit temperatures when it exits the ash cooler. Three different cases are set up to have consideration of unburnt carbon in the bottom ash. Sensible heat comparison and heat transfer calculation between the fluidization air and the bottom ash are conducted and 3-D CFD analysis is done on three cases. We have obtained the results that the bottom ash with unburnt carbon is exiting the ash cooler, exceeding the targeted temperature from both 1-D calculation and 3-D CFD simulation.

• KSCE Journal of Civil and Environmental Engineering Research
• /
• v.12 no.1
• /
• pp.207-217
• /
• 1992

In this study, isolated and cultured nitrogen fixed microbes were seeded in the three-phase fluidized bed in which gas, solid and liquid were contacted directly. Input velocity was varied from 8.12 cm/hr to 16.32 cm/hr. And upflow gas pressure was fixed to 80 psi. Return ratios were from 0.2 to 0.6 with the each experimental condition. According to these condition, movement of media, growth of biofilm and removal efficiency were measured. As the results, in case of briquette ash, biofilm was developed to $170{\mu}m$ when velocity was 8.12 cm/hr and return ratio was 0.6. In this condition, COD removal efficiency was 97% and $NH_4$-N removal efficiency was 83%. At the same condition, biofilm thickness of glass bead was $17.59{\mu}m$ and its COD and $NH_4$-N removal efficiency was 83% and 72%. Nitrogen fixed microbes have following characters: it formed dark-brownish sludge, excellent adhesive force, easy solid-liquid separation and low oxygen uptake ratio, but sensitive to DO concentration. Not only it endured shock loading, but required short time to steady state.

• Korean Chemical Engineering Research
• /
• v.43 no.4
• /
• pp.525-530
• /
• 2005

The erosion rate of water wall tube has been measured and discussed in a commercial circulating fluidized bed combustor (200 ton steam/hr, $4.97{\times}9.90{\times}28.98m\;height$). Tube thickness was measured with ultrasonic method. Severe tube erosion rate was observed in the splash region on all waterwalls including wingwalls. The tube erosion rate increased after an initial decrease as height from the distributor increased. The difference of erosion rate among wing walls was found due to unbalanced distribution of gas and solid flow rates. The erosion rate of the wing wall increased as location of the wing wall became closer to the center of combustor crosssection.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.953-961
• /
• 2011

A numerical model of the igniter for the interior ballistics has been developed combining the lumped parameter model with the theoretical equation of the orifice. With the developed model of the igniter, the numerical study on characteristics of the interior ballistics according to the igniter configuration in terms of the igniter length, the side hole diameter, and the distribution of side holes has been conducted. As results of the calculation of the pressure difference between the breech and shot base, the low frequency oscillations have been influenced by the igniter length, while the high frequency oscillations have been affected by the side hole diameter and the distribution of side holes.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.17 no.2
• /
• pp.105-113
• /
• 2013

A numerical model of the igniter for the interior ballistics has been developed by combining lumped parameter model with the theoretical equation of orifice. With the developed model of the igniter, the numerical study on characteristics of the interior ballistics has been conducted according to the igniter configuration in terms of igniter length, side hole diameter, and distribution of side holes. As results of the calculation of the pressure difference between the breech and shot base, the low-cycle oscillations have been influenced by the igniter length, while the high-cycle oscillations have been affected by the side hole diameter and the distribution of side holes.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2013.02a
• /
• pp.303-303
• /
• 2013

표면에 부착된 나노/마이크로 입자는 다양한 분야에서 오염물질로 작용한다. 특히 형상이 미세하고 공정 단계가 복잡한 반도체 및 디스플레이 등의 전자 소자 공정에서 미치는 영향이 크다. 따라서 입자상 오염물질의 제거에 관하여 상용화된 습식 세정 방법이 다양하게 존재하지만 표면 손상, 화학 반응, 부산물, 세정 효율 등 여러 가지 문제점이 있어 새로운 세정 방법이 요구된다. 이에 건식 세정 방법, 그 중에서도 입자의 충돌을 통해 제거하는 방법인 에어로졸 세정, 필렛 세정 등이 개발되었으나 마이크로 크기로 생성되는 입자로 인하여 형상의 손상이 크다. 따라서 본 연구에서는 나노 단위로 기체/고체 혼합물만 생성하여 세정하는 가스 클러스터 세정 방법을 이용하여 이러한 문제점을 해결하고자 하였다. 클러스터 세정 장비를 이용한 표면 처리는 충돌에 의한 제거에 기반한다. 따라서 생성 및 가속되는 클러스터로부터 대상으로 전달되는 운동량의 정도가 세정 특성에 영향을 미치며 이는 생성되는 클러스터의 크기에 종속적이다. 생성 클러스터의 크기 분포는 분사 거리, 유량, 분사 각도, 노즐 냉각 온도 등의 변수에 관한 함수이다. 따라서 본 연구에서는 $CO_2$ 클러스터를 이용한 세정 특성을 정의 및 제어하기 위하여 생성되는 클러스터 특성에 관하여 이론적, 수치 해석적, 실험적 연구를 수행하였다. 먼저, $CO_2$의 물리적 특성 및 이를 이용한 특정 크기 오염 물질을 제거하는데 요구되는 임계 클러스터 크기 계산을 이론적으로 구하였다. 이는 오염물질의 부착력과 클러스터의 운동량 전달에 의한 제거력의 비교를 통해 이루어졌다. 두 번째로 클러스터 크기분포를 수치 해석적으로 예측하기 위하여 각 조건에 대하여 유동해석을 수행하고 이를 통해 구해진 노즐 내 기체의 냉각 속도를 GDE (General Dynamic Equation) 계산에 대입하여 구하였다. 마지막으로 PBMS(Particle Beam Mass Spectrometer)를 이용하여 실험적으로 클러스터 크기분포를 각 조건에 대하여 구할 수 있었다. 또한 크기 분포 경향에 대한 간접적 확인을 위하여 포토레지스트가 코팅된 웨이퍼에 클러스터의 충격으로 생성된 크레이터 크기의 경향을 분석하였다. 이와 같은 방법에 의하여 생성되는 클러스터는 노즐의 유량 증가, 온도 상승에 각각 비례하여 작아지는 것을 확인할 수 있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.520-526
• /
• 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 Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.70-75
• /
• 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.