• Proceedings of the Korean Institute of Navigation and Port Research Conference
• /
• 2016.05a
• /
• pp.88-89
• /
• 2016

선택적 환원 촉매(SCR : Selective Catalytic Reduction) 시스템은 대기오염을 예방하기 위한 배기가스 처리장치 중 하나이다. 본 연구에서는 전산유체역학(CFD : Computational Fluid Dynamics)를 사용하여 SCR 시스템 의 효율향상을 위하여 ANSYS-CFX package를 이용하여 점성 유동 해석을 수행하였다. SCR 시스템의 점성 유동 흐름의 전산 유체 역학을 이용하여 시뮬레이션하기 위하여 Navier-Stokes 방정식을 지배방정식으로 사용하였다. CATIA V5를 사용하여 SCR 시스템의 형상을 3D 모델링을 하였고, 암모니아와 배기가스의 혼합 비율을 확인하기 위해 요소수 분사 노즐의 위치를 변경하였다. 요소수 분사 노즐은 배기관의 입구로부터 1/3, 1/2, 2/3에 위치한다. 또한, 분사 노즐의 위치가 배기관 입구의 1/3에 위치할 때 노즐의 분사구수에 따른 효율을 확인하기 위하여 분사구수를 4Hole, 6Hole, 8Hole일 경우를 확인하여 비교하였다. 시뮬레이션의 결과로는 배기관 입구에 가까울수록, 분사구수가 많을수록 효율이 좋아짐을 확인하였다.

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 1993.04b
• /
• pp.33-37
• /
• 1993

연결부를 지닌 대형의 노즐형상 제품은 대형산업기기에서 용기의 일부 및 추진체 및 인공위성 발사 대등에서 쓰이는 제품으로 목적하고자 하는 최종 조립품의크기에 따라 제품자체의 지름이 1m 에서 수m 에 이르는 대형으로 제작된다. 대형노즐형 제품은 제품 자체의 강도, 정확한 치수 및 소요재료의 다수등도 중요한 요소이나, 가공하중의 크기에 따라 다르지만 제품을 만들기 위해서는 수만톤을 필요로하기 때문에 제품제조의 가능여부가 성형기의 능력에 의존하게 된다. 본 연구는 비교적 소형장비로써 대형 노즐형단조 품의 제작이 가능한 새로운 성형공정을 개발하는데 그 목적이 있으며 공정개발은 비교적 소형 장비로써 대형단조품의 제작이 가능하도록 하는데 촛점을 맞추고서 이루어 졌다. 이를 위해 여러가지 가능한 방법 들을 제안하고, 각각의 공정 방법들에 대해서 Plasticine 모델 시험을 통하여 소성유동에 의한 성형성과 하중을 검토한 후에 국내에서 사용가능한 장비 및 하중능력, 그리고 성형성 등을 고려하여 적절한 공정방법을 선택하였다. 선택된 공정에서 점진적 팽창단조를 위한 예비 성형체의 결정 및 공정변수의 결정등을 납 모델링실험을 행하여하였으며 실재 재료의 축소모형실험을 수행하여 공정을 확인 하였다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.25 no.3
• /
• pp.1-13
• /
• 2021

Effects of the nozzle wall angles on the supersonic flow field in a thrust optimized nozzle were numerically investigated. The combustor and operating condition of 30-tonf rocket engine was selected to study the optimum nozzle shape. The nozzle flow of combustion products was realized by the shifting equilibrium calculation for the propellant of kerosene-LOx. The change of nozzle wall angles induced different developing patterns of the internal and secondary shock wave. The optimum nozzle was obtained when the internal shock was in a specific position at the nozzle outlet. The nozzle wall angles of the optimum nozzle were very similar to those of the optimum nozzle which does not consider the shock wave.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.18 no.2
• /
• pp.80-85
• /
• 2014

Side jet thruster using nozzle closure separation device provides a solid rocket with a trajectory shift function. Side jet thruster consists of low combustion temperature propellant, neutral type propellant grain and nozzle closure separation device. If a trajectory shift is required, side jet thrust is generated on the rocket by separating some nozzle closures located in the opposite direction to thrust. After completing trajectory shift, the other nozzle closures located in the thrust direction are separated to cease side jet thrust. The operation process is verified through ground static test. The result in this study can be applied to changing rocket trajectory by controlling side jet thrust through nozzle closure separation.

• Korean Chemical Engineering Research
• /
• v.47 no.5
• /
• pp.630-638
• /
• 2009

A computational fluid dynamics(CFD) model is developed and validated with on-site experiments for a urea-based SNCR(selective non-catalytic reduction) process to reduce the nitrogen oxides($NO_x$) in a municipal incinerator. The three-dimensional turbulent reacting flow CFD model having a seven global reaction mechanism under the condition of low CO concentration and 12% excess air and droplet evaporation is used for fluid dynamics simulation of the SNCR process installed in the incinerator. In this SNCR process, urea solution and atomizing air were injected into the secondary combustor, using one front nozzle and two side nozzles. The exit temperature($980^{\circ}C$) of simulation has the same value as in situ experiment one. The $NO_x$ reduction efficiencies of 57% and 59% are obtained from the experiment and CFD simulation, respectively at NSR=1.8(normalized stoichiometric ratio) for the equal flow rate ratio from the three nozzles. It is observed in the CFD simulations with varying the flowrate ratio of the three nozzles that the injection of a two times larger front nozzle flowrate than the side nozzle flowrate produces 8% higher $NO_x$ reduction efficiency than the injection of the equal ratio flowrate in each nozzle.

• Clean Technology
• /
• v.18 no.4
• /
• pp.410-418
• /
• 2012

The performance of the ammonia injection gun (AIG) used for maximizing the utilization of reducing agent in the selective catalytic reduction (SCR) system is decided by several parameters such as the pattern of flow distribution, geometry of the air distribution manifold (ADM) and the array and geometry of nozzles. In the study, the uniformity of jet flows from the nozzles in AIG was analyzed statistically by using the computational fluid dynamics (CFD) method to evaluate the role of design parameters on the performance of the SCR system. The uniformity of jet flows from the nozzles is being deteriorated with increasing the supplying flow rate to the AIG. Distribution rates to each branch pipe become lower with decreasing distance to the header, and flow rates from nozzle are also reduced with decreasing distance to the header. The uniformity of jet flows from nozzles becomes stable significantly when the ratio of summative area of nozzles to each sectional area of the branch pipe is below 0.5.

• Journal of Animal Environmental Science
• /
• v.11 no.2
• /
• pp.111-116
• /
• 2005

The purpose of this study was to analyze the performance of vehicle disinfector nozzles using at the livestock farm. The nozzle of vehicle disinfectors was measured spraying rate and equality distribution ratio by pressures. The spraying rate of TK-I's nozzle was 1,605 ml/min at 3 MPa, TK-II's nozzle was 2,020 ml/min, JA's nozzle was 1,150 ml/min and IS's nozzle was 795 ml/min. The number of nozzles of TK-I's, TK-II's, JA's and IS's for reasonable spraying rate($25{\ell}/min$. at 3 MPa) was respectively 16, 13, 22 and 32 units. The equality distribution ratio of TK-I's nozzle by pressures was equalized and the nozzles of TK-II's, JA's and IS's was sprayed to the center or side more then other sides in the measured boxes.

• Journal of Astronomy and Space Sciences
• /
• v.3 no.1
• /
• pp.29-40
• /
• 1986

It is the aims of this study to choose the materials and determine the material thickness of laminated Rocket Nozzle Wall operating at high pressure and high temperature. The heat conduction analysis of each layer was performed by Crank Nicolson method changing the thickness and the materials for the imput data of Tungsten, Graphite, Alumina, Aluminum, Molybdenum, Plastic laminate. The results of the study for pressure of 93.5kg/$cm^2$ and temperature of $3000^{circ}C$ in the nozzle dia of 40cm are as follows.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2013.08a
• /
• pp.322-322
• /
• 2013

$CO_2$를 $CH_4$와 열 및 전기화학적인 반응을 통해 고농도의 CO 및 $H_2$로 구성된 합성가스로 효율적으로 전환시키기 위해, 반응가스 주입용 간극형 노즐을 가진 비이송식 직류 열플라즈마 토치 시스템을 설계, 제작하고 다양한 조건에서 이 두 가스의 개질 실험을 수행하였다. 설계 제작된 간극형 노즐과 리액터 내 고온 반응 영역을 활용한 $CO_2$ 및 $CH_4$ 반응가스의 효율적인 처리를 통하여, 최고 70% 이상의 $CO_2$ 및 $CH_4$의 전환율과 최고 80% 이상의 CO 및 $H_2$선택도를 달성할 수 있음을 확인하였다. 또한, 상기 조건의 경우, 플라즈마 입력 전력 10.6 kW 대비 49 lpm 의 반응가스 처리량을 통하여 얻은 것으로 최고 2.5 mmol/kJ 이상의 Specific Energy Requirement (SER) 조건도 만족할 수 있음을 보였다. 특히, 제안된 막대 음극-반응 가스 주입구를 가진 양극 노즐 플라즈마 토치의 경우, $CH_4$ 반응가스를 음극에 직접 닿지 않도록 간극을 통해 주입하게 함으로써, 반응 가스 분해에 의한 음극 등 전극 부식을 최소화하면서도 고에너지 전자가 풍부한 아크 컬럼에 의해 $CO_2$ 및 $CH_4$의 전환 반응을 효율적으로 일으킬 수 있어 효율적인 $CO_2$ 및 $CH_4$ 개질을 위한 열플라즈마 토치 시스템의 개발이 기대된다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.3
• /
• pp.28-39
• /
• 2018

In this study, numerical simulations were performed for steady and unsteady state characteristics of length effects on linear pintle nozzles using the overset grid method. Nozzles and pintles are created separately by an auto grid generation program to use the overset grid method. Appropriate turbulent models and numerical methods are selected for the validation of simulations. Pintle shapes are chosen from five types, with differences in the ratio of length and diameter. The longer the pintle length, the greater the thrust and thrust coefficient. The chamber pressure tendency of steady-state and unsteady-state are different for various pintle velocities. The thrust of the nozzle exit responds to changes in the nozzle throat in the unsteady-state, and the speed of pressure propagation wave generated by movement of the pintle is considered to predict the major factor of performance.