• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.4
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• pp.83-92
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• 1999

A numerical analysis of two phase flow in the solid rocket nozzle was conducted. Stoke number was defined over the various aluminum oxide($AI_2$$O_3$) particle sizes and particle trajectories were treated by Lagrangian approach. Particle stability was considered by the definition of Weber number in a rocket nozzle. Large particles are divided after the nozzle throat as the flow accelerates rapidly. The division of particles changes the particle distribution at the nozzle exit. From the above results, it was found that the nozzle converge section surface might be affected by aluminum oxide particles. Also, Mechanical erosion rate of nozzle surface was predicted for different materials.

• Proceedings of the KAIS Fall Conference
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• 2007.11a
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• pp.312-314
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• 2007

본 논문에서는 비데용 물 분사 노즐의 내부유동을 가시화하기 위해서 여러 가지 설계변수에 관한 연구가 수행되었다. 특히 물 분사에 만 의존했던 과거의 세정시스템과는 달리 물과 공기를 혼합해서 물도 절약하고 세정의 효과도 높이고자 하는 기술을 개발하고자 했다. 상용코드인 CFD-ACE+를 이용하여 내부유동 특성을 관찰했고 여러 가지 인체 공학적인 설계가 되도록 다양한 각도에서 검토되었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.18-21
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• 2011

In this study, basic research on the pressure control using driven pintle of modulatable thruster is presented. For this purpose, pintle thruster and pintle shape was developed. The actuator model was selected by calculating pintle load using Fluent software. Preliminary unsteady experimental results show that huge pressure oscillation is occurred as the pintle approach toward nozzle wall. From the preliminary experimental results, we could see possibility of pressure control of the modulatable thruster.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.32-32
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• 1998

고체 추진제 로켓의 연소시에 발생되는 산화 알루미늄(A1$_2$O$_3$) 입자는 로켓 추진 노즐에서 팽창과정의 효율을 저하시키는 요소가 되며, 이러한 비효율성은 연소 가스와 입자간의 비평형 상태 효과와 기본적인 속도와 열적 차이에 의해서 발생된다고 보고되었다. 또한 연소시 발생된 산화 알루미늄 입자는 높은 열과 큰 운동량을 가지고 로켓 노즐 내부를 유동하게 되며, 매우 많은 량이 짧은 시간에 고온 고속으로 노즐 벽면이나 기타 구조물에 충돌 및 점착하기 때문에 로켓 노즐내의 표면이 손상을 입게 되고, 로켓의 방향 제어 및 조정 안정성이 저하되며, 구조적인 강도가 약화 될 수 있다. 또한 산화 알루미늄 액적들의 경우 노즐 벽면에 고착되게 되면 로켓의 중량 증가로 인해서 추력의 손실을 초래할 수 있다. 따라서 이러한 연소 부산물들의 운동 경로와 충돌 위치 및 표면에서의 충돌량과 그리고 충돌에 따른 마모량 및 점착 그리고 열전달 특성을 예측하는 것이 필수적이다.

• Proceedings of the KAIS Fall Conference
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• 2008.05a
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• pp.299-301
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• 2008

본 논문은 세정용 노즐의 기하학적인 형상을 변화시킴으로써 물과 공기를 이용한 비데용 분사노즐의 세정효과를 극대화하기 위한 연구이다. 세정효과와 절수를 목적으로 과거 물만을 공급되었던 비데노즐에 공기를 물을 혼합한 혼합류를 주입하면서 형성되는 노즐 내부 유동현상을 상용코드인 CFD-ACE+을 이용하여 가시화하고자 했다.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.37 no.11
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• pp.1361-1369
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• 2013

This study performs a computational fluid dynamics (CFD) analysis of the inner flow of a multihole injector nozzle by using ANSYS CFX 13.0. Based on the obtained results, a design of experiment (DOE) was performed and applied to investigate the effects of injector nozzle design parameters on cavitation. To analyze the design sensitivity and signal-to-noise ratio (S/N ratio), the hole diameter, hole length, hole angle, and K-factor of the nozzle hole were selected as design parameters, and the effect of these parameters was investigated at 16 experimental points. Consequently, it was found that the effect of the K-factor on the cavitation and inner flow of the injector nozzle is the greatest. Thus, the selection of a suitable K-factor is important in nozzle design considering cavitation flow.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.3
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• pp.31-39
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• 2011

The flowfield in a solid rocket motor was simulated at the wall-injection test model, which has a fin-slot grain and submerged nozzle, and visualized by a smoke-wire. The high speed CCD camera captured the visualized images around the nozzle inlet through the grain center port. The vortical tube structure and circumferential flow patterns at the nozzle throat were visualized. The radial momentum transfer caused by the shear-interactions of slot-outlet flow, fin-base flow and grain port flow from upstream worked as the source of these phenomena.

• Journal of Energy Engineering
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• v.23 no.4
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• pp.95-105
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• 2014

The CUPID code has been developed for a transient, three-dimensional, two-phase flow analysis at a component scale. It has been validated against a wide range of two-phase flow experiments. Especially, to assess its applicability to single- and two-phase flow analyses in the Calandria vessel of a CANDU nuclear reactor, it was validated using the experimental data of the 1/4-scaled facility of a Calandria vessel at the STERN laboratory. In this study, a preliminary thermal-hydraulic analysis of the CANDU reactor moderator tank using the CUPID code is carried out, which is based on the results of the previous studies. The complicated internal structure of the Calandria vessel and the inlet nozzle was modeled in a simplified manner by using a porous media approach. One of the most important factors in the analysis was found to be the modeling of the tank inlet nozzle. A calculation with a simple inlet nozzle modeling resulted in thermal stratification by buoyance, leading to a boiling from the top of the Calandria tank. This is not realistic at all and may occur due to the lack of inlet flow momentum. To improve this, a new nozzle modeling was used, which can preserve both mass flow and momentum flow at the inlet nozzle. This resulted in a realistic temperature distribution in the tank. In conclusion, it was shown that the CUPID code is applicable to thermal-hydraulic analysis of the CANDU reactor moderator tank using the cost-effective porous media approach and that the inlet nozzle modeling is very important for the flow analysis in the tank.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.349-352
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• 2008

Thrust vectoring control by injection of secondary jet inside a convergent-divergent supersonic nozzle was studied by both experimentally and computationally. For various stagnation pressure of the secondary jet injected at a specific location(12 mm-downstream of throat) in the divergent section of nozzle, the characteristics of thrust vectoring were observed. Present numerical results were compared with previous investigators' results and Schlieren flow visualizations for the identical boundary conditions, and it showed a qualitatively good agreement. It was also noticed that the characteristics of thrust vectoring is strongly related to the reflection structure of oblique shock inside nozzle, ie., the pressure ratio of the secondary jet, SPR.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.17 no.6
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• pp.650-655
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• 2016

In this study, a computational simulation of the internal flow characteristics was carried out for a Urea-SCR Injector. A single hole swirl injector with a swirl disk and slanted nozzle was used in this simulation. The maximum needle lift and opening velocity were selected as the design parameters. To analyze the unsteady internal flow characteristics of the Urea-SCR injector, the moving grid technique was applied to simulate the delicate needle movement. According to the simulation results, the injected mass flow rate from the Urea-SCR injector decreased with increasing needle opening velocity and maximum needle lift. This is because the Urea-solution tends to fill the empty space that the needle previously occupied. The swirl flow is decreased as the flow goes through the injector nozzle, because of the friction with the nozzle wall. Also, during the maximum needle lift period, the swirl coefficient and mean swirl coefficient increase with increasing needle lift. The results of this study may be used as the basic design data of related injectors.