• Korean Chemical Engineering Research
• /
• v.48 no.4
• /
• pp.450-456
• /
• 2010

This study was conducted in order to design a piston, part of a shock absorber, and the findings after examining the features of the velocity distribution and the static pressure distribution of oil on a low-velocity piston are as follow. The compression speed of oil passing through an 0.9 mm orifice was 0.0156~0.0642 m/s, and the velocity vector of the velocity distribution and the static pressure distribution had a greater tendency to rotate when the velocity increased. In case of the velocity vector of the velocity distribution and the static pressure distribution with an 0.8mm orifice, the speed changed secondarily, the second pressure-drop was observed and as for the distribution of the streamline around the orifice, a vortex was produced around the center. As for the velocity distribution of oil passing from the compression cylinder to the compact pipe, the velocity was greater in orifice of small diameter. Also, the greater the pressure difference was between the compression cylinder and the compact cylinder, the greater the force it was upon the piston.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.17 no.4
• /
• pp.81-88
• /
• 2013

It was designed and tested at the design point that an oxidizer rich preburner for a staged combustion liquid rocket engine propelled by kerosene and LOx. The oxidizer rich preburner was designed as some of LOx injected from the mixing head was burned with kerosene and the rest of LOx injected from injection holes in the regenerative cooling chamber was vaporized by combustion gas. The preburner is operated at OF ratio of 60 and combustion pressure of 20 MPa. The Preburner has a honey-comb type mixing head with simplex swirl injectors, a turbulence ring improving combustion stability and uniformity of product gas temperature distribution, and a nozzle simulating the duct. With the combustion test results at the design point, the oxidizer rich preburner showed high combustion stability and uniformity of product gas temperature distribution.

• Proceedings of the Computational Structural Engineering Institute Conference
• /
• 2009.04a
• /
• pp.421-424
• /
• 2009

사장교 케이블의 감쇠비를 추정하기 위하여 실교량 계측을 수행하였다. 사장교 케이블은 감쇠비가 낮고, 고유 진동수가 케이블의 길이에 따라 넓은 범위에 걸쳐 분포하므로, 바람이나 지점 가진에 의하여 과도한 진동이 발생될 수 있다. 케이블 진동 현상의 원인과 발생되고 진행되는 구조는 다양하나, 진동 현상의 가장 중요한 요소는 감쇠비이며, 케이블 진동의 과도한 진동을 감소시키기 위하여, 케이블의 감쇠비를 증가시키는 방법이 널리 사용되고 있다. 사장교 케이블의 다양한 진동 현상에 대한 발생 여부를 판단하고, 케이블 댐퍼와 같은 여러 제진 대책을 설계하고, 설치된 케이블 제진 대책의 성능을 검증하기 위해서는, 케이블의 감쇠비를 추정하는 것이 매우 중요하다. 일반적으로 사용되어져 온 케이블의 감쇠비 추정 방법은 정해진 모드로 자유 진동을 발생시킨 후, 진폭의 감소 추세로부터 Logarithmic Decrement를 계산하여 감쇠비를 구하는 방법이다. 그러나 수백m에 이르는 긴 케이블에서 정해진 모드의 자유 진동을 발생시키는 것은 쉽지 않다. 최근에는 상시 진동으로부터 감쇠비를 추정하는 여러 기법들이 개발되어져 왔으며, Frequency Domain Decomposition Method나 Stochastic Subspace Identification Method 등이 많이 사용되고 있다. 이 논문에서는, 상시진동 기반의 기법들을 사용하여, 사장교 케이블의 감쇠비를 추정하였으며, 추정된 감쇠비의 신뢰도를 높이기 위해, 측정시간을 늘리고, 가진 풍하중의 영향을 반영하여 보정하였다. 또한 추정된 감쇠비를 Buffeting 진동과 와류 진동과 같이 진동 현상과 진폭별로 분석하였다.

• Journal of the Korean Society of Combustion
• /
• v.22 no.3
• /
• pp.29-34
• /
• 2017

The multi-environment probability density function model has been applied to simulate a turbulent premixed flame in a swirl combustor. To realistically account for the unsteady flow motion inside the combustor, the formulations are derived for the large eddy simulation. The Flamelet generated manifolds is utilized to simplify a multi-dimensional composition space with reasonable accuracy. The sub grid scale mixing is modeled by the interaction by exchange with the mean mixing model. To validate the present approach, the simulation results are compared with experimental data in terms of mean velocity, temperature, and species mass fractions.

• Bulletin of the Society of Naval Architects of Korea
• /
• v.30 no.2
• /
• pp.8-10
• /
• 1993

선박에너지 개발을 위한 미래의 유력한 추진체로서 초전도 자력장을 이용한 선박을 들 수 있는데 이와 같은 경우에는 실험을 하기에는 비용이 엄청나게 소요되고 설비 자체가 복잡하기 때문에 CFD를 이용해서 초기 계\ulcorner을 구상하고 선체 주위의 유동장의 제어 및 기초 설계를 하여야 할 것이다. CFD계산을 통해 일반적으로 얻을 수 있는 것은 -압력 분포 -자유 표면 파고 -유속 분포 -유선 추적 -선체 표면의 응력 분포 -한계 유선 분포 -선미 와류 생성 과정 -선체 저항 계산 등으로 선형 개발에 필요한 기본 자료들이다. 여기서 CFD의 유용가치를 강조할 수 있는데 위의 많은 데이터를 실험을 통해서 얻으려면 막대한 경비와 노력이 투입되어야 한다. 또한 현재의 실험 시설로는 정량적으로 측정할 수 없는 부분도 일부 있다. CFD의 경우는 그러한 어려움은 없으나 꼭 필요한 것이 수치계산의 검증이다. 계산 결과의 유효성(validity)을 검증해야 한다는 의미이다. 계산은 실험을 통하여 반드시 비교 검토가 이루어져야 하며 이의 수단으로 선박 분 야에서는 Wigley 모형이나 Series 60와 같은 것들이 사용되고 잇다. 당 연구소의 저항추진연구 실에서는 CFD의 연구가 수년 전부터 소수의 인원을 중심으로 이루어져 왔다. 이와 관련하여 대표적인 몇 가지만 소개하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.614-615
• /
• 2010

The propellants distribution of an oxidizer rich preburner was predicted by a simplified physical approach. The Mixing head is composed of honeycomb array of 7 fuel injectors and 24 oxidizer injectors. The OF ratio of the mixing head is 15. As results, the OF ratio of the central area is about 9 and the OF ratio of the wall area is about 30.

• Proceedings of the KIEE Conference
• /
• 1996.11a
• /
• pp.471-474
• /
• 1996

The effects of injection angles between $0^{\circ}$ and $9^{\circ}$, mainstream turbulent intensities between 0.36 percent and 9.3 percent and embedded longitudinal vortices on jets issuing from a single film cooling hole and from a row of inclined holes are investigated. The heat transfer coefficients around film cooling holes are affected greatly by the compound injection angles. The injected jets affected weakly by the freestream turbulence at low level. However, the heat transfer coefficients near the film cooling holes have higher values at a high turbulence intensity. The vortices generated from a delta winglet change the injected jet direction and the kidney-type vortex pattern.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.04a
• /
• pp.69-72
• /
• 2011

Hot-firing tests were performed on the third sub-scale gas generator for development of a 75 ton-class liquid rocket engine. This paper deals with the analysis results of low-frequency combustion instabilities that were encountered during combustion tests of the gas generator. The low-frequency pressure fluctuations seem to be related to chamber pressure and pressure drops through oxidizer/fuel injectors.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.15 no.6
• /
• pp.3403-3409
• /
• 2014

Hot-firing tests were carried out using a mixing head with 19 swirl coaxial injectors and a combustion chamber with internal cooling channels. The propellants of liquid oxygen and kerosene(Jet A-1) were burned in a range of chamber pressures (59~82 bar) and mixture ratios (2.0~3.0). The temperature of water used as the cooling fluid was measured at the inlet and outlet of the cooling channels, and the heat flux was calculated. The aim of this study was to examine the effect of combustion instability on heat transfer in a subscale thrust chamber, and detect the temperature variation of cooling water. During several hot-firing tests, combustion instability was encountered which caused a 5~20% increase in heat flux. The peak heat flux took place in the initial stages of combustion instability.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.8 no.2
• /
• pp.85-94
• /
• 2004

Experimental study on combustion characteristics of double swirl coaxial injectors has been conducted for the assessment of critical injector design parameters. A reusable, unielement thrust chamber has been fabricated with a water-cooled copper nozzle. Two principal design parameters. a swirl angle and a recess length, have been investigated through hot firing tests for the understanding of their effects on high pressure combustion. Clearly, both parameters considerably affect the combustion efficiency, dynamics and hydraulic characteristics of an injector. Internal mixing of propellants in a recess region increases combustion efficiency along with the increase of a pressure drop required for flowing the same amount of mass flow rates. It is concluded that pressure buildup due to flame can be released by the increase of LOx flow axial momentum or the reduction of a recess length. Dynamic pressure measurements of the thrust chamber show varied dynamic behaviors depending on injector configurations.