• Journal of ILASS-Korea
• /
• v.17 no.3
• /
• pp.128-133
• /
• 2012

The present study aims to examine the influence of flame spray distance on the thermal behavior of micro-metal particles and the morphological characteristics of $Ni_{20}Cr$ layers coated on the preheated SCM415 substrates by using the conventional flame spray system. Commercially available nickel-based $Ni_{20}Cr$ particles with a mean diameter of $45{\mu}m$ were used. In addition, CFD simulations using a commercial code (FLUENT ver. 6.3.26) were conducted to estimate temperature and velocity distributions of the continuous and discrete phases before impact on the substrate. From FE-SEM images of coated layers on the substrates, it was observed that as the spray distance decreased, the metal particle morphology showed splash-like patterns and such a short stretch shape, resulting from higher particle momentums and the impact of partially melted particles. Moreover, it was found that the spray distance should be considered as one of important parameters in controlling the porosity and the adhesion strength.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.3
• /
• pp.222-229
• /
• 2012

The cooling of a injector effects on the vapor pressure of cryogenic oxidizer spray, and it decides the phase transition point at the ignition process, when the combustion chamber pressure increases drastically. The phase transition of oxidizer spray affects the ignition characteristics, and several ignition tests with the LOx/$GCH_4$ uni-element coaxial swirl injector was performed in the different initial temperatures of oxidizer injector, in order to investigate the effect of injector cooling on the ignition transient characteristics. At the transition point of oxidizer phase, where the combustion chamber pressure increased over the LOx vapor pressure, the temporary quenching phenomenon of the flame occurred. The lower temperature of chilled down injector and tubing tends to move up the phase transition earlier.

• Fire Science and Engineering
• /
• v.20 no.4 s.64
• /
• pp.135-142
• /
• 2006

The experiment applied Positive Pressure Ventilation to rapidly exhaust heat and smoke inside the construction in the fire was done. Changes of heat discharge and smoke density were measured, with the various blowing condition like a fan tilting angle to find the effect of the parameter. Experimental apparatus were with PPV and water mist system for better efficiency, and investigate the effect of heat discharge and smoke removal. In the experiment, flame temperature has decreased when PPV was applied. Smoke density, generated from fire also decreased dramatically and the efficiency showed the highest rate at $0^{\circ}$ tilting angle. In addition, combination of PPV and water mist system highly improved the efficiency of evacuation on heat and smoke density, clearly was influenced by the tilting angle.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.12 no.1
• /
• pp.29-36
• /
• 2008

Spray characteristics for APU gas turbine engine are investigated. In the test, four flight conditions such as sea level idle, sea level max power, 20,000 feet idle, 20,000 feet max power are used as spray experimental conditions. Spray visualization was performed by using ND-YAG laser bean PDPA(Phase Doppler Particle Analyzer) was used for measuring the particle diameter and velocity from 20 mm to 100 mm from discharge orifice. From the test result, SMD is $90{\sim}95\;{\mu}m$ 맛 20,000 ft idle condition and SMD is $60{\sim}75\;{\mu}m$ at sea level idle condition. Also SMD is $55{\sim}65\;{\mu}m$ at 20,000 ft max power condition and SMD is $30{\sim}70\;{\mu}m$ at sea level max power condition. In the case of 20,000 ft idle condition, combustion instability could be occurred due to the higher drop diameter. Therefore it is necessary to decrease the droplet diameter in the high altitude condition.

• Journal of Ocean Engineering and Technology
• /
• v.10 no.4
• /
• pp.128-140
• /
• 1996

To analyze a formation process of the soots in spray flame in the combustion chamber, an optically accessible DI Diesel engine was used for visualization. The images of the flames and soots were visualiaed with high speed camera by Schlieren method and Light extinction method. The spray flame and soot images on the films were analyzed at the various engine operating conditions. Soot distributed widely in spray flame and its concentration was about $100g/m^3$ at the position close by nozzle tip of spray flame region, however it decreased below $20g/m^3$ at the corner of combustion chamber due to soot oxidation.

• 한국가시화정보학회:학술대회논문집
• /
• 2005.04a
• /
• pp.3-57
• /
• 2005

왕복동 내연기관에서의 연소 및 배기가스 생성은 복잡한 3차원 영역 내에서 난류 유동, 분무, 화학반응, 열전달, 경계층 현상이 상호 연계되어 있는 매우 복합적인 과정이다. 특히 난류 연소 현상은 기관의 효율을 결정하는 연소 속도와 pollutant의 배출 농도를 결정하는 핵심 요소로서 관련 모델과 수치 해법에 대해 학술적, 공학적 측면에서 세계적으로 활발한 연구가 이루어지고 있다. 이를 위해 수행되는 다양한 실험 측정과 수치 해법을 통해 얻어지는 3차원 과도 상태의 방대한 스칼라량과 벡터량에 대한 정보를 효율적으로 처리하기 위해서는 적절한 가시화 과정이 필수적이다. 여기서는 최근 다양한 엔진 타입들에 대한 응용 사례와 함께 난류 연소 모델링을 위한 새로운 접근법으로서 조건평균법(conditional averaging)에 대해 간략히 소개하고자 한다. 난류예혼합연소에서의 난류화염속도에 대한 DNS와 영역조건평균에 기초한 예측식의 검증, 천연가스 jet의 자발화 지연기간, n-heptane jet의 자발화 진행 과정, HSDI 엔진, HCCI 엔진, CNG 엔진, LPG 분무 및 엔진, GDI 엔진 등에 대한 연구 결과들은 정보 가시화의 한 사례가 될 수 있을 것으로 생각된다.

• Journal of ILASS-Korea
• /
• v.6 no.3
• /
• pp.1-7
• /
• 2001

In this study, quantitative measurement of nitric oxide concentration distributions visualization were investigated in the laminar $CH_4/O_2N_2$ nixed flame by Planar laser-induced fluorescence(PLIF). The NO A-X (0,0) vibrational band around 226nm was excited using a XeCl excimer-pumped dye laser. Selecting an appropriate NO transition minimizes interference from Rayleigh scattering and $O_2$ fluorescence. The measurements were taken in $CH_4/O_2N_2$ premixed flame with equivalence ratios varying from $1.0{\sim}1.6$, and a fixed flow rate of 3slpm. NO was found to produce primarily between an inner premixed and an outer nonpremixed flame front, and total NO concentration is raised when equivalence ratios increase. These results suggest that prompt NO is likely to contribute to MO formation in $CH_4/O_2N_2$ premixed flame. Furthermore, this trend was well matched with previous works.

• Journal of ILASS-Korea
• /
• v.6 no.3
• /
• pp.8-16
• /
• 2001

The present study is focused on modeling the transient behavior of the local flame structure which is especially important for slow reaction processes, such as NOx formation in the radiating flame field. The unsteady flamelet model recently developed has been applied to analyze a steady, turbulent jet flame. Numerical results are compared with experimental data and numerical results of the conventional steady flamelet model. The numerical result reveals that the unsteady flamelet model correctly predicts the nonequilibrium effect upsteam and the subsequent decay of the superequilibrium radical concentrations further downstream.

• Journal of ILASS-Korea
• /
• v.3 no.1
• /
• pp.10-18
• /
• 1998

To investigate the in-cylinder phenomena in a SI engine with 3 valves and pent-roof type combustion chamber, flow fields, fuel distributions, and flame propagations were measured in a single c!'tinder visualized engine. Flow fields were visualized by PTV system during the intake and compression process. Fuel distributions were measured by PLIF at the various engine conditions including the cold and hot engine conditions and the effect of air-shrouded injector on the fuel distribution was investigated also. In addition, flame propagation patterns were characterized.

• Journal of ILASS-Korea
• /
• v.15 no.4
• /
• pp.189-194
• /
• 2010

This study has been mainly motivated to numerically model the transcritical mixing and reacting flow processes encountered in the liquid propellant rocket engines. In the present approach, turbulence is represented by the extended k-$\varepsilon$ turbulence model. To account for the real fluid effects, the propellant mixture properties are calculated by using SRK (Souve-Redlich-Kwong) equation of state model. In order to realistically represent the turbulence-chemistry interaction in the turbulent non-premixed flames, the flamelet approach based on the real fluid flamelet library has been adopted. Based on numerical results, the detailed discussions are made for the real fluid effects and the precise structure of the transcritical cryogenic liquid nitrogen jet and gaseous hydrogen/liquid oxygen coaxial jet flame.