• 대한기계학회논문집
• /
• 제13권4호
• /
• pp.618-624
• /
• 1989

본 연구의 목적은 낮은 포화 압력하에서의 초음파에 의한 미세포 포움 구조 획득의 가능성을 평가하기 위한 것으로, 이 초음파 가공을 고분자 포움의 연속적인 압출 가공에 적용하기 위한 기초 연구를 이론적 및 실험적으로 수행함에 있다.따라서 미세포구조의 획득이 본 연구의 목적은 아니며 초음파를 이용한 열가소성 수지내의 핵생성 거동에 대한 고찰을 하고자 한다.

• 대한기계학회논문집B
• /
• 제39권1호
• /
• pp.37-43
• /
• 2015

현열 뿐만 아니라 잠열을 이용하는 증발냉각은 배기열 회수에 매우 유용하게 사용될 수 있다. 본 연구의 목적은 증발냉각을 이용한 배기열 회수장치의 성능을 실험적으로 규명하는 것이다. 성능실험장치는 플라스틱 열교환기, 물 분무 노즐, 공기유동용 홴, 물 순환용 펌프, 수조, 온도 습도 유량 측정 센서 등으로 구성되었다. 증발이 없는 현열 회수에서의 유용도와 증발을 수반하는 전열 회수에서의 유용도를 여러가지 작동조건에서 측정하여 비교하였다. 현열냉각과 증발냉각의 유용도는 공기의 유량이 증가함에 따라 감소하고, 대향류에서의 유용도가 평행류에서의 유용도 보다 휠씬 높다. 증발냉각의 경우 물 유량이 증가함에 따라 유용도는 증가하고, 평행류가 대향류보다 물 유량에 더 민감함을 알 수 있다.

• 한국추진공학회지
• /
• 제6권1호
• /
• pp.21-29
• /
• 2002

하이브리드 연소 시스템은 안정된 작동조건이나 안전성 면에서 많은 장점을 가지고 있는 반면 기존의 하이브리드 모터는 고체 추진 로켓모터보다 낮은 연료 regression율과 연소효율은 갖는 단점이 있다. 따라서 최근의 연구들은 하이브리드 로켓모터의 연소실 체적의 제한과 연료의 regression율을 향상시키는데 그 초점을 맞추고 있다. 본 연구는 하이브리드 로켓 엔진의 연소과정을 수치적으로 해석하였다. 난류연소는 eddy breakup 모델을 이용하였으며 soot의 생성 및 산화를 다루기 위하여 Hiroyasu와 Nagle and Strickland-Constable 모델을 적용하였다. 복사열전달은 유한체적법을 이용하여 계산하였으며 고체 연료 벽면에서의 분출 효과로 야기되는 대류열전달의 불확실성을 줄이기 위하여 낮은 레이놀즈 수 $\kappa-\varepsilon$ 난류모델을 적용하였다. 계산된 수치결과를 토대로 선회 유동을 가지는 하이브리드 로켓 엔진의 난류연소과정에 대하여 상세히 기술하였다.

• 유기물자원화
• /
• 제26권2호
• /
• pp.65-73
• /
• 2018

본 연구는 음식물쓰레기의 발효건조를 위한 최적 운전조건을 도출하기 위하여 0.75, 1.00, 1.25, $1.50L/min{\cdot}kg$의 송풍조건에서 발효건조 회분식 반응기를 20일간 운전하였으며, Modified Gompertz 모델을 이용하여 발효건조 기간 중 반응기내에서의 유기물 분해반응속도를 분석하였다. 유기물 분해 반응속도 분석에서 최대 유기물 분해량 (P)은 송풍량 0.75, 1.00, 1.25, $1.50L/min{\cdot}kg$에서 각각 2.31, 2.52, 2.27, 1.88 kg이었으며, 최대 유기물 분해속도 ($R_m$)는 송풍량 0.75, 1.00, 1.25, $1.50L/min{\cdot}kg$에서 각각 0.33, 0.45, 0.28, 0.18 kg/day를 보여 송풍량 $1.00L/min{\cdot}kg$에서 우수한 유기물 분해효율을 보였다. 발효건조 반응기의 지체성장시간 (${\lambda}$)은 송풍량 0.75, 1.00, 1.25, $1.50L/min{\cdot}kg$에서 각각 2.10, 1.48, 1.15, 1.06 일로 나타나 $0.75L/min{\cdot}kg$의 적은 송풍조건에서 가장 긴 지체성장시간을 보여 송풍량의 증가는 지체성장시간을 단축시키는 것으로 나타났다. 음식물쓰레기 발효건조 반응기의 운전에서 수분 제거율은 발효건조 반응기 운전 초기에서 중기로 갈수록 송풍량 증가와 함께 증가하다가 발효건조 반응기 운전 말기에는 송풍량 $1.00L/min{\cdot}kg$에서 가장 높은 수분 제거율을 보여 발효건조의 최적 송풍조건은 $1.00L/min{\cdot}kg$으로 나타났다.

• 한국유체기계학회 논문집
• /
• 제17권5호
• /
• pp.5-10
• /
• 2014

In this paper, the experimental study was carried to investigate the effect of angle of the anti-vortex holes on the film cooling effectiveness on a flat plate. The pressure sensitive paint technique was applied to measure the film cooling effectiveness. Two anti-vortex hole angles of $0^{\circ}$ and $15^{\circ}$ with respect to the primary hole were considered, and the simple cylindrical hole case was also tested. The blowing ratio based on the cylindrical hole was 0.5 and the same flow rate was kept for all anti-vortex hole cases. Results showed that the film cooling effectiveness for the anti-vortex hole cases were much higher than that of the cylindrical case. Among the anti-vortex hole cases, $15^{\circ}$ angle anti-vortex hole case showed higher film cooling effectiveness than that by the $0^{\circ}$ angle anti-vortex hole case.

• 대한기계학회논문집B
• /
• 제27권10호
• /
• pp.1472-1479
• /
• 2003

An attempt to reduce supersonic jet noise is carried out by using two steady microjets in a round jet. The jet is issued from a round sonic nozzle with an exit diameter of 10 mm. Two micro-nozzles with an inside diameter of 1 mm each are installed on the exit plane at an angle of 45 relative to the main jet axis. Far-field noise was measured at 40 diameters off the jet axis. The angle between a microphone and the jet axis is 30 or 90$^{\circ}$. For an injection rate of 4-6% of the main jet, screech tones were completely suppressed by the microjets. The reduction in the overall sound pressure levels were 2.4 and 2.7 dB for 90 and 30 measuring directions, respectively. However, the enhancement of mixing/spreading of the jet by the microjet was negligible. The reduction of noise is probably due to distorted shock cell structures and/or deformed large scale vortical structures by the microjets.

• International Journal of Safety
• /
• 제4권2호
• /
• pp.24-29
• /
• 2005

An experimental study was presented for extinguishing characteristics of liquid fuel fire by water mist($Dv_{0.99}{\leq}200{\mu}m$) containing potassium acetate and sodium acetate trihydrate. To evaluate the extinguishing performance of water mist containing additives, the evaporation characteristics of a water droplet on a heated surface was examined. The evaporation process was recorded by a charge-coupled-device camera. Also, small-scale extinguishing tests were conducted for n-heptane pool fire in ventilated space. During the experiments, flame temperatures were measured, and concentrations of oxygen and carbon monoxide were analyzed by a combustion gas analyzer. The average evaporation rate of water droplet containing additives was lower than that of pure water at a given surface temperature and decreased with the concentration increase due to the precipitation of salt in the liquid-film and change of surface tension. In case of using additives, the fire extinguishing times was shorter than that of pure water at a given discharge pressure and it was because the momentum of a water droplet containing additives was increased. And also dissociated metal atoms, potassium or sodium, were reacted as a scavenger of the major radical species OH, H which were generated for combustion process. Moreover, at a high pressure of 4 MPa, the fire was extinguished through blowing effect as well as primary extinguishing mechanisms.

• 한국안전학회지
• /
• 제17권2호
• /
• pp.39-44
• /
• 2002

This study was investigated the thermal decomposition characteristics of azo type sponge blowing agent azodicarbonamide(ADCA) using differential scanning calorimeter(DSC). The experimental results showed that the exothermic onset $temperatures(T_{o})$ for ADCA were about $201{\sim}206^{\circ}C$ and evolution heats(Q) were about $144{\sim}150cal/g$. The exothermic onset $temperatures(T_{o})$, exothermic maximum $temperature(T_{m})$ and exothermic final $temperature(T_{f})$ were decreased by decreasing particle size of ADCA and evolution heats(Q) were increased with it. $T_{o}$ and Q for $6.1{\sim}7.2{\mu}m$ ADCA were increased by increasing heating rate at constant sample weight and activation energy was about 37.29kcal/mol. A positive gas pressure was employed in the elucidation of the decomposition behavior of ADCA because it sublimes during linear heating at atmospheric pressure. $T_{o}$ and Q of ADCA tended to increase with a pressure in air or nitrogen. In the case of azo dye, experimental results showed that $T_{o}$ were about $280{\sim}420^{\circ}C$ and Q were about $2{\sim}30cal/g$.

• 한국유체기계학회 논문집
• /
• 제9권6호
• /
• pp.45-53
• /
• 2006

Turbo-blower as an air supply system is one of the most important BOP (Balance of Plant) systems for FCV(Fuel Cell Vehicle). For generating and blowing compressed air, the motor of air blower consumes maximum 25% of net power, and fuel cell demands a clean air. In this study, turbo-blower supported by air foil bearings is introduced as the air supply system used by 80kW proton exchange membrane fuel systems. The turbo-blower is a turbo machine which operates at high speed, so air foil bearings suit their purpose as bearing elements. Analysis for confirming the stability and endurance is conducted. The rotordynamic stability was predicted using the numerical analysis of air foil bearings and it is verified through experimental works. In spite of various transient dynamic situation, the turbo-blower had stable performances. After the performance test, results are presented. The normal power of driving motor has about 1.6 kW with the 30,000 rpm operating range and the flow rate of air has maximum 160 SCFM. The test results show that the aerodymic performance and stability of turbo-blower are satisfied to the primary goals.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2002년도 학술대회지
• /
• pp.747-750
• /
• 2002

An attempt to reduce supersonic Jet noise is carried out by using two steady microjets in a round jet. The jet is issued from a round sonic nozzle with an exit diameter of 10mm. Two micro-nozzles with an inside diameter of 1mm each are installed on the exit plane with an off-axis angle of $45^{\circ}$. Far-field noise was measured at a location 40 diameters off the jet axis. The angles between a microphone and the jet axis are $45^{\circ}\;and\;90^{\circ}$. For an injection rate less than $1{\%}$ of the main jet, screech tones were completely suppressed by the microjets. The reduction in the ovelall sound pressure levels were $2.4\;and\;2.7\;dB\;for\;90^{\circ}\;and\;45^{\circ}$ directions, respectively. The enhancement of mixing/spreading of the jet by the microjet was negligible. The reduction of noise is probably due to distorted shock cell structures and/or broken large scale vortical structures by the microjets.