• Journal of Mechanical Science and Technology
• /
• 제16권5호
• /
• pp.732-742
• /
• 2002

This paper presents twin spray characteristics of two impinging F-O-O-F type injectors in which fuel and oxidizer impinge on each other to atomize under the various conditions. The droplet size and velocity in the impinging spray flow field were measured using PDPA. The droplet size and velocity were investigated at the mixture ratios of 1.5, 2.0, 2.47 and 3.0 for four injectors in which two single F-O-O-F injectors were arranged at the intervals of 20.8, 31.2, 41.6 and 62.4mm respectively. In general, the arithmetic mean diameter, SMD and standard deviation of droplet size in the interaction area (X=0 and Y=0mm) were smaller, while the axial velocity in the interaction area was slightly higher. An empirical correlation is obtained for the (D$\_$10/)$\_$D//(D$\_$10/)$\_$c/ value under the assumptions of two identical droplets and these with different size and velocity. The droplets with low Weber numbers below 40 have possibility to coalesce, while those over 40 tend to disintegrate after impingement in the interaction area.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2001년도 추계학술대회논문집B
• /
• pp.758-763
• /
• 2001

This paper presents twin spray characteristics of two impinging F-O-O-F type injectors in which fuel and oxidizer impinge on each other to atomize under the various conditions. The droplet size and velocity in the impinging spray flow field were measured using a PDPA. The droplet size and velocity were investigated at mixture ratios of 1.5, 2.0, 2.47 and 3.0 for four injectors in which two single F-O-O-F injectors were arranged at intervals of 20.8, 31.2, 41.6 and 62.4mm respectively. In general, the arithmetic mean diameter, SMD and standard deviation of droplet size in the interaction area (X=0 and Y=0mm) were smaller. The axial velocity in the interaction area was slightly higher. Considering the behavior of impinged droplets using the We number calculated by using the axial velocity instead of the relative velocity in line C in Fig. 1(b) for four injectors, it is consumed that the We number over 500 had the possibility to disintegrate, and the We number below 500 had it to cohere after impingement of twin spray. The results of this study can be used for the design of a nozzle for liquid propellant rockets.

• 한국분무공학회지
• /
• 제3권2호
• /
• pp.42-50
• /
• 1998

The effect of swirl flows un the fuel spray characteristics were investigated for various swillers in a model combustor. The interaction between the flow field and fuel spray in the main combustion tone made by frontal devices including fuel injection nozzles and swirlers. which were characterized by flow velocities, fuel droplet sizes and their distributions which were measured by APV(Adaptive Phase/Doppler Velocimetry) under atmospheric condition at 320cc/min kerosine fuel flow and 0.04kg/sec air supply. A dual swirler with circumferential two-stage swirl vanes of $40^{\circ}\;and\;45^{\circ}$ vanes in different directions and two single-stage swillers of $40^{\circ}$ vanes with 12 and 16 vanes were tested. It was found that the dual swirler has the largest recirculating zone with highest reverse flow velocity. The strongest swirl flow was found at the boundary of recirculation zone. Small fuel droplets were observed in the main axial stream and inside the recirculation zone when swirling flow field were generated by the frontal devices. These findings could give the tips on the optimal design of frontal devices to realize low emissions in gas turbine combustion.

• 한국연소학회:학술대회논문집
• /
• 한국연소학회 1998년도 제17회 KOSCI SYMPOSIUM 논문집
• /
• pp.9-21
• /
• 1998

The optimization of frontal device including fuel nozzle and swirler is required to secure the mixing of fuel and air, and the combustion stability in the gas turbine combustor design for the reduction of pollutant emissions and the increase of combustion efficiency. The effects of injection nozzle and swirler on the flow field, spray characteristics and consequently the combustion stability, were experimentally investigated by measuring the velocity field, droplet sizes of fuel spray, lean combustion limit and the temperature field in the main combustion region. The effect of fuel injection nozzle was tested by adopting three different nozzles; a dual orifice fuel nozzle, a hollow cone nozzle and a solid cone nozzle. These tests were combined with the three different swirler geometries; a dual-stage swirler with 40$^{\circ}$ /-4 5$^{\circ}$ vanes and two single-stage swirlers with 40$^{\circ}$ vane angle having 12 and 16vanes, respectively. Flow fields and spray characteristics were measured with APV(Adaptive Phase Doppler Velocimetry) under atmospheric condition using kerosine fuel. Temperatures were measured by Pt-PtI3%Rh, R-type thermocouple which was 0.2mm thick. It was found that the dual swirler resulted in the biggest recirculation zone with the highest reverse flow velocity at the central region, which lead the most stable combustion. The various combustion characteristics were observed as a function of the combination between the injector and swirler, that gave a tip for the better design of gas turbine combustor.

• 한국화재소방학회논문지
• /
• 제13권1호
• /
• pp.37-47
• /
• 1999

부유중인 분진의 화재 및 용기 또는 파이프의 미세한 균열에서 비산되는 가연성 액체의 분무화재의 위험성은 착화후의 고속 확산과 높은 열방출율로 인하여 매우 높은 것으로 알려졌다. 이에 대한 연구는 주로 실험적으로나 또는 거시적인 관점의 해석으로 제한되어 왔다. 본 연구는 미시적인 관점의 해석으로서 분진 및 분무를 가연성 미세 액적으로 가정하여 그의 증발과 착화에 대하여 연구하였다. 첫 단계로서 일열의 액적 배열을 계산영역으로 하여, 비정상 이차원 보존방정식들을 적용하였다. 수치해석은 일반화된 비직교 좌표계를 사용하였고, 화학반응은 Arrhenius의 법칙에 의하여 반응속도가 제어되는 일단계 반응을 고려하였다. 계산결과는 액적 주위의 온도와 반응물질의 농도분포를 시간에 따라 보여준다. 주위의 산소가 증발하는 액적의 연료와 섞이기 시작하고 착화 조건에 다다르면, 급격한 발열반응이 예혼합된 가스로부터 일어나기 시작한다. 최대온도 영역은 점차적으로 액적 표면으로 이동하며 최대온도는 착화이후 급격히 상승한다. 연료와 산소의 농도는 최대온도 영역 근처에서 최소값을 보인다. 따라서 착화순간에는 예혼합연소의 양상을 띠는 것으로 나타났다. 이후에는 예혼합 가스의 소멸로 확산연소의 양상을 띠게 된다. 액적간의 거리는 중요한 요소로서 멀리 떨어져 있는 경우부터 액적간의 거리가 가까워지면 착화지연 시간이 줄여들어 착화가 빨리 일어나는 것으로 관찰되었다. 또한 착화 후에는 최대온도 영역이 일열의 중심선으로부터 멀어지는 것으로 나타났는데 이것은 중심부근의 산소가 먼저 소모되고 외부로부터의 산소공급도 화염에 의해 차단되어 나타나는 현상이다. 이번 연구로 미세적인 착화현상에 대한 이해를 높이게 되었고 추후 복잡한 배열에 대한 연구도 가능할 것이다.

• 한국자동차공학회논문집
• /
• 제21권3호
• /
• pp.74-81
• /
• 2013

Due to its accuracy and efficiency, reduced kinetic mechanism of diesel surrogate is widely used as fuel model when applying 3-D diesel engine simulation. But for the well-developed prediction of diesel surrogate reduced kinetic mechanism, it is important to know some meaningful factors which affect to ignition delay time. Meanwhile, ignition delay time consists of two parts. One is the chemical ignition delay time related with the chemical reaction, and the other is the physical ignition delay time which is affected by physical behavior of the fuel droplet. Especially for chemical ignition delay time, chemical properties of each fuel were studied for a long time, but researches on their mixtures have not been done widely. So it is necessary to understand the chemical characteristics of their mixtures for more precise and detailed modeling of surrogate diesel oil. And it shows same ignition trend of paraffin mixture with those of single component, and shorter ignition delay at low/high initial temperature when mixing paraffin and toluene.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2009년도 춘계학술대회 논문집
• /
• pp.233-236
• /
• 2009

산화제는 $LN_2O$, 고체연료는 HDPE(High Density PolyEthlene)를 사용하여 산화제의 상 및 연료포트 직경에 따른 하이브리드 로켓 모터의 연소특성을 비교 분석하였다. 불완전한 액적의 기화와 연료와 산화제의 혼합으로 인해 산화제로 $GN_2O$ 보다 $LN_2O$를 적용했을 때, 연소효율이 낮게 나타났다. O/F비에 따른 화염온도변화 및 끝 단면적에서의 연소반응으로 인해 $LN_2O$와 $GN_2O$를 사용하였을 경우 고체연료의 초기 포트 직경에 따른 후퇴율의 경향이 달리 나타났다.