• 청정기술
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• 제23권1호
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• pp.42-53
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• 2017

탈질과 탈황을 동시에 수행하는 과산화수소($H_2O_2$) 수용액 세정탑의 반응효율을 증가시키기 위해 예혼합이 이루어지는 혼합 냉각기(mixing quencher) 영역 내부의 유체유동에 대한 수치해석이 수행되었다. 산업공정에서 상용화되고 있는 세정탑 전단부의 혼합냉각기에서 과산화수소 수용액이 주입되는 노즐의 분사방식은 배기가스와 과산화수소 수용액의 혼합에 중요한 역할을 하며, 혼합냉각기에서의 혼합도는 세정탑 의 효율을 결정하는 중요 요소가 된다. 본 연구에서는 혼합냉각기 내부유체의 농도분포 개선을 목적으로 하여 혼합냉각기 내의 노즐 관의 배열을 조절하거나 노즐 팁 각도를 변경하며 유체혼합을 최적화하였다. 전산해석은 이 냉각기영역의 내부유동 및 각 유체 농도에 대한 RMS (root mean square) 값을 계산하여 내부유체의 혼합도의 개선을 확인하였다. 세부적으로는 노즐 관의 위치를 조절할 때 변경되는 냉각기 영역 후단의 농도 RMS 값을 확인하여 난류형성위치에 따른 최적화된 혼합도를 확인하였으며 기본형상 대비 난류형성방향을 조절하는 목적의 노즐 팁 각도를 증감하여 농도분포의 균질화를 비교하였다. 노즐 관의 배열에 따라 난류형성위치와 그에 따른 유체혼합이 해석되었다. 또한 노즐 팁 각도를 조절하는 경우에는 유동방향과의 각도에 따라, 흐름이 병류와 향류에 따라 혼합도의 최적화를 확인할 수 있었다. 노즐 관의 위치는 0.3 m, 노즐 팁은 병류의 $15^{\circ}$일 때 최적의 조건을 가지며 가장 낮은 RMS 값인 12.4%를 가졌다.

• 한국항공우주학회지
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• 제36권9호
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• pp.898-906
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• 2008

본 연구에 적용된 터빈은 2단으로 구성되며, 첫 번째 단에는 축류형 터빈이 적용되고 두 번째 단에는 반경류형 터빈이 적용되었다. 축류형 터빈에서 동익의 평균반경은 70mm 이며, 반경류형 터빈의 외경은 입구에서 68mm였다. 실험에서 반경류형 터빈의 경우에는 두 개의 다른 형태가 적용되었으며, 최적의 설계변수를 확인하기 위하여 노즐의 각도를 3가지로 변경하면서 실험을 수행하였다. 터빈의 형상에 따른 성능평가를 위하여 총비토오크를 기준으로 비교하였다. 실험의 결과에서 낮은 부분분사에서 작동하면서 고토오크를 얻기 위한 소형터빈의 성능에는 노즐 각도가 가장 중요한 설계변수임을 보여주었다. 부분분사율이 3.4%이면서 노즐의 분사각도가 $75^{\circ}$인 경우에 두 번째 단에 반경류형 터빈을 장착하였을 때 총비토오크는 13%향상하는 결과를 보여주었다.

• 한국표면공학회지
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• 제36권1호
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• pp.69-73
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• 2003

The atmospheric pressure plasma is regarded as an effective method for surface treatments because it can reduce the period of process and doesn't need expensive vacuum apparatus. The performance of non-transferred plasma torches is significantly depended on jet flow characteristics out of the nozzle. In order to produce the high performance of a torch, the maximum discharge velocity near an annular gap in the torch should be maintained. Also, the compulsory swirl is being produced to gain the shape that can concentrate the plasma at the center of gas flow. In this work, the distribution of gas flow that goes out to atmosphere through a plenum chamber and nozzle is analyzed to evaluate the performance of atmospheric pressure plasma torch which can present the optimum design of the torch. Numerical analysis is carried out with various angles of an inlet flow velocity. Especially, three-dimensional model of the torch is investigated to estimate swirl effect. We also investigate the stabilization of plasma distribution. For analyzing the swirl in the plenum chamber and the flow distribution, FVM (finite volume method) and SIMPLE algorithm are used for solving the governing equations. The standard k-model is used for simulating the turbulence.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.357-364
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• 2004

A computational study on the supersonic flow around the lateral jet controlled missile has been performed. Case studies have been performed by comparing the normal force coefficient and the moment coefficient of a missile body for several different jet flow conditions, angle of attacks, circumferential jet locations, and spouting jet angles. For the several different jet flow conditions, which include the jet pressure, the jet Mach number, and the corresponding jet mass flow rate, the results show that the normal force coefficient is almost proportional to the jet thrust but the moment coefficient is not. Distinctly different flow phenomena can be noticed as the pressure ratio and the jet Mach number increase. By investigating the angle of attack effect to the normal force and the pitching moment, it has been identified that the normal force and the pitching moment show nonlinearity with respect to the angle of attack. From the detailed flow field analyses with respect to the jet flow conditions and the angle of attacks, it is verified that most of the normal force loss and the pitching moment generation are taken place at the low-pressure region behind the jet nozzle. Furthermore, the normal force and the pitching moment characteristics of the missile have been identified by comparing different circumferential jet locations and spouting jet angles.

• Journal of Mechanical Science and Technology
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• 제14권4호
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• pp.456-465
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• 2000

An experiment was conducted to investigate the aerodynamic losses of high pressure steam turbine nozzle (526A) subjected to a large range of incident angles ($-34^{\circ}\;to\;26^{\circ}$) and exit Mach numbers (0.6 and 1.15). Measurements included downstream Pitot probe traverses, upstream total pressure, and end wall static pressures. Flow visualization techniques such as shadowgraph and color oil flow visualization were performed to complement the measured data. When the exit Mach number for nozzles increased from 0.9 to 1.1 the total pressure loss coefficient increased by a factor of 7 as compared to the total pressure losses measured at subsonic conditions ($M_2<0.9$). For the range of incidence tested, the effect of flow incidence on the total pressure losses is less pronounced. Based on the shadowgraphs taken during the experiment, it' s believed that the large increase in losses at transonic conditions is due to strong shock/ boundary layer interaction that may lead to flow separation on the blade suction surface.

• 한국자동차공학회논문집
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• 제22권1호
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• pp.183-192
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• 2014

In this work, the mixture formation and atomization characteristics of biodiesel fuel were reviewed under various test conditions for the optimization of compression-ignition engine fueled with biodiesel. To achieve these, the effect of nozzle caviting flow, group-hole nozzle geometry and injection strategies on the injection rate, spray evolution and atomization characteristics of biodiesel were studied by using spray characteristics measuring system. At the same time, the fuel heating system was installed to obtain the effect of fuel temperature on the biodiesel fuel atomization. It was revealed that cavitation in the nozzle orifice promoted the atomization performance of biodiesel. The group-hole nozzle geometry and split injection strategies couldn't improve it, however, the different orifice angles which were diverged and converged angle of a group-hole nozzle enhanced the biodiesel atomization. It was also observed that the increase of fuel temperature induced the quick evaporation of biodiesel fuel droplet.

• 대한기계학회논문집
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• 제13권3호
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• pp.547-553
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• 1989

본 연구에서는 작동유체로서 수증기와 거동이 유사한 습공기를 대기 흡입식 풍동을 사용하여 원호 노즐로서 팽창시키는 경우에 대하여 응축충격파가 발생하는 흐름이 측정부내에 쐐기를 설치하여 발생시킨 경사충격파에 미치는 영향에 대해 실험적으로 조사하였다.

• Advances in aircraft and spacecraft science
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• 제3권4호
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• pp.367-378
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• 2016

Thrust Vectoring is a dynamic feature that offers many benefits in terms of maneuverability and control effectiveness. Thrust vectoring capabilities make the satisfaction of take-off and landing requirements easier. Moreover, it can be a valuable control effector at low dynamic pressures, where traditional aerodynamic controls are less effective. A numerical investigation of Fluidic Thrust Vectoring (FTV) is completed to evaluate the use of fluidic injection to manipulate flow separation and cause thrust vectoring of the primary jet thrust. The methodology presented is general and can be used to study different techniques of fluidic thrust vectoring like shock-vector control, sonic-plane skewing and counterflow methods. For validation purposes the method will focus on the dual-throat nozzle concept. Internal nozzle performances and thrust vector angles were computed for several range of nozzle pressure ratios and fluidic injection flow rate. The numerical results obtained are compared with the analogues experimental data reported in the scientific literature. The model is integrated using a finite volume discretization of the compressible URANS equations coupled with a Spalart-Allmaras turbulence model. Second order accuracy in space and time is achieved using an ENO scheme.

• 한국공작기계학회논문집
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• 제17권4호
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• pp.89-94
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• 2008

Differential pressure flow meters which have a shape of triangular separate bar(TSB) were tested for investigating the flow rate characteristics of the flow meters with varying the temperature of the gas flow. Three kinds of the triangular separate bar flow meters whose aerodynamic angles are different one another are used. The mass flow rate of the flow meters are evaluated using a non-dimensional parameter which includes the gas temperature, exhaust gas pressure and differential pressure at the flow meters, and atmospheric pressure. A burner system which is similar to gas turbine was used for raising the gas flow temperature. The burner system was operated with varying the air/fuel ratio by controlling both the fuel injection rate from the fuel nozzle and air flow rate from a blower. An empirical correlation between the mass flow rate at the TSB flow meter and the non-dimensional parameter was obtained. The empirical correlation showed linear relationship between the mass flow rate and the non-dimensional parameter H. Also, the mass flow rate characteristics at the TSB flow meter was affected by the gas temperature.

• 한국정밀공학회지
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• 제14권3호
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• pp.21-27
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• 1997

This paper aims to clarify the effects of grinding conditions in form grinding of Sr-ferrite with the electro-plated diamond wheel. The main conclusions obtained were as follows. (1) The flexural strength and surface roughness of ferrite became the best at the peripheral wheel speed of 1700 m/min. (2) In the case of the depth of cut larger than 0.4mm, crack layers is induced in the ground surface, and the fracture type of chips exhibits slight ductile mode in the depth of cut smaller than 0.2mm. (3) Whe the depth of cut exceeds 0.6mm, the wheel life becomes extremely severe due to the large chipping and brack- age in the diamond grains. However, at the depth of cut .leq. 0.05mm, the diamond grain shows abrasive wear. (4) The decrease of flexural strength and the increase of surface roughness is in proportion to the increase of the feed rate. (5) Most effective nozzle setting angles with various delivery conditions of the grinding fluid, such as nozzle position .PHI. , flow rate Q, etc., were made clear.