• 대한기계학회논문집B
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• 제28권4호
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• pp.475-485
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• 2004

This paper was studied to investigate and compare the effects of inclined baffle plate on the turbulent flow characteristics of a gun-type gas burner through X-Y plane and Y-Z plane respectively by using X-probe from hot-wire anemometer system. For this purpose, two burner models with a cone-type baffle plate and a flat-type one respectively were used. The fast jet flow spurted from slits plays a role such as an air-curtain because it encircles rotational flow by swirl vanes and drives mixed main flow to axial direction regardless of the inclination of baffle plate. The inclined baffle plate causes axial mean velocity component and turbulent intensities etc. to be greatly concentrated towards the central part of a burner, and its effect especially appears in the range of about X/R=1.0-2.0. Also, it gives much larger size to axial mean velocity component and turbulent intensities etc formed near the slits in the range of X/R=1.4103. Especially the inclined baffle plate shifts more the Reynolds shear stress uw to the central region of a burner(Y/R=${\pm}$0.75) than the flat-type one, moreover it develops more strongly than uv.

• 한국공간구조학회논문집
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• 제6권1호
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• pp.111-115
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• 2006

방풍팬스의 설치에 의한 저층건물 주변의 풍압특성을 분석하기 위하여 풍압실험을 실시하였다. 방풍팬스의 다공율은 0%와 20%을 중심으로 하였다. 방풍팬스와 저층건물의 거리는 1H-9H까지 범위안에서 측정을 하였다. 사용된 풍속은 6m/s로 일정하게 하였다. 저층건물의 측압공 위치는 정면과 측면 후면을 중심으로 총 54개를 측정하였다. 분석결과 다공률 20%일때는 측정거리 1H-3H일 때 다공률 40%일 때는 측정거리 4H-6H일 때 가장 효과적이었다.

• 대한기계학회논문집B
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• 제27권4호
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• pp.466-475
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• 2003

The gun-type gas burner adopted in this study is generally composed of eight slits and swirl vanes. Thus, this paper is studied to investigate the effect of slits and swirl vanes on the turbulent flow fields in the horizontal plane of gas swirl burner with a cone type baffle plate measured by using X-probe from hot-wire anemometer system. This experiment is carried out at flow rate 450 $\ell$/min in the test section of subsonic wind tunnel. The axial mean velocity component in the case of burner model with only swirl vanes shows the characteristic that spreads more remarkably toward the radial direction than axial one, it does, however, directly opposite tendency in the case of burner model with only slits. Consequently. both slits and swirl vanes composing of gun-type gas burner play an important role in decrease of the speed near slits and increase of the flow speed in the central part of a burner because the biggest speed spurted from slits encircles rotational flow by swirl vanes and it drives main flow toward the axial direction. Moreover, the turbulent intensities and turbulent kinetic energy of gun-type gas burner are distributed with a fairly bigger size within X/R<0.6410 than burner models which have only slits or swirl vanes because the rotational flow by swirl vanes and the fast jet flow by slits increase flow mixing, diffusion, and mean velocity gradient effectively.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.341-346
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• 2001

The gun-type gas burner adopted in this study is generally composed of some slits and swirl vanes. Therefore, this paper is studied to investigate the effect of slits and swirl vanes on the turbulent flow fields in the horizontal plane of gas swirl burner with a cone type baffle plate measured by using X-probe from hot-wire anemometer system. This experiment is carried out at flow rate $450\;{\ell}/min$, which is equivalent to the combustion air flow rate necessary for heat release 15,000 kcal/hr in gas furnace, in the test section of subsonic wind tunnel. When the burner has only swirl vanes, the axial mean velocity component shows the characteristic that spreads more remarkably toward radial direction than axial one, but when it has only slits, that is developed spreading more toward axial direction than radial one. Therefore, because the biggest speed is spurted in slits and it derive main flow toward axial direction encircling rotational flow that comes out from swirl vane that is situated on the inside of slits, both slits and swirl vanes composing of cone type gas burner act role that decreases the speed near slits and increases the flow speed in the central part of a burner. Moreover, because rotational flow by swirl vanes and fast jet flow by slits increase turbulent intensities effectively coexisting, the turbulent kinetic energy is distributed with a bigger size fairly near slits than burner models which have only slit or swirl vanes within X/R<0.6410.

• 동력기계공학회지
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• 제5권2호
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• pp.22-29
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• 2001

This paper represents axial mean velocity, turbulent kinetic energy and swirl number based on momentum flux measured in the X-Y plane and Y-Z plane respectively of a cone type gas swirl burner by using X-probe from the hot-wire anemometer system. This experiment is carried out at flow rates 350 and $450{\ell}/min$ respectively, which are equivalent to the combustion air flow rate necessary for heat release 15,000 kcal/hr in gas furnace, in the test section of a subsonic wind tunnel. Axial mean velocities and turbulent kinetic energies show that their maximum values exist centering around narrow slits situated radially on the edge of and in the forefront of a burner until $X/R{\fallingdotseq}1.5$, but they have a peculiar shape like a starfish diffusing and developing into inward and outward of a burner by means of the mixing between flows ejected from narrow slits, an inclination baffle plate and swirl vanes respectively according to downstream regions. Moreover, they show a relatively large value in the inner region of 0.5$S_m$ obtained by integration of velocity profiles shows a characteristic that has an inflection point composing of the maximum and minimum value until X/R<3, but shows close agreement with the geometric swirl number after a distance of X/R=3.

• 한국항공우주학회지
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• 제45권2호
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• pp.85-91
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• 2017

본 연구에서는 NREL 5 MW 해상풍력터빈 모형의 후류 유동장 분석을 위해 1/86 축소모형을 사용한 실험적 연구를 수행하였다. 정격출력 속도 11.4 m/s와 회전수 1,045 rpm 조건에서 열선풍속계를 사용하여 반경의 6배까지 후류에서 속도 결핍 및 난류도 변화를 측정하는 풍동시험을 수행하였다. 그 결과 풍력터빈의 후류에서의 속도결핍은 횡방향과 수직 방향으로는 반경의 2배 이내에서 회복됨을 볼 수 있었으며, 끝단 와류에 의한 영향은 반경의 5배 이후에는 나타나지 않음을 볼 수 있었다. 또한, 후류의 난류도는 블레이드 끝단 부근에서 크게 나타나며 길이방향으로 반경 거리까지는 급격한 감소가 일어나지만 이 이후부터 반경의 6배까지 유지되었다.

• 한국항공우주학회지
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• 제33권1호
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• pp.48-53
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• 2005

본 연구의 목적은 기계적인 전단층 자극방법을 이용 스월제트 혼합향상의 가능성을 고찰함에 있다. 이를 위해 기계적 자극장치가 설계, 제작되었다. 주요 구성품으로는 두개의 아음속 노즐, 스월 발생기, 그리고 유동 자극기 등이다. 실험은 다음과 같은 다양한 헬리컬 모드들에서 수행되었다; m=+0, m=$\pm$1, m=$\pm$2, m=$\pm$3, m=$\pm$4. 열선유속계를 이용한 plane 파동과 헬리컬 파동 자극에 따른 제트속도 측정이 이루어 졌다. 다양한 헬리컬 모드에서의 결과 값들이 기준 값(plane-wave)과 비교되었다. 획득된 결과는 3-D mesh plot 과 2-D contour plot으로 표현되었다. 이로써 새로 고안된 장치는 헬리컬 불안정파 자극에 대한 효과를 입증하였고 또한 결과적으로 스월제트의 혼합을 증진시켰다.

• 한국공간구조학회:학술대회논문집
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• 한국공간구조학회 2006년도 춘계 학술발표회 논문집 제3권1호(통권3호)
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• pp.91-101
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• 2006

We have conducted the study about the shelter effect against the wind by using the wind fence with various porosities and the measured distance from the wind fence, in three different types of it ; (Circle wind fence, Vertical wind fence, Horizontal wind fence) The shelter effect and turbulence characteristics of the selected wind barrier is throughly investigated by wind tunnel test. flow characteristics of velocities and turbulences behind wind fence were measured using hot-wire anemometer. we characterize the turbulence behind the wind fence by varying the porosity of 0 %, 20 %, 40%, and 60%, and the distances from the wind fence from 1 H to 9 H with maintaining the uniform flow velocity of 6 m/s. In addition, we investigated the overall characterization of the wind fence by measuring total of twenty eight points on the wind fence, which forms the lattice structure on it with seven points in lateral direction and four points in vertical direction. The results of analysis from the circle wind fence indicate that the degree of the turbulence is lowered and the velocity of the wind is decreased when the porosity of 40 % are used at the distance from 3 H to 9 H. On the other hand, the vertical, horizontal wind fence with the porosity of 20% is more advantageous at the distance of 2 H to 9 H. For the effectiveness of the wind fence depending on the position, the center part is the greatest and it decreases at the edges with 10 % to 30 % less than that of at the center.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.691-698
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• 2017

본 연구에서는 스피커를 사용하여 Jet와 Swirl 유동에 각각 가진을 가함으로써 기체-기체 동축형 제트-스월 인젝터의 Injector transfer function (ITF)을 측정하였다. Feed system의 길이를 변화시켜감에 따라 ITF를 측정한 결과 섭동이 가해진 유동이 흐르는 공간의 공진주파수에서 ITF의 peak가 발생하는 것을 확인할 수 있었다. Jet 유동을 변화시키면서 Jet 유동에 가진을 줄 때, ITF의 크기는 감소하다가 56 slpm 이후부터는 증가하는 것을 확인할 수 있었다. 즉, Jet와 Swirl 유동의 속도차가 클수록 ITF의 크기가 커지는 것을 확인할 수 있었다. Swirl 가진 시에는 Jet 유동이 증가함에 따라 ITF가 감소하는 것을 확인할 수 있었는데, 이는 후단에서 일정 유량 대비 가진 에너지가 감소하기 때문이며, 이러한 차이는 후단의 Hot wire anemometer가 인젝터 중심축에 위치하기 때문이다.

• 대한기계학회논문집B
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• 제25권2호
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• pp.225-234
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• 2001

This paper represents the vector fields, three dimensional mean velocities, the turbulent intensities, the turbulent kinetic energy, and the Reynolds shear stresses in the X-Y plane of gas swirl burner with a cone type baffle plate measured by using X-probe from hot-wire anemometer system. This experiment is carried out at flow rates 350 and 450ℓ/min respectively, which are equivalent to the combustion air flow rate necessary for heat release 15,000 kcal/hr in gas furnace, in the test section of subsonic wind tunnel. The vector plot shows that the maximum axial mean velocity component exists in the narrow slits situated radially on the edge of gas swirl burner, for that reason, there is some entrainment phenomena of ambient air in the outer region of burner. Moreover, mean velocities in the initial region are largely distributed near the outer region of burner at Y/R≒0.97, but they diffuse and develop into the center flow region of burner according to the increase of axial distance. The turbulent intensities and the turbulent kinetic energy due to large inclination of mean velocity and swirl effect show that the maximum value in the initial region of burner is formed in the narrow slits situated radially on the edge of gas swirl burner and large values are mainly formed in the entire region of burner after X/R=2.4358, hence, the combustion reaction is anticipated to occur actively near this region. And the Reynolds shear stresses are also largely distributed from slite to vanes of gas swirl burner in the intial region, but their values largely disappear after X/R=3.2052.