• 대한설비공학회:학술대회논문집
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• 대한설비공학회 2007년도 동계학술발표대회 논문집
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• pp.286-293
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• 2007

• 한국터널지하공간학회 논문집
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• 제2권3호
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• pp.3-11
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• 2000

본 연구의 목적은 고속철도 터널 입구에 슬릿 커버 후드를 적용하여, 고속열차 터널 진입시 터널 출구 쪽에서 방사되는 미기압파를 저감시키는데 있다. 경부고속철도 $107m^2$의 단면적을 갖는 슬라브 궤도 0.5 km 터널에 대하여 슬릿 커버 후드라는 구조물 대책을 마련하였다. 개발시험 결과는 터널 입구에만 후드를 설치했을 경우 미기압파가 최대 41.2 %가 저감되었으며, 터널 입구에 후드를 설치하고 출구에 $45^{\circ}$ 경사갱구를 설치했을 경우는 47.7 %가 저감되었다.

• 대한기계학회논문집B
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• 제21권9호
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• pp.1095-1104
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• 1997

When a high-speed railway train enters a tunnel, a compression wave is generated ahead of the train and propagates along the tunnel, compressing and accelerating the rest air in front of the wave. At the exit of the tunnel, an impulsive wave is emitted outward toward the surrounding, which causes a positive impulsive noise like a kind of sonic boom produced by a supersonic aircraft. With the advent of high-speed train, such an impulsive noise can be large enough to cause the noise problem, unless some attempts are made to alleviate its pressure levels. For the purpose of the impulsive noise reduction, the present study investigated the effect of a vertical bleed duct on the compression wave propagating into a model tunnel. Numerical results were obtained using a Piecewise Linear Method and testified by experiment of shock tube with an open end. The results showed that the vertical bleed duct reduces the maximum pressure gradient of compression wave front by about 30 percent, compared with the straight tunnel without the bleed duct. As the width of the vertical bleed duct becomes larger, reduction of the impulsive noise is expected to be greater. However the impulsive noise is independent of the height of the vertical bleed duct.

• 대한기계학회논문집B
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• 제20권12호
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• pp.4036-4043
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• 1996

When a high-speed railway train enters a tunnel, a compression wave is generated ahead of the train and propagates along the tunnel, compressing and accelerating the rest air in front of the wave. At the exit of the tunnel, an impulsive wave is emitted outward toward the surrounding, which causes a positive impulsive noise like a kind of sonic boom produced by a supersonic aircraft. With the advent of high-speed train, such an impulsive noise can be large enough to cause the noise problem, unless some attempts are made to alleviate its pressure levels. In the purpose of the impulsive noise reduction, the present study tested the effect of porous walls on the compression wave propagating into a model tunnel. Experimental results were obtained using a shock tube with an open end. The results showed that the cavity/porous wall is very effective for the compression wave with a large nonlinear effect. The porosity of 30% is most effective for attenuation and pressure gradient reduction of the compression wave front. Also the impulsive noise reduction increases with increasing the length and height of the cavity, compared with the tunnel equivalent diameter.

• 터널과지하공간
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• 제24권4호
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• pp.308-315
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• 2014

본 연구에서는 도로터널 화재 시 외부 바람에 의한 영향을 평가하기 위하여 축소모형 실험을 실시하였다. $1.1m{\times}0.5m{\times}50.4m$ 모형 터널에서 휘발유 4.5리터를 사용하여 실험을 실시하였다. 터널 내부의 온도, 산소와 일산화탄소 농도를 측정하였다. 외부 바람의 영향에 따라 연기의 출구 도달 시간에 차이를 보였다. 최성기 이후에는 외부 바람의 영향이 초기에 비하여 작은 것을 확인할 수 있었다. 화재로 인하여 발생한 일산화탄소가 1,500 ppm 이상 도달하여 피난자에게 치명적인 위해를 가할 수 있다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집E
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• pp.373-379
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• 2001

When a train runs into a tunnel at high-speed, aerodynamic drag suddenly increases and the booming noise is generated at the exit of tunnel. The noise shape is very important to reduce the aerodynamic drag in tunnel as well as on open ground, and the micro-pressure wave that is a source of booming noise is dependent on nose shape, especially on area distribution. In this study, the nose shape has been optimized employing the response surface methodology and the axi-symmetric compressible Navier-Stokes equations. The optimal designs have been executed imposing various conditions of the aerodynamic drag and the micro-pressure wave on object functions. The results show that the multi-objective design was successful to decrease micro-pressure wave and aerodynamic drag of trains.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집E
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• pp.335-340
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• 2001

There are many tunnels located apart short distance from each other in mountainous country like Korea. Serial tunnels are connected by snow shelter in many cases. This study presents some countermeasures against micro-pressure wave at the tunnel exit using snow shelter. Through 1/60 scale model laboratory test, we find that snow shelter with 3.6m slit and slit cover show the effect of reducing the micro pressure wave to about 50.6%.

• 대한기계학회논문집B
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• 제22권6호
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• pp.823-831
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• 1998

In order to investigate the impulsive noise at the exit of high-speed railway tunnel and the pressure transients inside the tunnel, numerical calculations using a Total Variation Dimishing difference scheme were applied to axisymmetric unsteady compressible flow field. Some compression wave forms were assumed to model the compression wave produced in real high-speed railway tunnel. The numerical data were extensively explored to analyze the peak over-pressure and maximum pressure gradient in the pressure wavefront. The effect of the distance and cross-sectional area ratio between two-continuous ducts on the characteristics of the pressure waves were investigated. The peak over-pressure inside the second duct decreases for the distance and cross-sectional area ratio between two tunnels to increase. The peak over-pressure and maximum pressure gradient of the pressure wavefront inside the second duct increase as the maximum pressure gradient of initial compression wave increases. The present results were qualitatively well agreed with the results of the previous shock tube experiment.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2001년도 제16회 학술발표회 논문초록집
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• pp.35-38
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• 2001

차세대 추진 기관으로 연구되고 있는 스크램제트 엔진의 열역학적 특성들을 검토하였다. 유동이 엔진을 통과하면서 연소에 의해 전압력이 손실되고 노즐 출구 마하수가 감소하지만, 고온 연소 가스가 배출되기 때문에 실질적인 속도는 증가하게 되고 추력이 발생한다. 초음속 연소를 모사하기 위해 blowdown 형태의 초음속 연소 풍동 설계를 위한 개념 설계가 이루어졌다. 초음속 풍동 시험부에서 마하 2.5의 속도를 유지하기 위한 작동 압력과 질유량이 계산되었다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1999년도 추계 학술대회논문집
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• pp.29-35
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• 1999

A two-dimensional Euler code based on flux vector splitting scheme has been developed to simulate the behavior of supersonic shock wave over the cylinder. AF+ADI scheme was used for time integration. The sliding multiblock technique was implemented to handle the relative motion of the moving cylinder and the stationary tunnel. The code is validated with a problem of subsonic flow around a Naca-0012 airfoil. The Computation results show complex phenomena of the propagation of shock waves and the reflection as expansion wave at tunnel exit.