• 한국터널지하공간학회 논문집
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• 제21권6호
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• pp.749-762
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• 2019

최근 들어 대도시의 교통난 해소 및 녹지공간 확보를 위해서 도로의 지하화가 추진되고 있으며, 대형차 혼입률이 낮기 때문에 소형차 전용 도로터널로 계획되거나 건설되고 있다. 또한, 도시에 건설되고 있는 터널은 간선도로의 기능을 수행하기 위해서 장대화되는 추세이다. 따라서 환기시스템의 용량이 증대하고 다양한 환기방식이 요구되고 있으며, 환기기 운전비용 등 터널준공 후, 유지관리의 중요성이 부각되게 되었다. 따라서 환기기 소비전력의 절감을 위한 운전단계의 최적화나 환기기 운전제어로직에 대한 연구의 필요성이 증대하고 있는 실정이다. 본 연구에서는 소형차 전용도로 터널에 ① 제트팬방식과 조합환기방식, ② 제트팬 + 공기정화방식, ③ 제트팬 + 수직갱방식, ④ 제트팬 + 급기반횡류환기방식을 적용하여 에너지 절약적인 환기기 운전을 실현하기 위해서 운전단계 및 제어로직 최적화 방안의 필요성에 대한 연구를 수행하였다. 연구의 결과로 조합환기방식의 터널의 경우, 다양한 운전조합이 있을 수 있으며, 발생되는 환기량이 동일할 지라도 운전조합에 따라 소요동력이 크게 차이가 나며, 일반적으로 수행하고 있는 제트팬 우선 운전방식보다는 축류팬을 우선 운전하는 것이 동력절감에 효과가 있는 것으로 나타났다.

• Wind and Structures
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• 제19권1호
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• pp.15-33
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• 2014

This paper describes partial turbulence simulation and validation of the aerodynamic pressures on building models for an open-jet small-scale 12-Fan Wall of Wind (WOW) facility against their counterparts in a boundary-layer wind tunnel. The wind characteristics pertained to the Atmospheric Boundary Layer (ABL) mean wind speed profile and turbulent fluctuations simulated in the facility. Both in the wind tunnel and the small-scale 12-Fan WOW these wind characteristics were produced by using spires and roughness elements. It is emphasized in the paper that proper spectral density parameterization is required to simulate turbulent fluctuations correctly. Partial turbulence considering only high frequency part of the turbulent fluctuations spectrum was simulated in the small-scale 12-Fan WOW. For the validation of aerodynamic pressures a series of tests were conducted in both wind tunnel and the small-scale 12-fan WOW facilities on low-rise buildings including two gable roof and two hip roof buildings with two different slopes. Testing was performed to investigate the mean and peak pressure coefficients at various locations on the roofs including near the corners, edges, ridge and hip lines. The pressure coefficients comparisons showed that open-jet testing facility flows with partial simulations of ABL spectrum are capable of inducing pressures on low-rise buildings that reasonably agree with their boundary-layer wind tunnel counterparts.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2006년도 제27회 추계학술대회논문집
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• pp.377-381
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• 2006

본 논문에서는 노즐출구 단면에 설치된 메쉬 스크린을 이용하여 초음속 제트 소음 제어하기 위한 실험을 수행하였다. 메쉬 스크린은 미소 직경을 가진 스테인레스 철사들로 만들어졌으며 철망 형태이다. 노즐 압력비는 과팽창에서 부족팽창된 초음속 제트를 얻기 위해 다양하게 변화시켰다. 초기 제트 전단층을 교란하기 위해, 메쉬 스크린의 중앙 부분에 구멍을 만들었으며 그 구멍크기는 메쉬 스크린의 소음 저감효과를 조사하기 위해 변화시켰다. 유동장을 가시화하기 위해 쉴리렌 광학 장치를 사용하였고 OASPL과 소음 스펙트럼을 얻기 위해 음향을 측정하였다. 본 실험으로부터 얻어진 결과는 메쉬 스크린이 스크리치 톤을 상당히 억제하였으며, 메쉬 스크린의 구멍크기는 초음속 제트 소음을 저감하는 중요한 인자였다. 과팽창된 제트인 경우, 소음 저감효과는 적정팽창과 부족팽창된 제트에서의 저감효과보다 매우 크게 나타났다.

• Journal of Advanced Marine Engineering and Technology
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• 제38권3호
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• pp.246-252
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• 2014

본논문은 150마력급 선내형 소형 워터제트 추진시스템 개발에 대한 연구이다. 워터제트는 흡입부, 임펠러, 디퓨저(공기확산기), 후진부와 메인 샤프트로 구성되어 있다. 워터제트의 구성품은 사형 주조후 정밀가공을 거쳐 개발하였다. 워터제트 추진기관의 개발은 각각의 부품에 대한 설계-제작-검사의 과정을 거쳐 최종 완성하였으며, 육상 시험 풀에서는 선체의 이동 없이 워터제트의 펌프 특성을 확인한 결과, 최대 37m/s의 유속과 0.29m3/s의 유량을 배출할 수 있는 성능을 확보하였다. 본 연구에서 개발된 워터제트 추진장치를 설치한 21ft 시험선을 사용하여 실증 연구를 수행하였다. 그 결과, 국내 연안에서 시험시 선체무게와 엔진등 기타 부수적인 무게가 대략 1.2ton 가량 이였으며 이 상태에서 엔진회전수 3,700rpm에서 최대시속 45km/h의 운항속도를 기록하였다.

• 대한기계학회논문집B
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• 제22권5호
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• pp.716-724
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• 1998

The objective of this research was to investigate the enhancement of heat transfer by mesh in impinging air jet system. The technique used in this research is to place mesh as a turbulence promoter in front of the impinging plate. The heat transfer characteristics with and without mesh, the effect of clearances between impinging plate and mesh, the effect of distance between nozzle exit and impinging plate, and the effect of nozzle exit velocity have been studied experimentally. When mesh was installed in front of the impinging plate, heat transer has been increased due to the acceleration between rectangular holes and divided small jets. When clearances are changed, heat transfer comes to a maximum under the condition of C = 1 mm, irrespective of nozzle exit velocity or H/B. Also the average heat transfer enhancement with mesh has been increased about 44% under the condition of U = 18 m/s, H/B = 2 and C = 1 mm, compared to the result of a flat plate without mesh. And the results of this research are compared with existing heat transfer augmentation method by rectangular or circular rod.

• 대한설비공학회:학술대회논문집
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• 대한설비공학회 2009년도 하계학술발표대회 논문집
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• pp.835-840
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• 2009

In this paper, confined multiple slot jet impingement with exhaust ports is investigated numerically. A flow cell, defined as volume sectioned by the impingement and confinement surfaces and the centerlines of adjacent nozzle and exhaust port, is chosen for computational domain. The effects of Reynolds number and geometrical parameters on the heat transfer performance and the flow characteristics are studied. For turbulence, the Abe-Kondoh-Nagano version of the low-Reynolds k-$\varepsilon$ model is employed. The results showed that the local Nusselt number distribution is shifted down and show poor heat transfer performance for small Reynolds number and small ratio of the lateral and axial length of flow cell. The rest of range, except the range of the shift phenomenon, can be classified into three groups by heat transfer characteristics.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.774-778
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• 2004

The atomization process of a circular $SF_{6}$ liquid jet issued into an otherwise quiescent, high-pressure $N_2$ gas was observed to explore the breakup mechanism of liquid ligaments involved in turbulent atomization. Both liquid and gas temperatures were fixed at a room temperature but the gas pressure was elevated to more than twice the critical pressure of $SF_{6}$. Therefore, the liquid surface was in a thermodynamic state close to a critical mixing condition with suppressed vaporization. Since the surface tension and the surface gas density approach zero and the surface liquid density, respectively, phenomena equivalent to those which would appear when a very high speed laminar flow of water were injected into the atmospheric-pressure air can be observed by issuing $SF_{6}$ liquid at low speeds in micro-gravity environment which avoid disturbances due to gravity forces. The instability ob near-critical mixing surface jet was quantitatively characterized using a newly developed device, which could issue a very small amount of $SF_{6}$ liquid at small constant velocity into a very high-pressure $N_2$ gas.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 춘계 학술대회논문집
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• pp.113-118
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• 2004

This paper presents a two-dimensional edge tone to predict the frequency characteristics of the discrete oscillations of a jet-edge feedback cycle by the finite difference lattice Boltzmann method (FDLBM). We use a new lattice BGK compressible fluid model that has an additional term and allow larger time increment comparing the conventional FDLBM, and also use a boundary fitted coordinates. The jet is chosen long enough in order to guarantee the parabolic velocity profile of the jet at the outlet, and the edge consists of a wedge with an angle of $\alpha=23^0$. At a stand-off distance $\omega$, the edge is inserted along the centreline of the jet, and a sinuous instability wave with real frequency f is assumed to be created in the vicinity of the nozzle and th propagate towards the downstream. We have succeeded in capturing very small pressure fluctuations result from periodically oscillation of jet around the edge. That pressure fluctuations propagate with the sound speed. Its interaction with the wedge produces an irrotational feedback field which, near the nozzle exit, is a periodic transverse flow producing the singularities at the nozzle lips. The lattice BGK model for compressible fluids is shown to be one of powerful tool for computing sound generation and propagation for a wide range of flows.

• 전기의세계
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• 제24권1호
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• pp.75-85
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• 1975

In order to develop the commercial frequency (60Hz) plasma torch of small capacity for material cutting, welding and other industrial heating, the A.C plasma jet generator of non-transfered type is made domestically and the electrode configurations of plasma torch are composed of two kinds of electrodes W-C and W-Cu, combined by thermal emission and field emission electrode materials. In this paper, the characteristics of input power, thermal efficiency, electrode consumption, the flame and forms of arc voltage and arc current for A.C plasma torch are investigated in relation to such variables as arc current, argon flow and magnetic field intensity to obtain the basic design data necessary to A.C plasma jet generator. The result are as follows; (1)The input power, thermal efficiency and electrode consumption are influenced greatly by argon flow, magnetic field intensity and nozzle materials. (2)A.C arc voltage and current are non-symmetrial, involving D.C Component. Due to this current of D.C Component, transformer core is saturated and a large abnormal current flows into the primary winding coil. In order to prevent this abnormal current flow, a condenser must be connected in series to the main discharge circuit. (3)The stability and sharpness of jet flame are improved more in the torch of W-C electrode configuration than in the torch of W-Cu electrode configuration.

• 한국전산유체공학회지
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• 제15권4호
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• pp.46-52
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• 2010

In the present work, the aerodynamic characteristics of elliptic airfoils which have a 12% thickness ratio are numerically investigated based on Reynolds-averaged Navier-Stokes equations and a transition SST model at a Reynolds number 8.0$\times$105. The numerical simulation of a synthetic jet actuator which is a well-known zero-net-mass active flow control actuator located at x/c = 0.00025, was performed to control massive flow separation around the leading edge of the elliptic airfoils. Four cases of non-dimensional frequencies were simulated at an angle of attack of 12 degree. It is found that the size of the vortex induced by synthetic jets was getting smaller as the jet frequency becomes higher. Comparison of the location of synthetic jets between x/c = 0.00025 (around the leading edge) and x/c = 0.9 (near the separation) shows that the control near the leading edge induces closed recirculation flow regions caused by the interaction of the synthetic jet with the external flow, but the control applied at 0.9c (near the trailing edge) induces a very small and weak vortex which quickly decays due to weak intensity.