• 한국산업보건학회지
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• 제16권3호
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• pp.290-301
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• 2006

A push pull hood system is frequently applied to control contaminants evaporated from an open surface tank. Efficiency of push pull hood system is affected by various parameters, such as, cross draft, vessel shapes, tank surface area, liquid temperature. A previous work assisted by flow visualization technique qualitatively showed that a strong cross draft blown from the pull hood to push slot could destroy a stable wall-jet on the surface of tank, resulting in the abrupt escape of smoke from the surface. In this study, the tracer gas method was applied to determine the effect of cross-draft on the capture efficiency qualitatively. A new concept of capture efficiency was introduced, that is, linear efficiency. This can be determined by measuring the mass of tracer gas in the duct of pull hood while the linear tracer source is in between push slot and pull hood. By traversing the linear tracer source from the push slot to the pull hood, it can be found where the contaminant is escaped from the tank. Total capture efficiency can be determined by averaging the linear efficiencies. Under the condition of cross-draft velocities of 0, 0.4, 0.75, 1.05 and 1.47m/s, total capture efficiencies were measured as 97.6, 95.4, 94.6, 92.7 and 70.5% respectively. The abrupt reduction of efficiency with cross-draft velocity of 1.47m/s was due to the destruction of tank surface wall-jet by the counter-current cross-draft. The same phenomenon was observed in the previous flow visualization study. As an alternative to overcome this abrupt efficiency drop, the 20% increase of hood flow rates was tested, resulting in 20% efficiency increase.

• 한국안전학회지
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• 제25권3호
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• pp.22-27
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• 2010

A prediction performance of Fire Dynamics Simulator(FDS) developed by NIST for the diffusion flame structure was validated with experimental results of a laminar slot jet diffusion flame. Two mixture fraction combustion models and two finite chemistry combustion models were used in the FDS simulation for the validation of the jet diffusion flame structure. In order to enhance the prediction performance of flame structure, DNS and radiation model was applied to the simulation. The reaction rates of the finite chemistry combustion models were appropriately adjusted to the diffusion flame. The mixture fraction combustion model predicted the diffusion flame structure reasonably. A 1-step finite chemistry combustion model cannot predict the flame structure well, but the simulation results of a 2-step model were in good agreement with those of experiment except $CO_2$ concentration. It was identified that the 2-step model can be used in the investigation of flame suppression limit with further adjustment of reaction rates

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 춘계학술대회
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• pp.1948-1954
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• 2003

The thrust vector control using a fluidic counterflow concept is achieved by applying a vacuum to a slot adjacent to a primary jet which is shrouded by a suction collar. The vacuum produces a secondary reverse flowing stream near the primary jet. The shear layers between the two counterflowing streams mix and entrain mass from the surrounding fluid. The presence of the collar inhibits mass entrainment and the flow near the collar accelerates causing a drop in pressure on the collar. For the vacuum asymmetrically applied to one side of the nozzle, the jet will vector toward the low-pressure region. The present study is performed to investigate the effectiveness of thrust vector control using the fluidic counterflow concept. A computational work is carried out using the two-dimensional, compressible Navier-Stokes equations, with several kinds of turbulence models. The computational results are compared with the previous experimental ones. It is found that the present fluidic counterflow concept is a viable method to vector the thrust of a propulsion system.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.37-40
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• 2003

The thrust vector control using a fluidic counterflow concept is achieved by applying a vacuum to a slot adjacent to a primary jet which is shrouded by a suction collar. The vacuum produces a secondary reverse flowing stream near the primary. The shear layers between the two counterflowing streams mix and entrain mass from the surrounding fluid. The presence of the collar inhibits mass entrainment and the flow m the collar accelerates causing a drop in pressure on the collar. For the vacuum asymmetrically applied to one side of the nozzle, the jet will vector toward the low-pressure region. The present study is performed to investigate the effectiveness of thrust vector control using the fluidic counterflow concept. A computational work is carried out using the two-dimensional, compressible Navier-Stokes equations, with several kinds of turbulence models. The computational results are compared with the previous experimental ones. It is found that the present fluidic counterflow concept is a viable method to vector the thrust of a propulsion system.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.592-597
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• 2003

Thrust vector control using a coflow-counterflow concept is achieved by suction and blowing through a slot adjacent to a primary jet which is shrouded by a suction collar. In the present study, the flow characteristics of thrust vectoring is investigated using a numerical method. The nozzle has a design Mach number of 2.0, and the operation pressure ratio is varied to obtain various flow features of the nozzle flow. Test conditions are in the range of the nozzle pressure ratio from 6.0 to 10.0, and a suction pressure from 90kPa to 35kPa. Two-dimensional, compressible Navier-Stokes computations are conducted with RNG ${\kappa}-{\varepsilon}$ turbulence model. The computational results provide an understanding of the detailed physics of the thrust vectoring process. It is found that an increase in the nozzle pressure ratio leads to increased thrust efficiency but reduces the thrust vector angle.

• Advances in aircraft and spacecraft science
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• 제7권6호
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• pp.537-551
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• 2020

Investigation of leading edge impingement cooling for first stage rotor blades in an aero-engine turbine, its effect on rotor temperature and trailing edge wake loss have been undertaken in this study. The rotor is modeled with the nozzle for attaining a more accurate simulation. The rotor blade is hollowed in order for the coolant to move inside. Also, plenum with the 15 jet nozzles are placed in it. The plenum is fed by compressed fresh air at the rotor hub. Engine operational and real condition is exerted as boundary condition. Rotor is inspected in two states: in existence of cooling technique and non-cooling state. Three-dimensional compressible and steady solutions of RANS equations with SST K-ω turbulent model has been performed for this numerical simulation. The results show that leading edge is one of the most critical regions because of stagnation formation in those areas. Another high temperature region is rotor blade tip for existence of tip leakage in this area and jet impingement cooling can effectively cover these regions. The rotation impact of the jet velocity from hub to tip caused a tendency in coolant streamlines to move toward the rotor blade tip. In addition, by discharging used coolant air from the trailing edge and ejecting it to the turbines main flow by means of the slot in trailing edge, which could reduce the trailing edge wake loss and a total decrease in the blade cooling loss penalty.

• 대한기계학회논문집B
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• 제21권7호
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• pp.849-861
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• 1997

In this study, the effect of hole geometry of the cooling system on the flow and temperature field was numerically calculated. The finite volume method was employed to discretize the governing equation based on the non-orthogonal coordinate with non-staggered variable arrangement. The standard k-.epsilon. turbulence model was used and also the predicted results were compared with the experimental data to validate numerical modeling. The predicted results showed good agreement in all cases. To analyze the effect of the discharge coefficient for slots of different length to width, the inlet chamfering and radiusing holes were considered. The discharge coefficient was increased with increment of the chamfering ratio, radiusing ratio and slot length to width and also the effect of radiusing showed better result than chamfering in all cases. In order to analyze the difference between the predicted results with plenum region and without plenum region, the velocity profiles of jet exit region for a various flow conditions were calculated. The normal velocity components of jet exit showed big difference for the low slot length to width and high blowing rate cases. To analyze the flow phenomena injected from a row of inclined holes in a real turbine blade, three dimensional flow and temperature distribution of the region including plenum, hole and cross stream with flow conditions were numerically calculated. The results have shown three-dimensional flow characteristics, such as the development of counter rotating vortices, jetting effect and low momentum region within the hole in addition to counter rotating vortex structure in the cross stream.

• 한국추진공학회지
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• 제13권1호
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• pp.10-18
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• 2009

본 연구에서는 평행 벽 제트-노즐 형상의 막냉각 수치해석에 적합한 난류모델을 선정하고자 하였다. 현재 실험을 하기 위한 전 단계이므로, 먼저 유사한 참고 형상에 대해 Standard $k-{\epsilon}$ 모델과 RNG $k-{\epsilon}$ 모델, SST $k-{\omega}$ 모델, 그리고 RSM 모델 등 다양한 난류모델을 적용하였고, Near-wall 처리 방법으로서 SST $k-{\omega}$ 모델을 제외하고는 Standard wall functions와 Enhanced wall functions 등 2종류를 각각의 모델에서 사용하였으며, 실험값과 비교하여 보다 적합한 난류모델을 선정하고자 하였다. 나아가 2차원 축대칭으로 평행 벽 제트-노즐 단일 슬롯 형상에 대해 기선정한 난류모델을 적용하여 막냉각 특성을 살펴보았다. 유사 참고 형상에 대한 해석 결과 Standard $k-{\epsilon}$ 모델 및 RSM 모델이 거의 비슷한 성능을 보여주었으나 수렴성이 우수한 Standard $k-{\epsilon}$ 모델이 선정되었다. 또한 Standard wall functions를 사용하는 것보다 Enhanced wall functions를 사용하는 것이 더 좋은 결과를 보여주었다. 나아가 평행 벽 제트-노즐 단일 슬롯 형상에 적용한 결과 물리적으로 타당한 막냉각 특성을 보여주었다. 선정된 모델 및 해석방법론을 이용하여 평행 벽 제트-노즐 다단 슬롯 형상에 대한 막냉각 해석을 수행할 예정이며, 관련 결과는 추후 실험 예비해석 방법론으로 활용할 예정이다.

• 대한토목학회논문집
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• 제7권1호
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• pp.11-22
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• 1987

흐름수역(水域)에서 연직상향으로 방류되는 평면부력(平面浮力)?의 거동이 연속방정식(連續方程式), 운동량방정식(運動量方程式) 및 추적물수송식(追跡物輸送式)의 기본방정식을 수치적(數値的)으로 풀음으로서 해석(解析)된다. 난류확산(亂流擴散)에는 Prandtl의 혼합거리이론(混合距離理論)을 도입한 난류수송모형(亂流輸送模型)이 이용된다. 수치해과정(數値解過程)은 기본방정식을 유함수(流凾數)(stream function)식(式)과 골도수송(滑度輸送)(vorticity transport)식을(式) 이용하여 변환(變換)한 후, ?방류속도(放流速度), ?방류구폭(放流口幅) 등(等)으로 표현되는 변수(變數)와 흐름을 지배(支配)하는 무차원매개변수(無次元媒介變數)를 도입하여 무차원화(無次元化)하고 successive under-relaxation을 이용하여 Gauss-Seidal 반복법(反復法)으로 해를(解) 구(求)하는 것이다. 수치실험(數値實驗)은 방류(放流)Froude수(數)가 4~32, 방류속도(放流速度)와 가로흐름속도와의 비로(比) 정의되는 속도비가 8~15 의 범위의 흐름영역(領域)에서 수행되었다. 부력(浮力)?으로 인한 주변(周邊)흐름수역(水域)의 속도변화(速度變化), 온도상승(溫度上昇)범위, 흐름상태 및 골도(滑度)가 조사되었으며, ?의 경로에 대한 속도비와 방류밀도Froude 수의 영향이 또한 조사되었다. ?중심선의 속도, 온도변화, 국부밀도(局部密度)Froude 수(數)의 변화가 계산되며 퍼짐율(spreading rate)과 확산비(擴散比)(dispersion ratio)가 방류밀도(放流密度)Froude 수, 국부밀도(局部密度)Froude 수(數) 및 속도비(速度比)의 항(項)으로 해석되었다. 또한 속도와 온도분포를 상사(相似)(similarity)로 나타낼 수 있음이 밝혀졌으며, Gaussian 분포(分布)를 이용한 적분형해석(積分型解析)(integral type analysis)이 가능한 것으로 사료된다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2006년도 제33회 KOSCO SYMPOSIUM 논문집
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• pp.60-64
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• 2006

Propagation rates ($U_{edge}$) of various premixed, twin edge-flames were measured as a function of global strain rate ($\sigma$), mixture strength, and Lewis number (Le). Using a counterflow slot-jet burner with electrical heaters at each end, both advancing (positive $U_{edge}$) and retreating (negative $U_{edge}$) edge-flames can be studied as they propagate along the long dimension of the burner. Experimental results are presented for premixed methane/air twin flames in terms of the effects of $\sigma$ on $U_{edge}$. Both low-$\sigma$ and high-$\sigma$ extinction limits were discovered for all mixtures tested. As a result, the domain of edge-flame stability was obtained in terms of heat loss factor and normalized flame thickness, and comparison with the numerical result of other researchers was also made. For low ($CH_4/O_2/CO_2$) and high ($C_3H_8$/air) Lewis number cases, propagation rates clearly show a strong dependence on Le.