• 한국추진공학회지
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• 제5권1호
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• pp.34-41
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• 2001

고온의 연소가스로부터 노즐 표면을 보호하기 위하여 슬롯을 통하여 냉각 유체를 분사하는 슬롯 막냉각에 대하여 연구하였다. 냉각효율 및 열전달 특성은 주유동과 2차 유동의 분사율에 따라 크게 달라지며, 형상변화 및 유동가속에 의해서도 냉각 효과의 변화를 가져오게 된다. 본 연구에서는 실험을 통하여 축소노즐에서 분사율 변화에 따른 슬롯 막냉각 열전달 특성을 고찰하고, 평판 슬롯 막냉각 경험식의 결과와 비교하였으며, 수치해석을 통하여 축소노즐과 원형관에서의 냉각효율 및 열전달 특성도 비교하였다. 상대적으로 낮은 분사율에서 분사율 증가에 따른 냉각효율의 증가가 크게 나타났으며, 일정 분사율 이상에서는 냉각 효율의 증가가 크게 둔화되었다

• International Journal of Aerospace System Engineering
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• 제2권1호
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• pp.6-11
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• 2015

An active flow control technique using blowing and distributed suction on low Reynolds airfoil is investigated. Simultaneous blowing and distributed suction can recirculate the jet flow mass, and reduce the penalty to propulsion system due to avoiding dumping the jet mass flow. Energy is injected into main flow by blowing on the suction surface, and the low energy boundary flow mass is removed by distributed suction, thus the flow separation can be successfully suppressed. Aerodynamic lift to drag ratio is improved significantly using the flow control technique, and the energy consumption is quite low.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.115-119
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• 2004

The effect of a continuous blowing or suction on an oscillating 2-D NACA0012 airfoil was investigated numerically for the dynamic stall control. The influence of control parameter variation was also studied in the view point of aerodynamic characteristics. The result showed that the blowing control kept a higher lift drag ratio before stall angle but the dynamic stall angle was not exceed to without control result. As the slot position was closer to leading edge, the positive control effect becomes greater. The stronger jet and the smaller jet angel made more favorable roles on the control performance. In the cases of the suction, the overall control features were similar to those of the blowing, but dynamic stall angle was increased, i.e. suction was more effective to control dynamic stall. It was also founded that the suction control was showed better control effect as the slot position moves to trail edge within thirty percentage of chord length. In the simulation for the jet strength and the jet angle control, the same tendencies were observed to those of blowing cases.

• 산업식품공학
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• 제21권2호
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• pp.110-115
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• 2017

본 연구에서는 절삭식 정미기의 절삭롤러에 장착된 통풍간극링의 통풍구 수와 정백 중 발생하는 미강제거에 필요한 흡인 송풍속도가 정백특성에 미치는 영향을 구명하여 절삭식 정미기 개발의 기초자료를 제시하고자 하였다. 그 결과를 요약하면 다음과 같다. 백도는 모든 조건에서 $38{\pm}0.5$로 측정되어 균일하게 정백된 것으로 나타났다. 정백 후 곡온 상승은 송풍속도가 증가할수록 곡온 상승이 낮아지는 경향을 보였고, 절삭롤러 통풍구 수 3구, 송풍속도 35, 40 m/s 조건에서 각각 $15.4^{\circ}C$ $14.6^{\circ}C$로 나타났다. 동할미율은 절삭롤러 통풍구 수 3구, 송풍속도 35 m/s 조건에서 2.13%로 가장 낮게 측정되었다. 싸라기율은 모든 조건에서 0.762-0.869%로 낮은 범위를 보였다. 백미 1 ton을 생산하기 위한 에너지 소비량은 송풍속도가 증가할수록 감소하는 것으로 나타났다. 따라서 절삭식 정미기의 절삭롤러 통풍구 수와 미강제거를 위한 흡인 송풍속도에 따른 적정 정백조건은 곡온, 동할미율, 싸라기율의 품질적인 측면과 에너지 소비량 등을 고려할 경우 절삭롤러 통풍구 수 3구, 송풍속도 35 m/s 조건이 적절한 것으로 판단된다.

• 대한기계학회논문집B
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• 제29권1호
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• pp.46-54
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• 2005

Film cooling characteristics has been examined numerically for the height variation of a stepped slot exit. In this study, the upstream wall height of the stepped slot exit varies from -2d (d = slot width) to 3d, blowing ratio ranges from 0.5 to 3, and injection angles are $15^{\circ},\;30^{\circ},\;and\;45^{\circ}$. The results showed that film cooling performance was mainly subjected to the magnitude of recirculation region near the downstream-side slot exit as well as the magnitude and the distribution region of turbulent kinetic energy due to the local velocity and momentum differences between the coolant and the main flow near the slot exit. The up-1d type slot at higher blowing ratios over 2 and the flat type slot at lower blowing ratios below 1 have the best film cooling performances, in case of the injection angles of $30^{\circ},\;and\;45^{\circ}$, respectively. Compared with the other injection angles, in case of the injection angles of $15^{\circ}$, the best film cooling performances was shown in even a higher upstream wall (up-3d) at higher blowing ratio like 3 by the gradual reduction of the coolant velocity which minimizes the local velocity differences between the coolant and the main flow near the slot exit.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
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• pp.91-94
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• 2003

An experimental study has been carried out in a supersonic blow-down wind tunnel for examining the influence of streamwise vortices on normal shock-wave/boundary layer interaction. It has been reported by the earlier investigator the streamwise vortices generated by the blowing jets can significantly suppress the shock-induced separation and reduce the wave drag. The blowing jets generate the streamwise vortices with 45$^{\circ}$ angle in the spanwise direction. The shock waves are visualized by a Schlieren optical system. Appropriate measurement systems are provided for the characterization of shock wave/boundary layer interaction. The chamber pressure ratio and blowing pressure ratio are varied from 1.5 to 2.4 and 1.0 to 2.0 respectively.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2001년도 유체기계 연구개발 발표회 논문집
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• pp.334-338
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• 2001

In order to investigate the effects of various injection hole shapes on the film cooling of turbine blade, three test models having cylindrical and shaped holes were used. A three-dimensional Navier-Stokes code with standard k-$\epsilon$ model was used to compute the film cooling coefficient on the film cooled turbine blade. Over 330,000 grids were used to compute the flow over the blade. Mainstream Reynolds number based on the cylinder diameter was $7.1{\times}10^4$. The turbulence intensity kept at $5.0\%$ for all inlets. The effect of coolant blowing ratio was studied for various blowing ratios. For each blowing ratios, wall temperatures around the surface of test model were calculated. Temperature was visualized using cartesian cut-cell method to obtain traces of the injected secondary air on the test surface, so we could interpret the film effectiveness as temperature distributions.

• 대한기계학회논문집B
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• 제22권12호
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• pp.1735-1745
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• 1998

Oil-film surface flow visualizations and three-dimensional flow measurements using a straight five-hole probe have been conducted for a circular impinging jet which is normally oriented to the crossflow in a channel. Throughout the experiments, the ratio of channel height to injection hole diameter, H/D, is fixed to be 1.0, and blowing ratio is varied to be 1.0, 2.0, 3.0 and 4.0. From the surface flow visualizations for both top wall(target plate) and bottom wall, impinging jet region on the target plate can be clearly identified, and for the small value of H/D = 1.0, presence of the bottom wall changes the near-hole flow structure, significantly. The three-dimensional flow measurements show that in the dawnstream region of the injection hole, there exist a pair of counter-rotating vortices, called "scarf vortices", and the strength of the vortices strongly depends on the blowing ratio. In addition, a new flow model in the flow symmetry plane has been proposed for H/D = 1.0.

• 한국유체기계학회 논문집
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• 제6권3호
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• pp.21-27
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• 2003

Dispersion of coolant jets in a film cooling flow field is the result of a highly complex interaction between the film cooling jets and the mainstream. In order to investigate the effect of blowing ratios on the film cooling of a turbine blade, cylindrical body model is used. Mainstream Reynolds number based on the cylinder diameter is $7.1{\times}10^4$. The effects of coolant flow rates are studied for blowing ratios of 0.7, 1.0, 1.3 and 1.7, respectively. The temperature distribution of the cylindrical model surface is visualized with infrared thermography (IRT). Results show that the film cooling performance could be significantly improved by the shaped injection holes. For higher blowing ratio, the spanwise-diffused injection holes are better due to the lower momentum flux away from the wall plane at the hole exit.

• 대한기계학회논문집B
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• 제37권7호
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• pp.655-663
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• 2013

막냉각에 관한 많은 연구들은 주유동과 이차유로가 평행한 형태로 연구가 이루어졌다. 하지만 실제 터빈 블레이드에서 이차유로의 방향은 일반적으로 주유동의 방향에 수직한 형태이다. 그래서 본 연구에서는 이차유동의 방향이 이중분사 막냉각의 효율에 미치는 영향을 수치해석을 통해 알아보고자 한다. 분사율은 1, 2이고 횡방향 분사각은 $22.5^{\circ}$이다. 분사율이 1일 때 평행 형상에서는 안티키드니 와류가 잘 형성되어 막냉각 효율이 수직 형상의 경우보다 더 높다. 반면에 분사율이 2일 때 수직 형상의 막냉각 효율은 평행 형상보다 향상되었다. 많은 유량의 제트가 서로 반대 방향으로 분사되기 때문에 두 형상 모두 막냉각 효율이 높게 나타난다. 하지만 안티키드니 와류의 영향은 다른 분사율보다 상대적으로 작다.