• 한국음향학회지
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• 제34권2호
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• pp.146-156
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• 2015

본 연구는 흡음재와 확산체의 적용위치가 소공연장의 음향성능에 미치는 영향에 대하여 알아보았다. 서울의 대학로의 2000년 이후 개관한 36곳의 공연장의 평균크기로 소공연장의 표준모델을 설정하여 연구를 진행하였다. 본 연구에서는 마감재 적용유효면적이 가장 작은 뒷벽을 기준으로 마감재의 적용면적을 산출하고, 마감재의 적용위치별 음향성능 변화를 분석하기 위하여 천장, 측벽의 적용위치를 전반부, 중반부, 후반부로 구분하여 총 8가지의 경우를 만들어, 1/10 축소모형실험을 진행하였다. 사용된 음향지표는 잔향시간(Reverberation Time, RT), 초기감쇠시간(Early Decay Time, EDT), 음악명료도(Clarity, C80), 음성명료도(Definition, D50), 음성전달지수(Speech Transmission Index, STI)를 이용하였다. 실험결과 마감재의 적용위치 변화는 소리의 울림에 양과 관련된 음향인자인 잔향시간, 초기감쇠시간 은 최소 변화 감지폭에 의한 (Just Noticeable Difference, JND) 평가시 변화가 뚜렷하게 나타났고, 소리의 명료도와 관련된 인자인 음악명료도, 음성명료도, 음성전달지수는 변화가 거의 없는 것으로 나타났다. 짧은 잔향시간을 얻고자 하는 경우 흡음재와 확산체 적용시 모두 측벽부분을 통한 잔향시간 조절이 가장 효과적이며, 측벽 전반부가 가장 짧은 잔향시간을 얻을 수 있는 위치인 것으로 나타났다.

• 한국항공운항학회지
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• 제19권4호
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• pp.24-29
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• 2011

Conceptual study of an open-circuit type low-speed wind tunnel for performance test of wind turbine blade and airfoil is conducted. The tunnel is constituted of a settling chamber, a contraction, closed test section, a diffuser, two corners, a cross leg and a fan and motor. For the performance test, the closed test section width of 1.8 m, height of 1.8 m and length of 5.25 m is selected. The contraction ratio is 9 to 1 and maximum speed in the test section is 67 m/sec. Input power in the tunnel is about 238 kW and its energy ratio is 3.6. The wind tunnel designed in present study will be an effective tool in research and development of wind turbine and airfoil.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제37회 추계학술대회논문집
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• pp.881-884
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• 2011

본 연구에서는 축소형 이차목 초음속 디퓨저를 Normal Shock Theory를 이용하여 설계/제작하여 상온의 질소가스를 이용하여 실험을 수행하였다. 실험 결과 이론식으로 설계된 이차목 초음속 디퓨저의 시동압력은 18%정도의 오차를 보였고, 이는 벽면 마찰 손실에 의한 차이로 보여진다.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 1999년도 유체기계 연구개발 발표회 논문집
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• pp.33-40
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• 1999

Upgrade development of a high pressure ratio centrifugal compressor in marine engine turbochargers is presented. A new matched operating point at increased speed of rotation was determined through system cycle analysis using the exisitng test data of turbine performance. Under some severe restrictions for geometric parameters, the state-of-the-art methods of both aerodynamic design and CFD analysis were applied, in which only an impeller, a vaned diffuser and some part of casing wall were modified. Prototype hardware was fabricated and assembled for system performance tests. Excellent performance in pressure ratio and efficiency was obtained over whole speed region. Reduced surge and choke margin was, however, observed at design speed of rotation.

• 대한전자공학회논문지TC
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• 제44권12호
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• pp.79-84
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• 2007

본 논문에서는 CRD(Cubical Residue Diffuser)를 이용하여 전자파 잔향실 내의 전기장 균일도를 향상시키고, 잔향실 내의 전기장 균일도가 최적화되는 CRD 면적비를 연구하였다. $1\sim3$ GHz 주파수 대역에서 Schroeder 방식의 CRD를 설계하였고, 전자파 잔향실 내의 전기장 분포 해석을 위해 FDTD(Finite Difference Time Domain) 수치해석이 이루어졌다. 해석결과 2 GHz에서 CRD의 면적이 잔향실 한쪽 내벽의 약 $40\sim80%$일 경우 전기장 강도 표준 편차가 낮고 균일하게 분포되었으며, 40 % 이하, 또는 80 % 이상의 면적에서는 표준 편차가 높게 나타났다. 특히 가장 나쁜 경우와 비교하여 44%일 때 전기장 균일도가 1 dB 향상됨을 알 수 있었다.

• 대한기계학회논문집B
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• 제28권3호
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• pp.330-337
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• 2004

Analysis of flow phenomena in a centrifugal compressor impeller has been carried out with numerical simulation to understand the physics of flow near stall. Near stall point, tip leakage flow spills ahead of the leading edge of adjacent blade and other leakage flow passes over the clearance of the adjacent blade instead of rolling up into vortex within the passage. The tip leakage flow at the mid chord of impeller blade impinges against the pressure surface of the adjacent blade and then rolls up into vortex within the passage, which blocks the flow passage and generates viscous loss. The spillage of leakage flow ahead of the adjacent blade generates the recirculation of flow entering the impeller, which causes the power transferred into the flow by the impeller to decrease and blocks the flow passage. Near diffuser hub wall, flow recirculation occurs. As operating point goes to stall point, the core of recirculation approaches the impeller exit The length rises to peak point and then drops with mass flow reduction, while the height steadily rises.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2002년도 유체기계 연구개발 발표회 논문집
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• pp.147-151
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• 2002

Cross flow fan system is widely used for various applications, especially for the air-moving device of heaters, air-conditioners, and air-curtains. Although there are efforts for the optimization of cross-flow fan flow path with different methods of approach, it is still being investigated by many researchers through experimentally and/or theoretically, because the flow pattern of the cross flow fan is not stereotyped. This paper presents some results from numerical experiments for the optimization of the flow path through a cross-flow fan to be applied to indoor wall-mounted room heater. Two dimensional analysis has been applied to a specific fan system including inlet and diffuser outlet. Flow characteristics art presented and discussed for two different flow path at three different operating conditions represented by rotational speed(800, 1,000, 1,200 rpm) of the In. According to the simulated results for the specific fan system under consideration, it could be found that the flow pattern resembles each other at different rotational speed (to say from 800 rpm to 1,200 rpm) for a fixed flow path, while the secondary flows mostly absorbs the speed effects. By changing the flow path significant increase in volume flow rate is estimated upto 2.65 at the same rotational speed. According to the present experience, fan flow path design can be performed more efficiently by incorporating this type of numerical experiments combined with the model tests.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2009년도 추계학술대회 논문집
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• pp.431-434
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• 2009

Conceptual study of an open-circuit type low-speed wind tunnel for test of wind turbine blade is conducted. The tunnel is constituted of a settling chamber, a contraction, closed and open test sections, a diffuser, two corners, a cross leg and a fan and motor. For the performance test, the closed test section width of 1.8 m, height of 1.8 m and length of 5.25 m is selected. The open test section with dimension width of 1.8 m, height of 1.8 m and length of 4.14 m is adopted for aeroacoustic test. The contraction ratio is 9 to 1 and maximum speed in the closed test section is 67 m/sec. Input power in the tunnel is about 238 kW and its energy ratio is 3.6. The wind tunnel designed in present study will be an effective tool in research and development of wind turbine.

• 한국유체기계학회 논문집
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• 제15권5호
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• pp.11-19
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• 2012

The main function of fuel cell manifold is to render reactants distribution as uniform as possible into a fuel cell stack. The purpose of this study is to numerically investigate the effects of stack manifold design on reactants distribution within a fuel cell stack. Four manifold designs with different manifold entrance shapes (expansion or diffuser) and different values of the extra width between the cell outer channel and manifold side wall are considered and applied to the fuel cell stack consisting of 50 cells. Since the fuel cell stack geometry involves several millions of grid points for numerical calculations, a parallel computing methodology is employed to substantially reduce the computational time and overcome the memory requirement. The numerical simulations are carried out and calculated results clearly demonstrate that both the manifold entrance shape and extra width have a substantial influence on manifold performance, controlling the degree of flow separation and entrance length for fully developed flow in the manifold channel. Finally, we suggest the optimum design of fuel cell manifold based on the simulation results.

• 대한기계학회논문집B
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• 제21권10호
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• pp.1273-1283
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• 1997

Experiments of shock wave/turbulent boundary layer interaction were conducted by using a supersonic wind tunnel. Nominal Mach number was varied in the range of 1.6 to 3.0 by means of different nozzles. The objective of the present study is to investigate the effects of boundary layer flow bleed on the interaction flow field in a straight tube. Two-dimensional slits were installed on the tube walls to bleed the turbulent boundary layer flows. The bleed flows were measured by an orifice. The ratio of the bleed mass flow to main mass flow was controlled within the range of 11 per cent. The wall pressures were measured by the flush mounted transducers and Schlieren optical observations were made for almost all of the experiments. The results show that the boundary layer flow bleed reduces the multiple shock waves to a strong normal shock wave. For the design Mach number of 1.6, it was found that the normal shock wave at the position of the silt was resulted from the main flow choking due to the suction of the boundary layer flow.