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김재홍,윤기범,박평원,김영진,전경민,김영태,김중환,곽호,구상완,송민석,유옥,지혜구,김동원,문상은,박영립,정승호,성범진,성순제,엄주용,황정열,이기홍,이주협,전태진 대한화학요법학회 1994 대한화학요법학회지 Vol.12 No.1
The prevalence of PPNG among pretreated gonorrhea cases isolated at the STD clinic of Choong-Ku Public Health Center in Seoul has been studied and reported annually since 1981. In 1991, 123 strains of N.gonorrhoeae were isolated, among which 58(47.1%) were PPNG. In 1992, 98 starains of N.gonorrhoeae were isolated, among which 51(52.0%) were PPNG. In all, 109(49.3%) strains were found to be PPNG among 221 strains isolated between 1991-1992. The prevalence of PPNG in Seoul showed increased tendency till 1989, thereafter, it has been stationary or slightly decreasing.
Prediction of Aerodynamic Loads for NREL Phase VI Wind Turbine Blade in Yawed Condition
Ki-Wahn Ryu,Seung-Hee Kang,Yun-Ho Seo,Wook-Ryun Lee 한국항공우주학회 2016 International Journal of Aeronautical and Space Sc Vol.17 No.2
Aerodynamic loads for a horizontal axis wind turbine of the National Renewable Energy Laboratory (NREL) Phase VI rotor in yawed condition were predicted by using the blade element momentum theorem. The classical blade element momentum theorem was complemented by several aerodynamic corrections and models including the Pitt and Peters’ yaw correction, Buhl’s wake correction, Prandtl’s tip loss model, Du and Selig’s three-dimensional (3-D) stall delay model, etc. Changes of the aerodynamic loads according to the azimuth angle acting on the span-wise location of the NREL Phase VI blade were compared with the experimental data with various yaw angles and inflow speeds. The computational flow chart for the classical blade element momentum theorem was adequately modified to accurately calculate the combined functions of additional corrections and models stated above. A successive under-relaxation technique was developed and applied to prevent possible failure during the iteration process. Changes of the angle of attack according to the azimuth angle at the specified radial location of the blade were also obtained. The proposed numerical procedure was verified, and the predicted data of aerodynamic loads for the NREL Phase VI rotor bears an extremely close resemblance to those of the experimental data.
KI-WAHN RYU,CHI-YONG PARK,HUINAM RHEE 한국원자력학회 2010 Nuclear Engineering and Technology Vol.42 No.1
Fluid-elastic instability and turbulence-induced vibration of steam generator U-tubes of a nuclear power plant are studied numerically to investigate the effect of design changes of support structures in the upper region of the tubes. Two steam generator models, Model A and Model B, are considered in this study. The main design features of both models are identical except for the conditions of vertical and horizontal support bars. The location and number of vertical and horizontal support bars at the middle of the U-bend region in Model A differs from that of Model B. The stability ratio and the amplitude of turbulence-induced vibration are calculated by a computer program based on the ASME code. The mode shape with a large modal displacement at the upper region of the U-tube is the key parameter related to the fretting wear between the tube and its support structures, such as vertical, horizontal, and diagonal support bars. Therefore, the location and the number of vertical and horizontal support bars have a great influence on the fretting wear mechanism. The variation in the stability ratios for each vibrational mode is compared with respect to Model A and Model B. Even though both models satisfy the design criteria, Model A shows substantial improvements over Model B, particularly in terms of having greater amplitude margins in the turbulence-excited vibration (especially at the inner region of the tube bundle) and better stability ratios for the fluid-elastic instability.
피치각 변화에 따른 헬리콥터 로터에서의 두께 및 하중소음 방사
유기완(Ki-Wahn Ryu) 한국항공우주학회 2007 韓國航空宇宙學會誌 Vol.35 No.10
정지비행시의 헬리콥터 로터 모형의 블레이드의 피치각 변화가 소음방사에 미치는 영향을 수치해석을 통해 파악하였다. 공력 자료는 비정상 패널법과 경험후류 방법을 이용하여 구하였으며, 0°에서 9°까지 등간격으로 1.5° 씩 피치각을 증가시키면서 블레이드 표면상의 공력 하중 분포를 얻어내었다. 수치해석을 통해 얻어낸 두께 소음은 피치각에 무관한 결과를 보였으나, 하중소음은 피치각이 1.5° 씩 증가할 때 마다 대략 3~4㏈A정도로 소음의 세기가 증가하는 경향을 보였으며, 이정도의 증가분은 소음이 더 커졌음을 감지할 수 있는 충분한 크기라 할 수 있다. 또한 하중소음의 방향성 결과로부터 블레이드의 윗면 보다는 아랫면에서의 소음의 세기가 더 크게 나옴을 알 수 있었다. Noises from the helicopter rotor model are calculated numerically at various pitch angles. The aerodynamic data are calculated by using prescribed wake model and unsteady panel method. The distribution of aerodynamic loads on the blade surface are obtained from 0° to 9° pitch angles with equiangular increments of 1.5°. Although thickness noise is not related to the change of pitch angles, loading noise level increases about 3~4㏈A every 1.5° increment of pitch angle. The additive noise level shows sufficient value to perceive the loudness. From the result of directivity pattern the sound level at the lower region of the blade disc plane is higher than that of the upper region.
Prediction of Aerodynamic Loads for NREL Phase VI Wind Turbine Blade in Yawed Condition
Ryu, Ki-Wahn,Kang, Seung-Hee,Seo, Yun-Ho,Lee, Wook-Ryun The Korean Society for Aeronautical and Space Scie 2016 International Journal of Aeronautical and Space Sc Vol.17 No.2
Aerodynamic loads for a horizontal axis wind turbine of the National Renewable Energy Laboratory (NREL) Phase VI rotor in yawed condition were predicted by using the blade element momentum theorem. The classical blade element momentum theorem was complemented by several aerodynamic corrections and models including the Pitt and Peters' yaw correction, Buhl's wake correction, Prandtl's tip loss model, Du and Selig's three-dimensional (3-D) stall delay model, etc. Changes of the aerodynamic loads according to the azimuth angle acting on the span-wise location of the NREL Phase VI blade were compared with the experimental data with various yaw angles and inflow speeds. The computational flow chart for the classical blade element momentum theorem was adequately modified to accurately calculate the combined functions of additional corrections and models stated above. A successive under-relaxation technique was developed and applied to prevent possible failure during the iteration process. Changes of the angle of attack according to the azimuth angle at the specified radial location of the blade were also obtained. The proposed numerical procedure was verified, and the predicted data of aerodynamic loads for the NREL Phase VI rotor bears an extremely close resemblance to those of the experimental data.