• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.743-750
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• 2008

Asymmetric tip clearance in an axial compressor induces pressure and velocity redistributions along the circumferential direction in an axial compressor. This paper presents the mechanism of the flow redistribution due to the asymmetric tip clearance with a simple numerical modeling. The flow field of a rotor of an axial compressor is predicted when an asymmetric tip clearance occurs along the circumferential direction. The modeling results are supported by CFD results not only to validate the present modeling but also to investigate more detailed flow fields. Asymmetric tip clearance makes local flow area and resultant axial velocity vary along the circumferential direction. This flow redistribution 'seed' results in a different flow patterns according to the flow coefficient. Flow field redistribution patterns are largely dependent on the local tip clearance performance at low flow coefficients. However, the contribution of the main flow region becomes dominant while the tip clearance effect becomes weak as the flow coefficient increases. The flow field redistribution pattern becomes noticeably strong if a blockage effect is involved when the flow coefficient increases. The relative flow angle at the small clearance region decreases which result in a negative incidence angle at the high flow coefficient. It causes a recirculation region at the blade pressure surface which results in the flow blockage. It promotes the strength of the flow field redistribution at the rotor outlet. These flow pattern changes have an effect on the blade loading perturbations. The integration of blade loading perturbation from control volume analysis of the circumferential momentum leads to well-known Alford's force. Alford's force is always negative when the flow blockage effects are excluded. However when the flow blockage effect is incorporated into the modeling, main flow effects on the flow redistribution is also reflected on the Alford's force at the high flow coefficient. Alford's force steeply increases as the flow coefficient increases, because of the tip leakage suppression and strong flow redistribution. The predicted results are well agreed to CFD results by Kang and Kang(2006).

• 대한기계학회논문집B
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• 제31권1호
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• pp.68-75
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• 2007

A three-dimensional computation is conducted to simulate a three-dimensional rotating stall in a low speed axial compressor. It is generally known that a tip leakage flow has an important role on a stall inception. However, almost of researchers have taken no interest in a role of the hub-comer-stall on the rotating stall even though it is a common feature of the flow in an axial compressor operating near stall and it has a large effect on the flows and loss characteristics. Using a time-accurate unsteady simulation, it is found that the hub-comer-stall may be a trigger to collapse the axisymmetric flows under high loads. An asymmetric disturbance is initially originated in the hub-comer-stall because separations are naturally unstable flow phenomena. Then this disturbance is transferred to the tip leakage flows from the hub-comer-stall and grows to be stationary stall cells, which adheres to blade passage and rotate at the same speed as the rotor. When stationary stall cells reach a critical size, these cells then move along the blade row and become a short-length-scale rotating stall. The rotational speed of stall cells quickly comes down to 79 percent of rotor so they rotate in the opposite direction to the rotor blades in the rotating frame.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.202-212
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• 2008

A three-dimensional computation was conducted to understand effects of the low Reynolds number on the loss characteristics in a transonic axial compressor, Rotor67. As a gas turbine becomes smaller in size and it is operated at high altitude, the operating condition frequently lies at low Reynolds number. It is generally known that wall boundary layers are thickened and a large separation occurs on the blade surface in axial turbomachinery as the Reynolds number decreases. In this study, it was found that the large viscosity did not affect on the bow shock at the leading edge but significantly did on the location and the intensity of the passage shock. The passage shock moved upstream towards leading edge and its intensity decreased at the low Reynolds number. This change had large effects on the performance as well as the internal flows such as the pressure distribution on the blade surface, tip leakage flow and separation. The total pressure rise and the adiabatic efficiency decreased about 3% individually at the same normalized mass flow rate at the low Reynolds number. In order to analyze this performance drop caused by the low Reynolds number, the total pressure loss was scrutinized through major loss categories such as profile loss, tip leakage loss, endwall loss and shock loss.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
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• pp.117-122
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• 2012

액체로켓 엔진의 시동과 종료 시, 터빈에 가해지는 열충격을 완화시키기 위해 초음속 충동형 터빈로터의 일체형 슈라우드를 여러 조각으로 분할하는 방법을 고안하였다. 구조해석 수행결과 슈라우드 분할은 동익의 허브와 팁에 나타나는 소성변형량을 크게 줄일 수 있는 것으로 나타났다. 그러나 슈라우드 분할은 의도하지 않은 누설손실로 인해 성능손실이 불가피하며 이에 대한 정량적인 성능감소를 측정하기 위해 다양한 슈라우드 분할 형상에 대해 시험을 수행하였다. 연구대상 터빈의 경우 슈라우드 분할 수를 최대로 할 경우 설계점 효율은 2.65% 비율로 감소하는 것으로 나타났다.

• Journal of Korean Neurosurgical Society
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• 제30권3호
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• pp.319-324
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• 2001

Objectives : The percutaneous vertebroplasty provides a good result in the treatment of osteoporotic vertebral compression fractures. But, the epidural leakage of polymethylmetacrylate(PMMA) after vertebroplasty may decrease the therapeutic effects because of the compression of thecal sac and/or nerve roots. The authors carried out a prospective study to evaluate the causative factors of epidural leakage of PMMA and to assess the influence on the outcome. Methods : This study involved 347 vertebral levels of compression fractures in 159 patients. Among these, the epidural leakages were identified in 92 vertebral levels(26.5%) in 64 patients(40.3%) on post-operative CT scan. Results : The incidence of epidural leakage of PMMA was significantly higher in the level above T7(p=0.001). The large amount of the injected PMMA and the use of an injector also increased the incidence(p=0.03 and p=0.045, respectively). The position of the needle tip in the vertebral body and the pattern of venous drainage did not influence. The immediate post-operative visual analogue scale(VAS) scores and facial scales(FS) were higher in the patients with epidural leakage(p=0.009). But there were no significant differences between the two groups after three months of operation(p=0.541). Conclusions : The incidence of epidural leakage of PMMA after percutaneous vertebroplasty appears to have relationship with the amount of PMMA and the levels injected. The epidural leakage of PMMA reduced the immediate therapeutic effects of vertebroplasty, but did not influence the late outcome. However, the epidural leakage should be avoided because of its potential neurological complications.

• International Journal of Aeronautical and Space Sciences
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• 제16권2호
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• pp.157-164
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• 2015

The present work performs three-dimensional flow calculations based on Reynolds Averaged Navier-Stokes (RANS) and Delayed Detached Eddy Simulation (DDES) to investigate the flow field of a transonic rotor (NASA Rotor 37) at near-stall condition. It is found that the DES approach is likely to predict well the complex flow characteristics such as secondary vortex or turbulent flow phenomenon than RANS approach, which is useful to describe the flow mechanism of a transonic compressor. Especially, the DES results show improvement of predicting the flow field in the wake region and the model captures reasonably well separated regions compared to the RANS model. Besides, it is discovered that the three-dimensional vortical flows after the vortex breakdown from the rotor tip region are widely distributed and its vortex structures are clearly present. Near the rotor leading edge, a part of the tip leakage flows in DES solution spill over into next passage of the blade owing to the separation vortex flow and the backflow is clearly seen around the trailing edge of rotor tip. Furthermore, the DES solution shows strong turbulent eddies especially in the rotor hub, rotor tip section and the downstream of rotor trailing edge compared to the RANS solution.

• Restorative Dentistry and Endodontics
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• 제27권3호
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• pp.270-276
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• 2002

치근단 수술시 구동형 수술현미경과 미세수술기구들이 사용됨에 따라 치근단 절제술 후 역충전와동의 효과적인 형성 및 충전을 위해 새로운 초음파기구가 개발되었다 따라서 본 연구에서는 최근 상품화되어 사용되고 있는 초음파기구중 신속하게 역충전와동을 형성할 뿐아니라 충분한 깊이를 제공하여 역충전재료의 변연누출 감소에 효과적인 것으로 알려져 있는 3종의 초음파기구를 사용하여 역 충전와동을 형성 한 후 SuperEBA로 충전하여 그 변연누출을 비교하였다. 모두 56개의 근첨형성이 완료된 단근치를 선택하여 Profile .06를 사용하여 근관형성한 후 음성대조군 2개를 제외한 54개의 치아를 수직가압법으로 충전하였다. 근단부 3mm를 절제한 뒤 KaVo Isthmus, KaVo T-shape 그리고 KiS tip을 각각 18개의 치아에 사용하여 역충전와동을 형성하고 그중 각각 2개의 양성대조군 치아를 제외한 나머지 치아에 SuperEBA로 충전하였다. 각치아는 1% methylene blue dye에 침윤시켜 1주일 후 종절단하여 그 색소침투정도를 측정, 비교하였다. 실험결과 측정된 평균 변연누출은 KaVo Isthmus가 $1.5\pm$1.4mm, KaVo T-shape이 1.7$\pm$1.2mm이고 KiS tip은 1.1$\pm$0.7mm 이었으며, 통계적으로 유의할만한 차이는 없었다. 따라서 초음파기구를 사용한 역충전와동의 임상시술 성공여부는 술자의 편의도와 임상적 사용시 조작능력에 달려 있는 것으로 사료된다.

• 대한기계학회논문집B
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• 제25권3호
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• pp.414-421
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• 2001

The present study is conducted to investigate the local heat/mass transfer characteristics on the shroud with blade tip clearances. The relative motion between blade and shroud has little influence on the overall heat transfer characteristics, except some local effects. Therefore, the relative motion between the blade and shroud is neglected in this study. A naphthalene sublimation method is employed to determine the detailed local heat/mass transfer coefficients on the surface of the shroud. The tip clearance is changed from 0.66% to 2.85% of the blade chord length. The flow enters the gap between the blade tip and shroud at the pressure side due to the pressure difference. Therefore, the heat/mass transfer characteristics on the shroud are changed significantly from those with endwall. At first, high heat/mass transfer occurs along the profile of blade at the pressure side due to the entrance effect and acceleration of the gap flow. Then, the heat/mass transfer coefficients on the shroud increase along the suction side of the blade because tip leakage vortices are generated and interact with the main flow. The results show that the heat/mass transfer characteristics are changed largely with the gap distance between the tip of turbine blade and the shroud.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제29회 추계학술대회논문집
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• pp.305-310
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• 2007

엇회전식 축류팬의 복잡한 유동특성을 이해하고 설계, 공력 해석 및 소음 특성 예측에 활용될 수 있는 3차원 비정상 유동장을 측정하였다. 엇회전식 축류팬의 3차원 비정상 유동장은 작동 영역인 설계점에서 $45^{\circ}$ 경사 열선을 이용하여 전단 동익의 전방, 전단 동익과 후단 동익 사이 그리고 후단 동익의 후방의 수직 유로 단면에서 측정되었다. 엇회전식 축류팬의 전단 동익과 후단 동익에 의해 발생되는 후류, 팁 와류 및 팁 누설 유동의 비정상 특성을 속도 벡터와 속도 윤곽을 통해 나타내었다.

• Journal of Minimally Invasive Surgery
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• 제21권4호
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• pp.180-182
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• 2018

The frequency of anastomotic leakage after gastrectomy is reported to be 0.9~8%. To reduce deleterious outcomes of anastomotic leakage, we devised the "Omental Free-shaped Flap Reinforcement On Anastomosis and Dissected area" procedure not only to prevent fatal complications following anastomotic leakage but also to promote vascularity of anastomoses and other expected oncological benefits. This video illustrates the surgical procedure following a totally laparoscopic distal gastrectomy. After completion of the anastomosis, the remaining omentum was mobilized upward and divided into two sections. We placed the left section of the omental flap under the anastomosis between the stomach and pancreas. Finally, we grasped and curved the tip of the section to cover the anastomosis from behind, and we placed the right section of the omental flap above the anastomosis. These two sections were approximated with clips to the anterior wall of the stomach. The patient was discharged without complications.