• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 추계학술대회
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• pp.1383-1388
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• 2004

The flow characteristics in the blade passage of a low speed axial flow fan have been investigated by experimental analysis using a rotating hot-wire sensor for design and off-design operating conditions. The results show that the tip leakage vortex is moved upstream when flow rate is decreased, thus disturbing the formation of wake flow near the rotor tip. The tip leakage vortex interfaces with blade pressure surface, and results in high velocity fluctuation near the pressure surface. From the relative velocity distributions near the rotor tip, large axial velocity decay is observed at near stall condition, which results in large blockage compared to that at the design condition. Througout the flow measurements using a quasi-orthogonal measuring points to the tip leakage vortex, it is noted that the radial position of the tip leakage vortex is distributed between 94 and 96 percent span for all flow conditions. High spectrum density due to the large fluctuation of the tip leakage vortex is observed near the blade suction surface below the frequency of 1000 Hz at near stall condition.

• 대한기계학회논문집B
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• 제27권1호
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• pp.84-94
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• 2003

It is known that tip clearance flows reduce the pressure rise, flow range and efficiency of the turbomachinery. So, the clear understanding about flow fields in the tip region is needed to efficiently design the turbomachinery. The Navier-Stokes code with the proper treatment of the boundary conditions has been developed to analyze the three-dimensional steady viscous flow fields in the transonic rotating blades and a numerical study has been conducted to investigate the detail flow physics in the tip region of transonic rotor, NASA Rotor 67. The computational results in the tip region of transonic rotors show the leakage vortices, leakage flow from pressure side to suction side and their interaction with a shock. Depen ding on the operating conditions, toad distributions and the position of shock-wave on the blade surface are very different close to the blade tip of the transonic compressor rotor. The load distribution and the shock-wave position close to the blade tip had the close relationship with the starting position of leakage vortex and the direction of leakage flow.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.91-98
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• 2017

Performance of a low speed axial compressor is enhanced through a proper configuration of blade row tip injection and casing treatment of groove type. Air injectors were mounted evenly spaced upstream of the blade row within the casing groove and were all aligned parallel to the compressor axis. The groove, which covers all the blade tip chord length, extends all-round the casing circumference. Method of investigation is based on solution of the unsteady form of the Navier-Stokes equations utilizing $k-{\omega}$ SST turbulence model. Extensive parametric studies have been carried out to explore effects of injectors' flow momentums and yaw angles on compressor performance, while being run at different throttle valve setting. Emphasis has been focused on situations near to stall condition. Unsteady numerical analyses for untreated casing and no-injection case for near stall condition provided to discover two well-known criteria for spike stall inception, i.e., blade leading edge spillage and trailing edge back-flow. Final results showed that with only 6 injectors mounted axially in the casing groove and at yaw angle of 15 degrees opposite the direction of the blade row rotation, with a total mass flow rate of only 0.5% of the compressor main flow, surprisingly, the stall margin improves by 15.5%.

• 한국항공우주학회지
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• 제31권7호
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• pp.69-74
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• 2003

Vane tip 개념을 도입하여 소음 특성을 개선하도록 설계된 차세대 로터 블레이드(NRSB-I)의 공력 성능을 기존의 BERP 블레이드와 비교하기 위하여, 제자리 비행에 대한 점성 압축성 계산을 수행하였다. 깃끝 영역의 면적감소에 의하여 설계된 로터 블레이드의 절대 추력이 6-7% 정도 감소하지만, 동력계수의 감소폭이 더 크기 때문에 제자리 비행 성능상의 손실은 거의 없는 것으로 파악되었다. 또한, 깃끝 절단부에서 발생한 와류는 블레이드 표면을 지날 때 확산에 의하여 그 강도가 현저하게 약화되므로, 설계요구조건을 만족시키기 위해서는 절단부 위치에 펜스가 필요함을 확인할 수 있었다.

• 한국유체기계학회 논문집
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• 제15권3호
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• pp.5-11
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• 2012

This study is to develop a 1kW-class horizontal axis wind turbine(HAWT) rotor blade which will be applicable to relatively low wind speed regions in southwest islands in Korea. Shape design of 1kW-class small wind turbine rotor blade is carried out using a blade profile with relatively high lift to drag ratio by blade element momentum theory(BEMT). Aerodynamic analysis on the newly designed rotor blade is performed with the variation of tip speed ratio. Power coefficient and pressure coefficient of the designed rotor blade are investigated according to tip speed ratio.

• International Journal of Aeronautical and Space Sciences
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• 제1권1호
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• pp.92-102
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• 2000

In this study, the 750kW medium scale composite blade for the horizontal axis wind turbine system was designed and manufactured, and it was tested and evaluated by the specific structural test rig. In the test, it was found that local bucklings at the trailing edge of the blade and excessive deflections at the blade tip were happened. In order to solve these problems, the design of blade structure was modified. After improving the design, the abrupt change of deflection at the blade tip was reduced by smooth variation of the spar thickness and the local buckling was removed by extending the web length. The modified design was analyzed by the FEM, the safety and stability of the blade structure. And Fatigue life over 20 years was confirmed by using S-N linear damage method, Spera's method, etc.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.619-622
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• 2002

It has been recognized that the flow in the blade passage of an axial turbomachinery rotor is very complex and is influenced by various flow phenomena, of which the tip leakage flow passing through the gap between rotor blade tip and casing plays a significant role. The losses produced due to the existence of the clearance have been known to be a large contributor of the rotor overall losses. Despite several experimental studies on non-rotating blade in the cascade configuration, and on actual rotating blades, the detailed nature of the complex flow phenomena associated with tip leakage, however, remains largely unresolved. Thus, a single-stage compressor test rig was built and measurements were taken at upstream and downstream of the rotor of this compressor at the aerodynamics laboratory of University of New South Wales. A five-hole probe and a hot-wire probe were used to measure mean and fluctuating flow parameters. The results show that tip leakage losses rise rapidly beyond tip gap of 0.01 Furthermore, the present project also identifies the regions in the wake behind the rotor of the axial compressor where such losses are concentrated. These results should be useful in the better design of rotors for improved performance of axial compressor.

• 농업과학연구
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• 제11권2호
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• pp.264-269
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• 1984

단면(單面)의 로우터리 경운(耕耘)날이 양면(兩面)보다 경운소요(耕耘所要)토오크를 절감(節減)시키는 데 효과적(效果的)이란 결과(結果)에 대(對)하여는 앞서의 연구(硏究)에서 보고(報告)한 바 있으며, 본(本) 연구(硏究)는 경운작업(耕耘作業)에 의(依)한 날의 마모과정중(磨耗過程中) 양(兩), 단면(單面) 형상(形狀)의 경운(耕耘)날이 경운소요(耕耘所要)토오크의 절감효과(節減效果)가 지속(持續)되는가를 구명(究明)하기 위(爲)하여 포장실험(圃場實驗)을 실시(實施)하였다. 양(兩), 단면(單面)의 공시(供試)날은 동일(同一) 로우터리 축(軸)에 부착(附着)시켜 미경운토양(未耕耘土壤)에서 포장작업(圃場作業)을 실시(實施)하여 매(每) 3시간(時間)마다 마모량(磨耗量)을 측정(測定)하였으며, 계량(計量)한 날의 경운소요(耕耘所要)토오크는 실험실(實驗室)에서 Soil bin system 을 이용(利用)하여 측정(測定)하였으며, 분석(分析) 결과(結果)를 요약(要約)하면 다음과 같다. 1. 로우터리 경운작업(耕耘作業)을 실시(實施)하는 동안 날의 단면형상(斷面形狀)의 원형(原形)은 변화(變化)하지 않았으며, 단면(單面)인 날이 양면(兩面)보다 전(全) 내용시간(耐用時間) 동안 최대경운소요(最大耕耘所要)토오크는 5~10%, 평균경운소요(平均耕耘所要)토오크는 3~15% 절감(節減)하는 것으로 분석(分析)되었다. 2. 일반적(一般的)으로, 경운소요(耕耘所要)토오크는 경운(耕耘)날의 형상(形狀)이 유지(維持)되는 12시간(時間)까지는 감소(減少)하였으나, 그 후(後)에는 날의 tip형상(形狀)의 변형(變形)에 의(依)하여 증가(增加)하는 것으로 나타났다. 이것은 날의 tip형상(形狀)이 경운소요(耕耘所要)토오크에 영향(影響)을 미치는 요인(要因)이라고 분석(分析)할 수 있으며, 이에 대(對)한 연구(硏究)는 계속(繼續)되어져야 할 것으로 사료(思料)된다.

• 소음진동
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• 제10권2호
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• pp.229-239
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• 2000

To reduce the drag rise on the advancing helicopter rotor blade tips, the tip of the blade is modified to have sweep, anhedral and pretwist. The equations of motion of rotor blade with these tip angles were derived using Hamilton principle, programmed using FORTRAN and named as ARMDAS(Advanced Rotorcraft Multidisplinary Design and Analysis System). Rotating frequency analysis of rotor blades with swept tipe was performed that is necessary in conceptual and preliminary design phases of the helicopter design. Vibration analysis of non-rotating blades was also accomplished and compared with MSC/NASTRAN resutls for the basis of comparison with the vibration test data. The rotating frequency analysis of blades with an actual rotor blade data was also performed to verify coded program and to check the possibility of a resonance of an actual rotor blade at the specific rotating speed.

• 대한설비공학회:학술대회논문집
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• 대한설비공학회 2009년도 하계학술발표대회 논문집
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• pp.1465-1469
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• 2009

Darrieus wind turbine blade is one of the vertical wind power system in which the lift of blade is used. In the calculation of wind power for the type of that, the multiple streamtubes method is known as an effective method. But it has big difference in the region of higher tip speed ratio because the incoming air velocity is used in the calculation of lift. The incoming air velocity is reduced from inlet to outlet continually by transferring energy to the wind blade. In this study, the air velocity on the blade, which is called blade velocity, is obtained with newly developed algorithm and used to determine the lift. And it is verified that applying blade velocity on the lift calculation cause the power prediction to improve dramatically in the region of higher tip speed ratio.