• Journal of Advanced Marine Engineering and Technology
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• 제32권5호
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• pp.698-706
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• 2008

Performance improvement of Small hydro turbine is a very important subject to solve in the stage of introduction and development of the turbine. Cross-flow hydro turbine should be also studied more in detail for the turbine performance in order to extend the sites of application. In order to improve the turbine performance, the effect of the turbine shape on the turbine performance should be examined. Therefore, the effect of runner blade number on the turbine performance is investigated by use of a commercial CFD code. The results show that runner blade number gives remarkable effect on the efficiency and output power of the turbine. Pressure on the surface of the runner blade changes considerably by the blade number at Stage 1, but relatively small change of velocity distribution occurs in the flow passage.

• 대한조선학회논문집
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• 제46권6호
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• pp.569-577
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• 2009

As the scale factor of model propellers utilized in cavitation test is about 40, it is difficult to find out practical countermeasures against the small area erosions on the blade tip region throughout model erosion tests. In this study, a partial propeller blade model was used for the observation of cavitation pattern for the eroded propeller. A partial propeller blade model was manufactured from 0.7R to tip with expanded profile and with adjustable device of angle of attack. Reynold's number of a partial propeller blade model is 7 times larger than that of a model propeller. Also, anti-singing edge and application of countermeasures to partial propeller blade model which produced in large scale can be more practical than a model propeller. For the observation of cavitation at high Reynold's number, high speed cavitation tunnel was used. To find out the most severe erosive blade position during a revolution, cavitation observation tests were carried out at 5 blade angle positions.

• International Journal of Aeronautical and Space Sciences
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• 제16권4호
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• pp.500-509
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• 2015

The numerical simulation of two-dimensional moving blade row interactions is conducted by CFD means to investigate the interactions between the front and rear propeller in a stratospheric airship contra-rotating open propeller configuration caused by different rotational speeds. The rotational speed is a main factor to affect the propeller Reynolds number which impact the aerodynamic performance of blade rows significantly. This effect works until the Reynolds number reaches a high enough value beyond which the coefficients become independent. Additionally, the interference on the blade row has been revealed by the investigation. The front blade row moves in the induced-velocity field generated by the rear blade row and the aerodynamic coefficients are influenced when the rear blade row has fast RPMs. The rear blade row moving behind the front one is affected directly by the wake and eddies generated by the front blade row. The aerodynamic coefficients reduce when the front blade row has slow RPMs while increase when the front blade row moves faster than itself. But overall, the interference on the front blade row due to the rear blade row is slight and the interference on the rear blade row due to the front blade row is much more significant.

• 한국유체기계학회 논문집
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• 제18권4호
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• pp.56-61
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• 2015

It is important requirement to properly evaluate the aerodynamic performance and characteristics during preliminary design of a centrifugal compressor. In this study the centrifugal compressor was calculated for variations of mass flow and blade Mach number by means of single passage steady state. A lot of quantitative performance values were obtained and through the obtained values the aerodynamic performance characteristics of designed impeller and vaned diffuser were investigated. The results were classified by blade Mach number to analyze characteristics and the aerodynamic performance was examined at choke of impeller, diffuser and separation of diffuser.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2004년도 유체기계 연구개발 발표회 논문집
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• pp.390-395
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• 2004

The characteristics of the circular arc shaped multi-blade windmil are investigatedl. The prototypical windmill was tested in the laboratory at wind tunnel speeds of 5.5, 9.4m/s. and the model windmill was also tested in the laboratory, The power and torque coefficients were studied as functions of the blade section, the aspect ratio for blade diameter and windmill radius(M = 0.3, 0.5, 0.7), the number of blades and finally the tip-speed ratio. The analysis of the experimental results for the model windmill showed that there is the highest revolutions per minute(R.P.M) at the circular arc shaped multi-blade windmill having the blade number 10, aspect ratio(M = 0.7). and the results for the prototypical windmill showed that the power coefficient increased to a maximum value and then decreased again with an increase in the tip speed ratio, while the torque coefficient decreased directly with an increase in the tip speed ratio Finally, the experimental results were compared with the Savonius blade. the maximum power coefficient for the arc shaped blade was greater than for the Savonius blade and occured at a lower tip speed ratio.

• 한국산림과학회지
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• 제89권5호
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• pp.666-676
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• 2000

굴참나무 천연집단의 형태적 변이(엽형 특성)를 연구하기 위하여 위도, 경도, 해발고 및 지리적 특성을 고려하여 19개 집단을 선발하였다. 각 집단별로 30개체를 대상으로 개체목당 수관 1/3 하단부에서 60개의 엽을 고르게 채집하여 엽신장, 최대엽폭, 엽맥수 및 엽병장을 조사한 후 그 값을 이용하여 엽신장/최대엽폭, 엽신장/엽병장, 상1/3폭/최대엽폭, 상1/3폭/하1/3폭 및 엽병장/엽맥수에 대한 형상비를 계산하여 엽형 특성에 대한 변이를 조사한 결과는 다음과 같다. 1. 엽신장/최대엽폭, 엽신장/엽병장, 엽병장/엽맥수, 상1/3폭/최대엽목, 상1/3폭/하1/3폭, 엽병장 및 엽맥수에 대한 변이는 집단간 및 집단내의 개체간에 고도의 유의적인 차이를 보였다. 특히, 분산기여도는 집단간보다 집단내의 개체간에 큰 것으로 나타나, 굴참나무의 연구는 집단보다 개체에 의한 연구가 바람직할 것으로 보여진다. 2. 엽형특성에 대한 주성분 분석은 첫 두 주성분까지의 적재 가여율이 80.5%로 굴참나무 엽형특성 분류에 중요한 정보를 주는 요인이었다. 각 인자별 기여도에 있어서는 제1주성분에서 엽병장/엽맥수 및 엽병장, 제2주성분에서 상1/3폭/최대엽폭, 상1/3폭/하1/3폭 및 엽맥수 인자가 높은 기여도를 나타냈다. 3. 위도, 경도 및 해발고에 따른 엽형특성에 대한 지리적 변이는 위도에 있어 엽신장/최대엽폭 및 엽신장/엽병장에 대해서는 정의 상관을 나타내었으며, 나머지 특성(엽병장/엽맥수, 상1/3폭/최대엽목, 상1/3폭/하1/3폭, 엽병장 및 엽맥수)들에 대해서는 부의 상관을 나타내었다. 그러나 경도와 해발고는 위도와 반대의 경향을 나타내었다. 4. 군집분석(Complete linkage cluster)한 결과는 거리지수 1.6에서 2개의 그룹 즉, I그룹(Pop. 1, 4, 5 및 13)과 II그룹(Pop. 2, 3, 6, 7, 8, 9, 10, 11, 12, 14, 15, 16, 17, 18 및 19)으로 나뉘었으며, 거리지수 1.3에서는 II그룹이 다시 Pop. 3, 7, 10, 14, 15 및 17의 군집(II-1)과 Pop. 2, 6, 8, 9, 11, 12, 16, 18, 19의 군집(II-2)으로 나뒤어 총 3그룹으로 분리되었다. 대체적으로 이것은 사면의 방향에 대하여 I그룹은 북동면에, II-1그룹은 남동면에, 그리고 II-2그룹은 남서면에 집단이 위치하고 있어 환경조건이나 입지조건의 차이에 의하여 일어난 자연도태의 결과로 집단간 차이를 보이는 것으로 사료된다.

• International Journal of Fluid Machinery and Systems
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• 제9권4호
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• pp.313-324
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• 2016

Surrogate model based shape optimization methodology to enhance performance of a centrifugal pump has been implemented in this work. Design variables, such as blade number and blade angles defining the pump impeller blade shape were selected and a three-level full factorial design approach was used for efficiency enhancement. A three-dimensional simulation using Reynolds-averaged Navier Stokes (RANS) equations for the performance analysis was carried out after designing the geometries of the impellers at the design points. Standard $k-{\varepsilon}$ turbulence model was used for steady incompressible flow simulations. The optimized impeller incurred lower losses by shifting the trailing edge towards the impeller pressure side. It is observed that the surrogates are problem dependent and most accurate surrogate does not deliver the best design always.

• 대한조선학회논문집
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• 제50권5호
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• pp.282-290
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• 2013

The effects of the combination of blade number for forward and after propeller on the propeller shaft forces of a contra-rotating propeller (CRP) system are presented in the paper. The research is performed through the numerical simulations based on the Reynolds-Averaged Navier-Stokes equations (RANS). The simulation results of the present method in open water condition are validated comparing with the experimental data as well as the other numerical simulation results based on the potential method for 4-0-4 CRP (3686+3687A) and 4-0-5 CRP (3686+3849) of DTNSRDC. Two sets of CRP are designed and simulated to study the effect of the combination of blade number in behind-hull condition. One set consists of 3-blade and 4-blade, while the other is 4-blade and 4-blade. A full hull body submerged under the free surface is modeled in the computational domain to simulate directly the wake field of the ship at the propeller plane. From the simulation results, the fluctuations of axial force and moment are dominant in the case of same blade numbers for forward and after propellers, whereas the fluctuations of horizontal and vertical forces and moments are very large in the case of different blade numbers.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2002년도 유체기계 연구개발 발표회 논문집
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• pp.227-233
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• 2002

It is common for highly loaded supersonic stage to have very high relative inlet Mach number. To get this level of inlet Mach number, rotor blade outer diameter or rotational speed should be increased. In the case of commercial turbo-fan engine, it is preferred to make the rotor blade outer diameter large than increasing the rotational speed. But, for multi-stage fan of military engines, overall diameter is often restricted and they are apt to increase the rotational speed. With high rotational speed, relative inlet Mach number is likely to be well supersonic over the entire rotor blade span and the characteristic of the stage is affected with meridional shape of the stage, especially at near hub or tip. In this paper, the aerodynamic performance of two different hub surface shape is compared and it's merit and demerits were discussed.

• 한국습지학회지
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• 제25권3호
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• pp.176-183
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• 2023

본 연구는 자유수면 아래 원통형 와류발생부에서 와류 수차 성능에 대한 블레이드 수가 미치는 영향을 이해하는 것이다. 동일한 블레이드 형상을 사용하여 상대 와류 수심비(y/h_v) 0.065 ~ 0.417 범위에 설치된 2개, 3개, 4개, 5개 및 6개의 블레이드로 마이크로 와류 수차의 성능을 실험하였다. 연구 결과로서 블레이드 수가 증가함에 따라 회전수, 전압, 전류 및 출력이 유속 0.7 m/s 이하일 때 상대 와류 수심비 0.065와 0.111 지점에서 증가한다. 5개 블레이드 수차의 평균 출력은 다른 블레이드 수보다 높게 나타난다. 오리피스 근처에 설치된 직경 130 mm인 4개의 블레이드 수차의 성능이 와류발생부에서 동일한 수의 직경 220 mm인 블레이드 수차보다 높다.