• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.586-591
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• 2003

The present study addresses experimental results to investigate the effect of the jet supply chamber configuration on the sonic/supersonic swirling jets, as the case study. The experiment is carried out using the convergent nozzle with a various different chamber configurations upstream the nozzle throat, which is composed of four tangential inlet holes for the swirling flows. The jet pressure ratio is varied between 3.0 and 7.0. The sonic/supersonic swirling jet flows are specified by the pitot impact and static pressure measurements and visualized using the Shadowgraph method. The results show that the major structures of the sonic/supersonic swirling jet are strongly influenced by the jet supply chamber.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.790-798
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• 2008

Counter-rotating axial flow fan(CRF) consists of two counter-rotating rotors without stator blades. CRF shows the complex flow characteristics of the three-dimensional, viscous, and unsteady flow fields. For the understanding of the entire core flow in CRF, it is necessary to investigate the three-dimensional unsteady flow field between the rotors. This information is also essential to improve the aerodynamic characteristics and to reduce the aerodynamic noise level and vibration characteristics of the CRF. In this paper, experimental study on the three-dimensional unsteady flow of the CRF is performed at the design point(operating point). Flow fields in the CRF are measured at the cross-sectional planes of the upstream and downstream of each rotor using the $45^{\circ}$ inclined hot-wire. The phase-locked averaged hot-wire technique utilizes the inclined hot-wire, which rotates successively with 120 degree increments about its own axis. Three-dimensional unsteady flow characteristics such as tip vortex, secondary flow and tip leakage flow in the CRF are shown in the form of the axial, radial and tangential velocity vector plot and velocity contour. The phase-locked averaged velocity profiles of the CRF are analyzed by means of the stationary unsteady measurement technique. At the mean radius of the front rotor inlet and the outlet, the phase-locked averaged velocity profiles show more the periodical flow characteristics than those of the hub region. At the tip region of the CRF, the axial velocity is decreased due to the boundary layer effect of the fan casing and the tip vortex flow. The radial and the tangential velocity profiles show the most unstable and unsteady flow characteristics compared with other position of rotors. But, the phase-locked averaged velocity profiles of the downstream of the rear rotor show the aperiodic flow pattern due to the mixture of the front rotor wake period and the rear rotor rotational period.

• 한국수자원학회논문집
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• 제50권2호
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• pp.129-138
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• 2017

대심도 저류 및 배수터널은 기 개발된 도시의 부족한 배수관망 능력을 보강하기 위하여 지하에 설치하는 대규모 도시홍수 배제 시설물로 원활한 홍수 유입을 위해 적정한 규모의 수직유입구가 요구되어진다. 접선형 수직유입구 설계 시 유입구의 능력을 평가하는 중요인자로 Yu and Lee(2009)가 지배유량개념을 소개하였는데, 본 연구에서는 서울시에 설치하고자 하는 신월빗물저류배수시설의 수직유입구 3개소를 대상으로 수리모형실험을 실시하고 제안된 지배유량 개념의 적정성을 평가하였다. 지배유량 이론식($Q_{cp}$)을 이용하여 실제 측정된 지배유량($Q_{cm}$)과 비교 분석하였는데, 그 결과 이론식 대비 66~69%로 이론식이 지배유량을 과대 산정하는 것으로 평가되었다. 지배유량 이론식의 과대산정 원인을 분석하기 위하여 Yu and Lee (2009)가 사용한 자료들과 본 연구에서 측정된 자료들을 활용하여 지배유량비($Q_{cm}/Q_{cp}$)를 3가지 영역으로 분류하고 각 인자에 대한 민감도 분석을 실시하였다. Yu and Lee (2009)가 제안한 지배유량식은 접선형 수직유입구 설계인자인 B, z, ${\beta}$, e/B에 대한 영향만 고려하였으나 ${\theta}$, L과 연계된 변수들로 복합적으로 고려하는 식의 개선이 필요한 것으로 판단된다.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2010년도 춘계학술대회 초록집
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• pp.192.1-192.1
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• 2010

Micro hydraulic turbines take a growing interest because of its small and simple structure as well as high possibility of applying to micro and small hydropower resources. The differential pressure exiting within the city water pipelines can be used efficiently to generate electricity like the energy generated through gravitational potential energy in dams. In order to reduce water pressure at the inlet of water cleaning centers, pressure reducing valves are used widely. Therefore, pressure energy is wasted. Instead of using the pressure reduction valve, a micro counter-rotating hydraulic turbine can be replaced to get energy caused by the large differential pressure found in the city water pipelines. In this paper, detail studies have been carried out to acquire basic design data of micro counter-rotating hydraulic turbine, output power, head, and efficiency characteristics on various number of runner vane. Moreover, the influences of pressure, tangential and axial velocity distributions on turbine performance are also investigated.

• 한국유체기계학회 논문집
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• 제3권2호
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• pp.7-14
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• 2000

For a given axial turbine blade, reverse design method is developed to improve blade efficiency, optimize blade profile, or repair parts etc. In this process, design parameters for designing axial turbine blade are induced. The induced design parameters are as follows; ellipse at leading edge, radios of trailing edge, axial chord, tangential chord, wedge angle at the inlet, and unguided turning angle. Suction and pressure surfaces of turbine blade are described by cubic polynomials. Two sample blades we chosen and their blade profiles are measured at the mean radius. Values of design parameters for sample blades are obtained by the reverse design method. Re-designed blade profiles using calculated design parameters are compared with the measured data, and they show good agreement. So, the developed design method could be applied to design general turbine blades. Various blade shapes are designed, and they show that designed blade profiles can be adjusted by controlling design parameters.

• Journal of Mechanical Science and Technology
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• 제17권10호
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• pp.1520-1532
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• 2003

An experiment was performed to obtain the local heat transfer coefficient and Nusselt number in a circular duct with a 180$^{\circ}$ bend for Re=6 x 10$^4$, 8 x 10$^4$ and 1 x 10$\^$5/ under swirling flow and non-swirling flow conditions. The test tube with a circular section was made from stainless steel having a curvature ration of 9.4. Current heat flux of 5.11 kW/㎡ was applied to the test tube by electrical power and the swirling motion of air was produced by a tangential inlet to the pipe axis at 180$^{\circ}$. Measurements of local wall temperatures and the bulk mean temperatures of air were made at four circumferential positions at 16 stations. The wall temperatures showed a reduced distribution curve at the bend for the non-swirling flow, but this effect did not appear for the swirling flow. The Nusselt number distributions for the swirling flow, which was calculated from the measured wall and the bulk temperatures, were higher than that of the non-swirling flow. The average Nusselt number of the swirling flow increased by about 90-100%, compared to that of the non-swirling flow. The Nu/Nu$\_$DB/ values at the 90$^{\circ}$ station for non-swirling flow and swirling flow were approximately 2.5 and 4.8 at Re=6x10$^4$ respectively. The values agree well with Said's results for non-swirling flow.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.387-391
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• 2009

소형 무인항공기 추진용 덕티드 팬의 실험적 연구가 수행되었다. 이 논문에서는 덕티드 팬의 입구, 로터 뒤, 스테이터 뒤에서 허브에서 팁 방향으로 $45^{\circ}$ 경사 열선으로 측정하여 비정상 3차원 유동 특성을 연구하였다. 경사열선 요각을 고정시켜 데이터를 획득하였다. 이 데이터는 위상평균기법을 이용하여 평균되었다. 이 데이터는 Newton-Rhapson 수치해법을 통하여 3개의 비선형 연립방정식을 풀었다. 축 방향, 반경 방향 그리고 원주 방향 속도의 윤곽을 통해 팁 후류, 이차유동 그리고 팁 누설유동과 같은 유동 특성을 확인 하였다.

• 한국가스학회지
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• 제22권3호
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• pp.7-12
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• 2018

화석연료를 연소할 때 연소로 내의 고온의 온도 분위기에서 열적 질소산화물이 발생하게 된다. 연소기기에서 질소산화물을 저감하기 위한 여러 가지 방법 중에 배기가스 재순환 방법이 널리 쓰이고 있다. 본 연구에서는 배기가스 재순환 배관에 코안다 노즐을 사용하고 양쪽 출구가 트인 재순환하는 버너에 대하여 냉간 유동 특성을 전산유체해석을 통해 살펴보았다. 재순환 배관이 원통 버너의 접선방향으로 설치되어 있어서 버너 내부에서 선회유동이 형성되어 원통 버너 중심 부분에 역류가 생기는 현상을 관찰하였으며 이는 한쪽이 막힌 재순환 버너와 유사한 경향임을 확인 하였다. 본 연구로부터 양쪽 출구가 트인 재순환 버너에서 재순환 유입량은 한쪽이 막힌 버너보다 약 5% 증가하는 것을 확인하였고 양쪽 트인 버너에서 배기가스 재순환 배관의 유입구 위치의 출구에서는 전체 영역에서 유입 유동이 형성되고 반대편의 출구에서는 총 유량은 배출되지만 원통의 가운데 부분은 역류가 일어나는 것을 확인하였다. 배출되는 출구에서 배출되는 유량은 유입되는 출구에서의 유입량보다 3~5배 유량이 크게 나타났다.

• 대한기계학회논문집B
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• 제26권6호
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• pp.805-810
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• 2002

Development of a small gas-turbine combustor for 100㎾ class APU(Auxiliary Power Unit) has been performed. This combustor is a reverse-annular type and has a tangential swiller in the liner head to improve the fuel/air mixing and flame stability. Three main and three pilot fuel injectors of the simplex pressure-swirl type are used. The performance target at the design condition includes a turbine inlet temperature of l170k, a combustion efficiency of 99%, a pattern factor of 30%, and an engine durability of 3000 hours. Under developing the combustor, we conducted the performance test of our first prototype(TS1) with some variants. As a result of the test, the performance targets of the combustor are satisfied except that the pattern factor is about 4% higher than the target value. Therefore, the second prototype(TS2) was redesigned and the performance test was conducted with the critical focus on the pattern factor and the exit mean temperature. We adopted TS2 four variants to check the improvement of the pattern factor. As a result, the pattern factors of several variants were satisfied with the performance target. Finally, the TS2A variant was chosen as a final combustor fur our APU model.

• 대한기계학회논문집B
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• 제24권6호
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• pp.870-879
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• 2000

An experimental investigation is conducted to improve a slot film cooling system which can be used for the cooling of gas turbine combustor liner. The tangential slots are constructed of discrete holes with different injection types which are the parallel, vertical, and combined to the slot lip. The investigation is focused on the coolant supply systems of normal-, parallel-, and counter-flow paths to the mainstream direction. A naphthalene sublimation technique has been employed to measure the local heat/mass transfer coefficients in a slot with various injection types and coolant feeding directions. The velocity distributions at the exit of slot lip for the parallel and vertical injection types are fairly uniform with mild periodical patterns with respect to the hole positions. However, the combined injection type increases the nonuniformity of flow distribution with the period equaling twice that of hole-to-hole pitch due to splitting and merging of the ejected flows. The secondary flow at the lip exit has uniform velocity distributions for the parallel and vertical injection types, which are similar to the results of a two-dimensional slot injection. In the results of local heat/mass transfer coefficient, the best cooling performance inside the slot is obtained with the vertical injection type among the three different injection types due to the effect of jet impingement. The lateral distributions of Sh with the parallel- and counter-flow paths are more uniform than the normal flow path. The averaged Sh with the injection holes are $2{\sim}5$ times higher than that of a smooth two-dimensional slot path.