• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 1999년도 유체기계 연구개발 발표회 논문집
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• pp.309-314
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• 1999

This paper is concerned with the viscous interaction between rotor and stator The viscous interaction is caused by wakes from upstream blades. The cascade was composed with five blades and cylinders were placed to make wakes and their location was about 50 percent of blade chord upstream. The location of cylinders were varied in the cascade axis with 0, 20, 40, 60 and 80 percent of pitch length. The velocity distribution in the cascade passage were measured using single slanted hot-wire and the ones in the boundary layer using boundary probe. As a result, wakes decay more rapidly at suction surface and more slowly at pressure surface. And the measurement of momentum thickness of cascade shows that the momentum thickness is larger near the blade surface. From measurement of blade boundary layer, turbulent intensity is also larger near the blade surface because wakes collide the boundary layer And wakes make boundary layer thickness smaller and delay flow separation.

• 한국유체기계학회 논문집
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• 제15권6호
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• pp.85-91
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• 2012

Numerical simulations on a single stage transonic compressor which is developed by Korea Aerospace Research Institute are carried out and their results are compared with experimental data for cross validations. Comparisons between experimental data and numerical simulation results show good agreements on a performance curve, static pressure and total pressure distributions. CFD results show that there is a clear interaction between tip leakage flow and normal shock in the rotor passage. Tip leakage flows are almost dissipated after the strong normal shock and it forms a strong recirculation near the blade tip. Also a large separation region grows on the suction surface just after the normal shock. As the pressure ratio and blade loading increase, the normal shock line moves upstream and it starts to deviate from the blade leading edge. Then the tip leakage flow does not overcome the strong adverse pressure gradient and flow blockage originated from the tip recirculation region. As a result, the tip leakage flow heads for the neighboring blade leading edge, which results in a compressor stall.

• 대한조선학회논문집
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• 제41권6호
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• pp.8-14
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• 2004

The numerical analysis of a waterjet propulsion system was performed to provide detail understanding of complicated flow phenomena including interactions of intake duct, rotor, stator, and contracted discharge nozzle. The incompressible RANS equations were solved on moving multiblocked grid system. To handle interface boundary between rotor and stator, the sliding multiblock method was applied. The numerical results were compared with experiments and good agreement was obtained. The complicated viscous flow features of the waterjet, such as secondary flow inside the intake duct, the recovery of axial flow by the role of the stator, and tip and hub vortex, etc. were well analyzed by the present simulation. The performance of thrust and torque was also predicted.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.881-888
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• 2017

일반적으로 다단 축류 터빈은 높은 압력비에서 유동 가속으로 인하여 특정 단에서 초킹 현상이 발생하게 된다. 초킹의 경우 유량 변화 없이 압력비만 증가하게 되며, 이러한 특성을 입구 유량 경계조건을 사용하는 일반적인 평균반경해석법을 이용하여 예측하는데 한계가 있다. 본 연구에서는 이러한 문제점을 해결하기 위해 초킹 영역에서의 성능을 예측하는 알고리즘을 재안하였다. 초킹 지점 이후에는 초킹이 발생하는 노즐 혹은 로터 출구 유동이 팽창하는 특성을 반영하여 고정된 유량 조건에서 압력비가 변할 수 있도록 알고리즘을 구성하였다. 이러한 결과를 다단 축류 터빈 전산해석 결과 및 실험결과와 비교하여 신뢰성을 확인하였다.

• 한국추진공학회지
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• 제22권2호
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• pp.20-28
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• 2018

일반적으로 다단 축류 터빈은 높은 팽창비에서 유동 가속으로 인하여 특정 단에서 초킹 현상이 발생하게 된다. 입구 유량 경계조건을 사용하는 일반적인 평균반경해석법을 사용하는 경우 유량 변화없이 팽창비만 증가하게 되는 초킹 현상을 예측하는데 한계가 있다. 본 연구에서는 이러한 문제점을 해결하기 위해 초킹 영역에서의 성능을 예측하는 알고리즘을 제안하였다. 초킹 지점 이후에는 초킹이 발생하는 노즐 혹은 로터 출구 유동이 팽창하는 특성을 반영하여 고정된 유량 조건에서 팽창비가 변할 수 있도록 알고리즘을 구성하였다. 계산된 결과를 다단 축류 터빈 전산해석 결과 및 실험결과와 비교하여 신뢰성을 확인하였다.

• 한국유체기계학회 논문집
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• 제10권6호
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• pp.7-16
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• 2007

An axial-type fan which operates at the relative total pressure of 671Pa and static pressure of 560Pa with the flow rate of $416.6m^3/min$ is developed with an optimization technique based on the gradient method. Prior to the optimization of fan blade, a three-dimensional axial-type fan blade is designed based on the free-vortex method along the radial direction. Twelve design variables are applied to the optimization of the rotor blade, and one design variable is selected for optimizing a stator which is located behind of the rotor and is used to support a fan driving motor. The total and static pressure are applied to the restriction condition with the operating flowrate on the design point, and the efficiency is chosen as the response variable to be maximized. Through these procedures, an initial axial-fan blade designed by the free vortex method is modified to increase the efficiency with the satisfaction of the operating condition. The optimized fan is tested to compare the aerodynamic performance with an imported same class fan. The test result shows that the optimized fan operates with the satisfaction of restriction conditions, but the imported fan cannot. From the experimental and numerical test, they show that this optimization method improves the fan efficiency and operating pressures of a fan designed by the classical fan design method.

• 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.

• 한국유체기계학회 논문집
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• 제2권3호
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• pp.7-16
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• 1999

The flow angle at the inlet and exit of a rotor or stator is an important design parameter involved in the design a fan blade. Flow angles along the radial direction for 3-D stacking are calculated using two kinds of vortex methods, i.e. free vortex method and forced vortex method. The performance test shows that a fan designed by the free vortex method is more efficient than a fan designed by the forced vortex method. As a reference, an imported fan is tested. Even though the straightner of the imported fan is used for the comparison test, the difference of efficiency between the imported fan and the fan designed by the free vortex method is negligible. The noise of the fan designed by the free vortex method is less than that of the imported fan. A bellmouth installed at the fan inlet improved the fan efficiency more than $10\%$.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.395-398
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• 2009

Currently, a new generation of ducted fan UAVs (Unmanned Aerial Vehicles) is under development for a wide range of inspection, investigation and combat missions as well as for a variety of civil roles like traffic monitoring, meteorological studies, hazard mitigation etc. The current study presents extensive results obtained experimentally in order to investigate the tip clearance effects on performance characteristics of a ducted fan for small UAV systems. Three ducted fans having different tip clearance gap and with same rotor size were examined under three different yawed conditions of calibrated slanted hot-wire probe. Three dimensional velocity flow fields were measured from hub to tip at outlet of the ducted fan. The analysis of data were done by PLEAT (Phase locked Ensemble Averaging Technique) and three non-linear differential equations were solved simultaneously by using Newton -Rhapson numerical method. Flow field characteristics such as tip vortex and secondary flow were confirmed through axial, radial and tangential velocity contour plots. At the same time, the effects of tip clearance on axial thrust and input power were also investigated by using wind tunnel measurement system. For enhancing the performance of ducted fan, tip clearance level should be as small as possible.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2002년도 유체기계 연구개발 발표회 논문집
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• pp.279-283
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• 2002

The effects of finite gap at the tip of turbomachinery blades have long been topics of both theoretical and experimental research because tip clearance degrades turbomachinery performance. This paper presents an analytical study of radial flow redistribution in a high speed compressor stage with axisymmetric tip clearance. The flow is assumed to be inviscid and compressible. The stage is modeled as an actuator disc and the analysis is carried out in the meridional plane. Upon going through the stage, the radially uniform upstream flow splits into the tip clearance and passage flows. The tip clearance flow is modeled as a jet driven by blade loading, or pressure difference between the pressure and suction sides. The model takes into consideration the detached shocks which occur in the rotor passage at the design point. This shock model is used to calculate the density ratio across the stage. Thus, the model is capable of predicting the kinematic effects of tip clearance in the high speed compressor flow field.