• 한국추진공학회지
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• 제20권1호
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• pp.58-68
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• 2016

고체 로켓 모타의 충전을 위한 추진제 믹서는 가장 중요한 장비 중 하나다. 추진제 믹서는 수출통제 품목으로 해외로부터 직접 구입하기 어렵다. 이에 당사에서는 해외 수출 통제(Export Licence) 품목으로 수입이 불가능한 어려운 상황에 대처하기 위해 국산화 개발을 진행하였다. 본 논문을 통해 일반적인 추진제용 믹서의 소개와 당사의 믹서 국산화 개발과정을 나타내었다. 또한, 블레이드-블레이드, 블레이드-보울 벽사이의 간극 측정 및 ADINA 해석을 통해 국산화 개발된 추진제 믹서의 설계를 검증하였으며 개발과제에 적용함을 기술하였다.

• 대한기계학회논문집B
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• 제27권7호
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• pp.883-892
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• 2003

The experiment using three-dimensional laser Dopperr velocimetery (LDV) measurements and the computation using the Reynolds stress model of the commercial code, FLUENT, were conducted to give a clear understanding on the structure of tip leakage flow in a forward-swept axial-flow fan operating at the maximum efficiency condition. The tip leakage vortex was generated near the position of the minimum wall static pressure, which was located at approximately 12% chord downstream from the leading edge of blade suction side, and developed along the centerline of the pressure trough within the blade passages. A reverse flow between the blade tip region and the casing, induced by tip leakage vortex, acted as a blockage on the through-flow. As a result, high momentum flux was observed below the tip leakage vortex. As the tip leakage vortex proceeded to the aft part of the blade passage, the strength of tip leakage vortex decreased due to the strong interaction with the through-flow and casing boundary layer, and the diffusion of tip leakage vortex caused by high turbulence. In comparison with LDV measurement data, the computed results predicted the complex viscous flow patterns inside the tip region, including the locus of tip leakage vortex center, in a reliable level.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2006년도 제26회 춘계학술대회논문집
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• pp.297-305
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• 2006

본 논문에서는 터빈의 형상 변수에 따른 부분흡입형 초음속 터빈 손실 특성을 분석하기 위하여 초음속 노즐 형상, 축방향 간극 길이, 로터 앞전의 모서리각에 따른 초음속 터빈내 유동 해석을 실시하였다. 먼저 축방향 간극을 진행하면서 발생하는 유동의 익렬 팁방향의 휘어짐은 초음속 노즐 형상에 크게 영향을 받는다. 다음으로 모서리각은 익렬 앞전에서 발생하는 충격파등의 강도를 결정한다. 마지막으로 축방향 간극에서 발생하는 유동의 확산 및 혼합은 축방향 간극 길이에 크게 영향을 받았다. 따라서 터빈내에서 발생하는 손실 중 유체역학적 손실은 노즐 형상과 로터 앞전의 모서리각에 의해 결정되었으며, 부분 흡입 손실은 노즐 형상 및 축방향 간극 길이에 영향을 받았다.

• 한국유체기계학회 논문집
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• 제11권6호
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• pp.54-63
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• 2008

A study on the flow characteristics in a 4-stage axial compressor and the behavior of rotating stall was experimentally performed at the third-stage rotor and stator rows in order to investigate its performance and instability of the compression system. The pressure losses generated due to the leakage flow at a tip clearance and a shroud seal clearance and the wake flow near the trailing edge of a blade were taken into consideration to estimate the causes of performance drop of the low speed research compressor(LSRC) in Seoul national university. In addition, the measurement of rotating stall was conducted with hot-wire probes and the existence and propagation of stall cell could be confirmed through fast Fourier transform and cross-correlation analysis.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2002년도 유체기계 연구개발 발표회 논문집
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• pp.17-30
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• 2002

The design method of turbomachinery has been developed highly. But some geometric dimensions have been determined from the empirical view points. In designing the inlet outer diameter of pump impeller and the hub ratio of blower, satisfactory theoretical grounds have not been presented till now. In the paper, these points are discussed and the method of increasing pump and blower efficiencies are also discussed on the basis of experimental and computational results of flow analysis. Further, the effects of tip clearance of rotor on its efficiency and the interference of rotor and stator blade rows are discussed and some ideas to estimate their effects are presented.

• 동력기계공학회지
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• 제15권6호
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• pp.35-40
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• 2011

The present study aims at investigating the effect of the fluid-structure interaction on the aerodynamic performances in the turbo blower. The design specifications of the reference model driven by 400kW power were given as 7.43kg/s of mass flow rate, 1.66 of pressure ratio with 12000rpm of impeller rotating speed. Numerical simulation has been performed on the three cases based on the tip clearance between the impeller blade and the shroud. The CFX-turbo for flow fields and ANSYS-mechanical for structure domain were applied to solve the present FSI problems inside the turbo blower. Through the numerical results, the performances corrected by the FSI effects were proposed for the more reliable predictions.

• 한국해양공학회지
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• 제19권6호통권67호
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• pp.1-7
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• 2005

This paper deals with the design and aerodynamic analysis of a special-type impulse turbine, with an end plate for wave energy conversion. Numerical analysis was performed using a CFD code, FLUENT. The main idea of the proposed end plate was to minimize the adverse effect of tip clearance of turbine blade, and was borrowed from ducted propeller, with so-called penetrating end plate for special purpose marine vehicles. Results show that efficiency increases up to $5\%$, depending on the flow coefficient; a higher flow coefficient yields increased efficiency. Decrease of input coefficient CAwith an end plate is the main reason for higher efficiency. Performance of end plate at various design parameters, as well as flow conditions, was investigated; the advantages and disadvantages of the presentimpulse turbine were also discussed.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2011년 춘계학술대회논문집
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• pp.567-571
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• 2011

Air Starter motors are used for the start of medium-speed diesel engine. One of the main part of air starting motors is the axial turbine stage. In this study, design of 1-stage axial type turbine for 14kw class air starter motors has been performed. The turbine blade was designed based on mean-line analysis. 1-D design calculation and numerical analysis with CFD were conducted iteratively. The validation between 1-D design method and numerical analysis for axial clearance has been performed. It revealed that there is optimum axial clearance of turbine design.

• 대한기계학회논문집B
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• 제21권4호
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• pp.541-550
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• 1997

Computational and experimental investigations on the three-dimensional flowfield through an automotive cooling fan are carried out in this work. Steady, incompressible, three-dimensional, turbulent flow through a rotating axial-flow fan is analyzed with Reynolds averaged Navier-Stokes equations and standard k-.epsilon. turbulence model. The governing equations are discretized with finite-volume approximations in non-orthogonal curvilinear coordinates. Computational static pressures on the casing wall agree well with the experimental data which are measured in this work. And, they are sensitive to the change of tip clearance. The flowfield is not significantly affected by the thickness of the blade. The k-.omega. model gives the static pressure rise on the casing wall which is similar to that with the k-.epsilon. model.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1998년도 춘계 학술대회논문집
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• pp.181-189
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• 1998

A numerical study based on the three-dimensional Reynolds averaged Navier-Stokes equations is presented to analyze the transonic flowfield through two-stage axial compressor. Explicit four-step Runge-Kutta scheme is used for solution algorithm, and local time step and implicit residual averaging are introduced for enhancing the convergency. Artificial dissipation model is adopted to assure the stability of solution. The solver is coupled with Baldwin-Lomax model to describe turbulence. To avoid calculating the unsteady flow, a mixing process is modeled at a station between rotating and stationary blade rows. Results show a variety of important physical phenomena. Comparison of the flowfields with and without tip clearance shows that the effect is considerable in this flowfield. Comparisons with experimental data carried out to validate the calculational results show reasonable agreements. Some remedies are also suggested to improve the revealed problems.