• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2002년도 유체기계 연구개발 발표회 논문집
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• pp.137-146
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• 2002

This paper presents a quasi-3-dimensional calculation method considering secondary flows in the impellers of diagonal flow blowers. A Quantitative estimation of the secondary flow effects is made by using secondary flow theories. In order to verify the validity of the adopted models, that is, span-wise mixing model and the tip clearance model, numerical simulations are performed for two different types of impellers of diagonal flow blowers which are designed differently. Numerical experiments are conducted for each of a constant tangential velocity type impeller, and a free vortex type impeller, both at two different flow coefficients. According to the simulation results, it was found that the present model considering span-wise mixing and tip clearance effect shows better agreements with the experimental data than those without these models in terms of the flow velocity and the angle distribution.

• 대한기계학회논문집B
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• 제28권8호
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• pp.887-894
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• 2004

A technique of mixing enhancement by using an elliptic jet screech reflector has been examined experimentally in an underexpanded sonic round jet where jet screech tone is generated. Since jet screech is known to enhance jet spreading, a reflector was designed to focus jet screech waves near the nozzle lip at an underexpanded jet. The reflector has an elliptic cross section of which one focus is located near the nozzle lip and the other in the jet screech source region in a plane including the jet axis. In the jet with the elliptic reflector, the mass flow rate showed a significant increase in the jet entrainment when compared to that for the small disk reflector. This was attributed to the increased screech amplitude near the nozzle lip as well as the mode change of the jet. The jet mixing was also increased by the amplified jet screech at two other underexpanded jets, but the jet oscillation mode did not change.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 추계학술발표대회 논문집
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• pp.125-128
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• 2005

The dispersion of carbon nanofiber (CNF) was carried out by solution blending, mechanical mixing, and sonication. CNFs at levels of 5-50% fiber weight content were mixed with polypropylene (PP) powder, and then were melt-mixed using a twin-screw extruder. For the further alignment of fibers, extruded rods were stacked uni-directionally in the mold cavity for the compression molding. For the evaluation of mechanical properties of nanocomposites, tension, in-plane shear, and flexural tests were conducted. CNF/PP composites clearly showed reinforcing effect in the longitudinal direction. The tensile modulus and strength have improved by 100% and 40%, respectively for 50 % fiber weight content, and the flexural modulus and strength have increased by 120% and 25%, respectively for the same fiber weight content. The shear modulus showed 65% increase, but the strength dropped sharply by 40%. However, the property enhancement was not significant due to the poor adhesion between fiber and matrix. In the transverse direction, the tensile, flexural, and shear strength decreased as more fibers were added.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2015년도 제49회 하계 정기학술대회 초록집
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• pp.188.1-188.1
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• 2015

For present investigation Fe/MgO/Fe/Co multilayer stack is grown on Si substrate using e-beam evaporation in ultrahigh vacuum. This stack is irradiated perpendicularly by 120 MeV $Ag^{8+}$ at different fluences ranging from $1{\times}10^{11}$ to $1{\times}10^{13}ions/cm^2$ in high vacuum using 15UD Pelletron Accelerator at Inter University Accelerator Centre, New Delhi. Magnetic measurements carried out on pre and post irradiated stacks show significant changes in the shape of perpendicular hysteresis which is relevant with previous observation of re-orientation of magnetic moment along the direction of ion trajectory. However increase in plane squareness may be due to the modification of interface structure of stacks. X-ray reflectivity measurements show onset of interface roughness and interface mixing. X-ray diffraction measurements carried out using synchrotron radiation shows amorphous nature of MgO and Co layer in the stack. Peak corresponding body centered Fe [JCPDS-06-0696] is observed in X-ray diffraction pattern of pre and post irradiated stacks. Peak broadening shows granular nature of Fe layer. Estimated crystallite size is $22{\pm}1nm$ for pre-irradiated stack. Crystallite size first increases with irradiation then decreases. Structural quality of these stacks was further studied using transmission electron microscopic measurements. Thickness from these measurements are 54, 36, 23, 58 and 3 nm respectively for MgO, Fe, MgO, Fe+Co and Au layers in the stack. These measurements envisage poor crystallinity of different layers. Interfaces are not clear which indicate mixing at interface. With increase fluence mixing and diffusion was increased in the stack. X-ray absorption spectroscopic measurements carried out on these stacks show changes of Fe valence state after irradiation along with change of O(2p)-metal (3d) hybridized state. Valence state change predicts oxide formation at interface which causes enhanced in-plane magnetization.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.75-78
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• 2004

Various jet engines (Turbine engine family and RAM Jet engine) have been developed for high speed aircrafts. but their application to hypersonic flight is restricted by principle problems such as increase of total pressure loss and thermal stress. Therefore, the development of next generation propulsion system for hypersonic aircraft is a very important subject in the aerospace engineering field, SCRAM Jet engine based on a key technology, Supersonic Combustion. is supposed as the best choice for the hypersonic flight. Since Supersonic Combustion requires both rapid ignition and stable flame holding within supersonic air stream, much attention have to be given on the mixing state between air stream and fuel flow. However. the wider diffusion of fuel is expected with less total pressure loss in the supersonic air stream. So. in this study the direction of fuel injection is inclined 30 degree to downstream and the total pressure of jet is controlled for lower penetration height than thickness of boundary layer. Under these flow configuration both streams, fuel and supersonic air stream, would not mix enough. To spread fuel wider into supersonic air an aerodynamic force, baroclinic torque, is adopted. Baroclinic torque is generated by a spatial misalignment between pressure gradient (shock wave plane) and density gradient (mixing layer). A wedge is installed in downstream of injector orifice to induce an oblique shock. The schlieren optical visualization from side transparent wall and the total pressure measurement at exit cross section of combustor estimate how mixing is enhanced by the incidence of shock wave into supersonic boundary layer composed by fuel and air. In this study non-combustionable helium gas is injected with total pressure 0.66㎫ instead of flammable fuel to clarify mixing process. Mach number 1.8. total pressure O.5㎫, total temperature 288K are set up for supersonic air stream.

• 대한전기학회:학술대회논문집
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• 대한전기학회 1999년도 추계학술대회 논문집 학회본부 C
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• pp.1128-1130
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• 1999

Optical encoding method of images using random-phase encoding in both input and Fourier Planes was proposed by Javidi and his group, and the method was realized experimentally by Singh and his group with use of a photorefractive crystal and a phase conjugate wave.[1-2] Recently various techniques have been proposed theorically and experimentally. These include the method using one random-phase mask in the Fourier plane or two random-phase masks in the input and the Fresnel planes.[3] We demonstrate the difference and the problem of the methods using one or two random-phase masks in the Fourier or Fresnel plane. We perform the encoding and decoding in $LiNbO_3$ crystal using degenerate four-wave mixing.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2001년도 제17회 학술발표회 논문초록집
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• pp.11-14
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• 2001

3-D compressible flow analysis was conducted by using mixing plane method for turbine system which is consisted of partial admission nozzle and rotor. Computational results are shown oblique shock wave in blade leading and trailing edge and also shown flow separation along suction surface of blade due to abrupt blade curvature. But computational results are well agree with 1-D calculation results and experimental data.

• 한국결정성장학회지
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• 제9권1호
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• pp.29-33
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• 1999

Verneuil 법에 의해 성장된 무색 sapphire {0001}, ${10\bar{1}0}$ 결정면에 전이금속 Cr을 확산시키고, 물리적, 전기적, 광학적 특성을 개선하였다. 확산분말은 금속산화물 분말과 금속분말을 혼합한 후 사용하였다. 혼합분말을 사용하였을 때 확산은 오랜시간 높은 온도를 필요로 하며 상대적으로 서서히 이루어 졌다. 금속분말은 $1{\times}10^{-4}$ torr, $2050^{\circ}C$의 조건에서 1차 기화하였고 이후 $2050~2150^{\circ}C$, 질소가압 6 atm의 확산조건에서 유지하였다. 사파이어의 표면밀도는 0.2254(c)와 $0.1199\;atom/{\AA}^2(a)$이었다. 확산이 이루어진 sapphires는 붉은색으로 변하였다. 고용반응은 ${10\bar{1}0}$ 결정면이 {0001} 보다 더욱 깊게 확산되었고, 면밀도가 확산효과를 결정하는 주요인자이었다.

• 한국항공우주학회지
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• 제30권4호
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• pp.77-83
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• 2002

헬리콥터용 2단 축류압축기의 성능향상을 위한 설계/재설계 과정에서 수치해석을 통한 성능예측 및 내부유동분석에 대한 연구가 수행되었다. 기초 설계된 2단 압축기에 대한 유동해석을 통하여 스톨, 쵸크 등의 주요한 유동현상의 발생원인을 파악하였다. 또한 전압력 상승, 효율, 출구유동분포 등의 계산값이 실험값과의 비교에서 비교적 잘 일치하는 결과를 얻음으로써 유동해석을 통한 다단 압축기 성능예측에 대한 가능성을 검증하였으며, 재설계의 방향을 제시하였다. 따라서 3차원 유동해석은 다단 압축기의 개발 및 설계변경에 있어서 실험을 대신하여 적은 비용과 시간을 들이고도 만족한 결과를 얻을 수 있는 가능성을 보여 주었다. 1D/2D 기법으로 재설계된 압축기는 요구성능에는 다소 미흡하지만 재설계의 목적과 방향에 성공적으로 부합함을 보였다. 그러나 보다 나은 성능을 위해 향후 3차원적인 블레이드의 설계변경이 필요할 것으로 예측되었다.

• 한국추진공학회지
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• 제13권2호
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• pp.42-53
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• 2009

가스터빈 엔진을 모사하기 위한 프로그램을 2차원 CFD 코드를 기반으로 개발 하였다. 압축기와 터빈은 k-$\omega$ SST 난류 모델의 2차원 NS(Navier Stokes) 코드를 이용하였고, 연소기는 lumped method 화학 평형 코드를 바탕으로 완전 혼합 상태에서 연소효율 100%로 가정된 케로신 공기 반응의 생성물 중 대표적인 10종류를 몰분율을 계산, 당량비에 따른 연소기 온도를 예측하였다. 압축기, 터빈에서 로터의 회전에 의한 비정상 유동 현상은 mixing-plane 기법을 이용한 경계면 처리로 그 효과를 나타내었고, 압축기는 연소기로 온도 압력을 주고, 연소기는 터빈으로 온도와 질유량을 전달하나 압력의 변화가 없는 것으로 가정하였다. 이를 바탕으로 아음속 조건에서의 압축기 입구 조건과 터빈 출구 조건, 회전수, 연소기의 당량비를 주는 것만으로 엔진의 성능이 계산 될 수 있는 통합 코드를 구성하였다.