• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2004년도 춘계학술대회 논문집
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• pp.217-224
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• 2004

개방해역에서의 폭풍고조의 계산은 특히 해안역의 계획 및 건설 작업 분야에서 의미있는 것이다. 본 연구에서 태풍으로 인한 수위의 변화예측은 물리모델에서나 실제현장에서 다루기가 매우 어렵기 때문에 수치모델에 주로 근거를 두었다. 폭풍고조에 대한 단순준이차원 수치모델을 다루었다. 모델배경에서 여러 가지 가정, 유효범위, 적용성을 이해하기 위하여 태풍과 폭풍의 발생과정을 좌우하는 물리적 인자들에 대하여 논하였다. 또한 수학적 관점 뿐만아니라 물리적인 관점에서 모델의 주요특성을 나타내기 위해 모델의 수립과정에 일반적으로 취한 가정과 함께 지배방정식을 따랐다. 본 논문에서 기술한 모델과 일치하는 방정식은 지배방정식을 축약시킨 것으로 이에 따른 수치기법을 제시하였다. 최종적으로 한국 남해안의 마산항에서 폭풍고조의 문제에 위에서 기술한 모델을 적용하여 천문조, 초기수면, 대기압에 따른 수위상승의 효과를 고려하였다. 아울러 해안도시역에서의 침수원인을 분석하고, 침수방지를 위한 합리적인 제안을 제시하였다.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2000년도 유체기계 연구개발 발표회 논문집
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• pp.211-218
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• 2000

Off-design experimental performance was investigated for a small centrifugal compressor, whose impeller diameter is about 125mm, used in an industrial gas turbine. Test rig was designed and manufactured with a radial inflow turbine and a combustor to supply driving power to the compressor. Static pressure was measured on the casing of the impeller, vaneless diffuser, vaned diffuser and volute. Total pressure was obtained using specially fabricated rakes at the vaned diffuser throat and exit. Circumferential nonuniformity was found, near surge, in the Impeller, vaned diffuser and volute region. Spanwise nonuniform flow from the impeller affected the total pressure defects in the vaned diffuser region. Static pressure distortion in the circumferential direction in the volute was found near surge, where the minimum occurred near 140 degree position.

• International Journal of Fluid Machinery and Systems
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• 제3권3호
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• pp.260-270
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• 2010

Reducing the losses of the tip clearance flow is one of the keys in an unshrouded centrifugal compressor design and development because tip clearances are large in relation to the span of the blades and also centrifugal compressors produce a sufficiently large pressure rise in single stage. This problem is more acute for a low flow high-pressure ratio impeller design. The large tip clearance would cause flow separations, and as a result it would drop both the efficiency and surge margin. Thus a design of a high efficiency and wide operation range low flow coefficient centrifugal compressor is a great challenge. This paper describes a recent development of high efficiency and wide surge margin low flow coefficient centrifugal compressor. A viscous turbomachinery optimal design method developed by the authors for axial flow machine was further extended and used in the centrifugal compressor design. The compressor has three main parts: impeller, a low solidity diffuser and volute. The tip clearance is under a special consideration in this design to allow impeller insensitiveness to the clearance. A patented three-dimensional low solidity diffuser design method is used and applied to this design. The compressor test results demonstrated to be successful to extend the low solidity diffusers to high-pressure ratio compressor. The compressor stage performance showed the total to static efficiency of the compressor being about 85% and stability range over 35%. The test results are in good agreement with the design.

• 소음진동
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• 제8권2호
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• pp.239-250
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• 1998

Traditionally, intake noise from internal combustion engine has not recevied much attention compared to exhaust noise. But nowadays, intake noise is a major contributing factor to automotive passenger compartment noise levels. The main objective of this paper is to identify the mechanism of generation, propagation and radiation of the intake noise. With a simplest geometric model, one of the main noise sources for the intake stroke is found to be the pressure surge, which is generated after intake valve closing. The pressure surge, which has the nonlinear acoustic behavior, propagates and radiates with relatively large amplitude. In this paper, unsteady compressible Navier-Stokes equations are employed for the intake stroke of axisymmetric model having a single moving cylinder and a single moving intake valve. To simulate the periodic motion of the piston and the valve, unsteady deforming mesh algorithm is employed and Thompson's non-reflecting boundary condition is applied to the radiation field. In order to resolve the small amplitude waves at the radiation field, essentially non-oscillatory(ENO) schemes with an artificial compression method (ACM) are used.

• 한국자동차공학회논문집
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• 제14권1호
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• pp.92-99
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• 2006

The swirl ratio of a charge in the cylinder was estimated by calculating the ratio of the rotary speed of charge which could be simulated from the rotary speed of paddle in the swirl measurement apparatus, to the engine speed which could be calculated by measuring intake air flow rate. The automation of the swirl ratio measurement for cylinder head was achieved by controling both valve lift in cylinder head and a suction pressure of surge tank using two step-motors. The number of measurement position for calculating mean swirl ratio was varied by adjusting the interval of valve lift. The mean swirl ratio with varying the number of measurement position showed nearly constant value. Two measurement methods for measuring the swirl ratio were compared, one was to control the suction pressure of the surge tank with PID (proportional, integral, differential) mode with by-pass valve controlled by the step motor and the other did not control the surge tank pressure by fixing the by-pass valve. The difference of the mean swirl ratio between the two measurement methods showed nearly constant value with varying the number of measurement position. This means that the w/o PID control method could be preferred to the PID control method which has been used, due to the simpleness of the swirl measurement.

• 한국소음진동공학회논문집
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• 제20권5호
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• pp.502-509
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• 2010

A test facility which can simultaneously measure turbocharger operating condition variables and vibro-acoustic emission in the situations that are quite similar to real internal combustion engine operating conditions has been introduced. Using this facility, a new method sweeping from full open throttle to deep surge region along constant speed curves can be utilized instead of the stationary method that has been traditionally used to obtain turbocharger compressor maps. Data covering an extensive range of the compressor performance map have been collected and analyzed. An experimental study is performed to define a noise diagram that correlates vibro-acoustic measurements to aerothermodynamic operating conditions. An instrumentation set in the facility allows the automatic definition of the operating point on the turbine and compressor map of the turbocharger. Also, radiated sound pressure and casing vibration data corresponding to the point are obtained by a microphone in the vicinity of the compressor casing and an accelerometer on the casing. The major source(s) of noise at specific operating point on the map can be easily identified with these maps. Also, acoustic characteristics of a given turbocharger at the vicinity of the surge as well as in the surge are also defined. Finally, the possibility to define mild surge region of a turbocharger using vibro-acoustic measurements is studied.

• 한국수자원학회논문집
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• 제42권10호
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• pp.785-793
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• 2009

본 연구에서는 부정류 상태의 조압수조를 해석 할 수 있는 수치모형이 개발되었다. 그리고 부정류 효과를 고려한 파이프의 파괴확률 산정을 위한 신뢰성 모형이 개발되었다. 파이프 파괴의 상대적 위험도 평가와 조압수조의 기능성 평가를 위해 부정류 효과를 고려한 조압수조가 있는 상수관망 시스템의 파괴확률을 산정하였다. 신뢰성 해석을 통하여 부정류가 파괴확률을 크게 증가 시키는 것을 알 수 있었으며 조압수조가 부정류의 압력을 크게 감쇠시킴으로써 파괴확률을 현저히 저하시키는 것을 확인할 수 있었다.

• 한국구조물진단유지관리공학회 논문집
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• 제11권2호
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• pp.164-174
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• 2007

댐에서 관로 시스템을 효과적으로 설계하기 위해서는 수격작용과 같은 과도수리현상을 해석해야 만 한다. 일반적으로 조압수조는 터빈의 부하변화에 의한 과도수리현상에 의해 발생되는 압력의 변화를 감소시키기 위해서 사용된다. 본 연구에서는 댐 안전관리를 위한 조압수조의 적정규모를 조사하였다. 지배방정식을 이용하여 조압수조 내 수위변동을 계산하였다. Thoma-Jaeger의 안정조건을 사용하여 홍수위, 상시만수위, 정격수위, 저수위인 경우에 정적안정조건과 동적안정조건을 검토하였다. 끝으로 조압수조의 수직갱과 수실의 적정 지름을 결정하였다.

• 한국유체기계학회 논문집
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• 제7권3호
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• pp.23-31
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• 2004

An experimental study on the performance and instability development characteristics of a centrifugal compressor equipped with an adjustable inlet guide vane has been performed with varying guide vane angles. The test was conducted at the design speed of 20,800 rpm for 6 guide vane angles : $-30^{\circ},\;-20^{\circ},\;10^{\circ},\;0^{\circ},\;10^{\circ},\;20^{\circ},\;30^{\circ}$. Unsteady pressures were measured using high-frequency pressure transducers at the inducer to investigate the instability phenomena such as rotating stall and surge inside the compressor. From the unsteady measurements, it is found that the transient process from rotating stall to surge was mainly affected by inlet guide vane angles. The results of the present study can be applied to the instability control of the centrifugal compressors using a adjustable inlet guide vane.

• 한국유체기계학회 논문집
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• 제11권1호
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• pp.33-39
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• 2008

Hybrid power generation systems combining a solid oxide fuel cell and a gas turbine is promising due to their high efficiency. In the pressurized hybrid system, the operating condition of the gas turbine may play a critical role in designing the hybrid system. In particular, prevention of surge of the compressor can be a critical issue. The existence of fuel cell between the compressor and the turbine may cause an additional pressure loss and thus compressor operating points tend to approach the surge if the original turbine inlet temperature is pursued. In this study, bypassing some of the turbine inlet gas directly to the turbine exit side is simulated. Its effects on suppressing the surge problem and change in performance characteristics are discussed.