• 한국광학회지
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• 제18권2호
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• pp.93-99
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• 2007

본 논문에서는 주기적으로 분산 값의 부호가 바뀌는(dispersion managed: DM) 선로에서 급작스런 분산 변화로 인한 scattering을 완화시키도록 이득을 공간적으로 변조(gain management: GM)하는 시스템을 제안하고 이에 대한 modulation instability(MI) 변화에 대한 이론적인 분석과 수치해석적인 분석을 보고한다. 연구결과 어떤 경우에도 GM을 가한 시스템이 DM만을 한 시스템 보다 MI 이득의 크기와 cutoff frequency, side band peak모두가 작아짐을 확인하였다. 동일한 광신호 세기에 대해서 MI 이득이 작아지는 것은 four wave mixing 등 광섬유의 비선형 현상을 완화시킴으로써 파장분할다중화 전송의 품질 향상에 도움이 될 뿐 아니라, 솔리톤(soliton)을 이용한 전송에 있어서 하나의 펄스에 더 많은 에너지를 갖게 함으로써 신호대 잡음비를 개선할 수 있음을 의미한다. 본 논문에서는 분산과 이득이 동시에 조절된 선로의 효과를 솔리톤 전송 시스템의 개선된 특성을 편광모드분산(polarization mode dispersion: PMD)가 존재하는 선로에서의 펄스 폭 증가를 통하여 살펴본다.

• 한국추진공학회지
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• 제26권6호
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• pp.62-73
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• 2022

본 연구에서는 환형연소기 형태를 가지는 가스터빈 연소기에서 연소불안정성을 제어하는 방법을 제시하고자 하였으며, 노즐 배치와 이에 따른 당량비 변화를 통한 유동적인 대칭성파괴(Flow symmetry breaking) 효과를 비교하였다. 이를 위하여 FFT, Time signal 및 위상궤적의 모드 분석을 통하여 대칭성파괴 효과를 확인하였다. 또한, 모드분석으로 불안정한 영역과 안정된 영역을 확인하였고 이를 등고선 지도에 나타내었다. 본 연구를 통해 노즐의 당량비와 배치가 대칭이거나 노즐이 연속적으로 배치되면 불안정성이 발생하였으나, 노즐의 배치 및 당량비가 대칭성을 가지질 않는다면 당량비의 차이가 작더라도 연소불안정성이 극적으로 감소하는 것을 확인할 수 있었다.

• 한국소음진동공학회논문집
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• 제14권1호
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• pp.50-55
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• 2004

In this study, slit-tones by plane impinging jet are investigated experimentally over the whole subsonic flow range, especially at low speeds, in order to obtain the instability behaviour of impinging plane jet. Slit-tones are generated at low speeds associated with laminar shear layer instability as well as at high speeds associated with turbulent instability. Most of low-speed slit-tones are induced by symmetric mode instability unless the slit is not so wide, in which case antisymmetric modes are induced like edge-tones. It is found that the frequencies at low speeds ate controled by the unstable condition of the vortex at the nozzle exit and its pairings by which the frequencies are decreased by half. In the case of symmetric modes related with low-speed slit-tones, frequencies lower than those associated with one-step pairings are not found.

• 소음진동
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• 제11권2호
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• pp.315-322
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• 2001

This paper is focused on the frictionally induced thermoelastic instability (TEI) in automotive disk brakes. This instability leads to the formation of localized high temperature contact regions known as hot spots. This article investigates the themoelastic instability in automotive disk brake systems consisting of a finite thickness layer (disk) and two half-planes (pads) using a perturbation method. The antisymmetric mode involves hot spots located alternately on two sides of the disk. As a result the circumferentially periodic hot spots produce rotor surface distortion and Induce low frequency vibration. Also the effects of system parameters on the critical speed for TEI are investigated.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제35회 추계학술대회논문집
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• pp.809-813
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• 2010

열음향학적 불안정성의 동역학적 저차 모델링 기법 개발을 위해 전기적으로 가열되는 Rijke 튜브 실험 장치를 구성하고, 불안정성으로 인해 발생되는 튜브 내의 압력 진동을 측정하였다. 측정된 데이터로부터 압력 신호의 주파수 스펙트럼을 분석한 결과 3개의 주요한 진동모드를 관측할 수 있었으며 특히 첫 번째 모드 주파수는 단순한 열음향학적 해석 결과와도 거의 일치하는 것을 확인하였다. 이러한 실험 자료와 데이터 분석을 바탕으로 추후 열음향학적 불안정현상의 저차 모델링을 수행할 예정이다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회B
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• pp.2946-2951
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• 2008

Combustion instability is a major issue in design of gas turbine combustors for efficient operation with low emissions. Combustion instability is induced by the interaction of the unsteady heat release of the combustion process and the change in the acoustic pressure in the combustion chamber. In an effort to develop a technique to predict self-excited combustion instability of gas turbine combustors, a new stability analysis method based on the transfer matrix method is developed. The method views the combustion system as a one-dimensional acoustic system with a side branch and describes the heat source as the input to the system. This approach makes it possible to use the advantages of not only the transfer matrix method but also well-established classic control theories. The approach is applied to a simple gas turbine combustion system to demonstrate the validity and effectiveness of the approach.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 1997년도 제8회 학술강연회논문집
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• pp.247-256
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• 1997

A nonlinear mathematical model of longitudinal combustion instability appropriate for ramjets and augmentors was developed based on modal analysis. The model was limited to a two-mode formulation. The associated differential equations were solved both analytically and numerically and used to perform parametric studies.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.853-858
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• 2001

The knowledge of flame structure is essential for control of combustion instability phenomena. Some results of an experimental study on mechanism of naturally occurring combustion oscillations with a single dominant frequency are presented. Tests were conducted in a laboratory-scale dump combustor at atmospheric pressure. Sound level meter was used to track the pressure wave inside the combustor. The observed instability was a longitudinal mode with a frequency of $\sim341.8Hz$. Instability map was obtained at the condition of inlet temperature of $360^{\circ}C$, mean velocities of $8.5\sim10.8m/s$ and well premixed mixture. It showed that combustion instability was susceptible to occur in the lean conditions. In this study, unstable flame was observed from stoichiometric to 0.7 in overall equivalence ratio. At selected unstable conditions, phase-resolved OH chemiluminescence images were captured to investigate flame structure with various mean velocities. As mean velocity is increased, the flame grows and global heat release was changed. Due to these effects, combustion instability can be maintained at more lean air-fuel ratio. Also, these results give an insight to the controlling mechanism for an increasing heat release at maximum pressure.

• 한국연소학회지
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• 제20권1호
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• pp.32-42
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• 2015

The combustion instability was experimentally investigated in model gas turbine combustor with dual swirl burner. When such instability occurs, a strong coupling between pressure oscillation and unsteady heat release excites a self-sustained acoustic wave which results in a loud sound, and can even cause fatal damage to the combustor and entire system. In present study, to understand the combustion instability with a premixed mixture, the detailed periods of pressure and heat release data in unstable flame mode were investigated by various measurement methods at relatively rich condition and lean condition near flammable limits. Also, to prepare the utilization of synthetic natural gas (SNG) fuel in gas turbine system, an investigation was conducted using a simulated SNG including methane as a reference fuel to examine the effects of $H_2$ content on flame stability. These results provide that the instability due to flash-back behaviour like CIVB phenomenon occurred at rich condition, while the repetition of relighting and extinction caused the oscillation of lean condition near flammable limit. From the analysis of $H_2$ content effects, it is also confirmed that the instability frequency is proportional to the laminar burning velocity at both rich and lean condition.

• 한국광학회지
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• 제29권4호
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• pp.159-165
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• 2018

본 논문에서는 3단으로 구성된 전광섬유(all-fiber) Master Oscillator Power Amplifier (MOPA) 구조의 협대역 이터븀 첨가 편광 유지 광섬유 레이저 증폭에 대해 보고한다. 편광유지 단일모드 출력은 85%의 기울기 효율을 가지는 400 W 출력을 얻을 수 있었고, 레이저 반치폭은 2.5 GHz였다. 더불어, 이득매질 광섬유를 11 cm 지름으로 코일링하여 모드 불안정성을 완화할 수 있었다. 추가적으로 레이저 출력 증가를 위한 방법들에 대해 논하였다.