• 대한기계학회논문집B
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• 제28권1호
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• pp.16-23
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• 2004

Acoustic characteristics of unbaffled and baffled combustion chamber are experimentally investigated under atmospheric condition to preliminarily determine baffle for mitigation of combustion instability. To investigate the effect of the baffle which has several configurations such as radial baffles and hub/blade baffle, resonant-frequency shift and damping factors of the chamber were analyzed and compared quantitatively with those of the unbaffled combustion chamber. From a view of acoustic characteristics, radial baffles with several configurations have not much difference in resonant-frequency shift and damping factor ratio with each other. On the other hand, hub and blade baffle is very effective to suppress the first tangential mode which was found to be the most harmful acoustic mode in KSR(Korean Sounding Rocket)-III engine. But more study on design parameters such as hub size and axial length should be done for complete optimization of hub and blade baffle. The present study based on linear acoustic analysis is expected to be a useful confirming tool to predict acoustic field and design a passive control devices such as baffle and acoustic cavity.

• 한국소음진동공학회논문집
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• 제12권1호
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• pp.21-28
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• 2002

This paper intends to investigate the effects of speed fluctuation caused by the cogging torque in permanent magnetic motors on the stability of the transverse vibration for a spinning disk. Based on the Kirchhoff\`s plate theory and the assumed mode methods, a set of discretized equations of motion were derived for an annular disk rotating with a harmonically varying speed. Then, a perturbation method using the multiple time scales was employed and stability boundaries were determined explicitly in terms of the magnitude and frequency of speed fluctuation, a nominal sped and the modal characteristics of the disk. It is found that parametric resonance occurs at several speed ranges and a single mode or a combination of two modes are involved to cause instability. It is also observed that unstable regions become broadened as the spinning speed increases or two modes are combined in parametric instability. As numerical simulations, stability analysis of a conventional CD-ROM drive was performed. Results of this work can e used as guidelines for motor design and operations with low vibration.

• 대한기계학회논문집B
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• 제30권9호
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• pp.905-912
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• 2006

Experiments in low strain rate methane-air counterflow diffusion flames diluted with $CO_2$ have been conducted to investigate the flame extinction behavior and edge flame oscillation in which flame length is less than the burner diameter and thus lateral conductive heat loss in addition to radiative loss could be remarkable at low global strain rates. The critical mole fraction at flame extinction is examined in terms of velocity ratio and global strain rate. It is seen that flame length is closely relevant to lateral heat loss, and this sheets flame extinction and edge flame oscillation considerably. Lateral heat loss causes flame oscillation even at fuel Lewis number less than unity. Edge flame oscillations are categorized into three: a growing-, a harmonic- and a decaying-oscillation mode. Onset conditions of the edge flame oscillation and the relevant modes are examined with global strain rate and $CO_2$ mole fraction in fuel stream. A flame stability map based on the flame oscillation modes is also provided at low strain rate flames.

• 한국소음진동공학회논문집
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• 제19권1호
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• pp.76-84
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• 2009

The vibration and stability of thin, flexible corotating disks in an enclosed compressible fluid is investigated analytically and compared with the results of a single rotating disk. The discretized dynamical system of the corotating disks is derived in the compact form of a classical gyroscopic system similar with a single disk. For the undamped system, coupled structure-acoustic traveling waves destabilize through mode coalescence leading to flutter instability. However, it is found that the flutter regions of the corotating disks are wider than those of a single disk. A detailed investigation of the effects of dissipation arising from acoustic or disk damping is also performed. Finally, in the presence of both acoustic and disk dampings, the instability regions are found and compared with those of a single disk. Although this study does not allow a radial clearance between the disk and the enclosure, the computational frame work of the problem can be expanded to the system having the radial clearance in an enclosure.

• Journal of Mechanical Science and Technology
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• 제15권10호
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• pp.1442-1450
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• 2001

The EGR system has been widely used to reduce nitrogen oxides (NO$\_$x/) emission, to improve fuel economy and suppress knock by using the characteristics of charge dilution. However, as the EGR rate at a given engine operating condition increases, the combustion instability increases. The combustion instability increases cyclic variations resulting in the deterioration of engine performance and emissions. Therefore, the optimum EGR rate should be carefully determined in order to obtain the better engine performance and emissions. An experimental study has been performed to investigate the effects of EGR on combustion stability, engine performance,70x and the other exhaust emissions from 1.5 liter gasoline engine. Operating conditions are selected from the test result of the high speed and high acceleration region of SFTP mode which generates more NO$\_$x/ and needs higher engine speed compared to FTP-75 (Federal Test Procedure) mode. Engine power, fuel consumption and exhaust emissions are measured with various EGR rate. Combustion stability is analyzed by examining the variation of indicated mean effective pressure (COV$\_$imep/) and the timings of maximum pressure (P$\_$max/) location using pressure sensor. Engine performance is analyzed by investigating engine power and maximum cylinder pressure and brake specific fuel consumption (BSFC)

• Ocean Systems Engineering
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• 제2권3호
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• pp.229-238
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• 2012

We discuss the bi - stability that is possibly exhibited by a liquid free surface in a parametrically - driven two-dimensional (2D) rectangular tank with finite liquid depth. Following the method of adaptive mode ordering, assuming two dominant modes and retaining polynomial nonlinearities up to third-order, a nonlinear finite-dimensional nonlinear modal system approximation is obtained. A "continuation method" of nonlinear dynamics is then used in order to elicit efficiently the instability boundary in parameters' space and to predict how steady surface elevation changes as the frequency and/or the amplitude of excitation are varied. Results are compared against those of the linear version of the system (that is a Mathieu-type model) and furthermore, against an intermediate model also derived with formal mode ordering, that is based on a second - order ordinary differential equation having nonlinearities due to products of elevation with elevation velocity or acceleration. The investigation verifies that, in parameters space, there must be a region, inside the quiescent region, where liquid surface instability is exhibited. There, behaviour depends on initial conditions and a wave form would be realised only if the free surface was substantially disturbed initially.

• 한국항공우주학회지
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• 제41권1호
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• pp.40-47
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• 2013

하이브리드 로켓은 고체로켓과 매우 흡사한 내부유동 특성을 가지고 있으므로 와류흘림(vortex shedding)은 하이브리드 로켓에서도 연소안정성에 영향을 미치는 중요한 인자로 판단된다. 본 연구에서는 예연소실에서 와류를 발생시켜 연료 표면와류와의 간섭과 연소특성 변화를 관찰하였다. 기본 형상과 디스크를 장착한 실험 결과, 5개의 주파수 특성이 관찰되었으며 이들은 각각 추진제의 열적지연에 의한 주파수, 디스크, 연료 단면, 후연소실 단면 변화에 의한 와류흘림과 관련된 주파수임을 확인하였다. 특히 디스크 1과 3의 결과를 비교해 보면 디스크 위치에 따라 변화하는 와류흘림이 연소실의 특정 주파수 특성과 상호 간섭하여 공진이 발생하기도 하지만, 또 다른 경우에는 어떠한 간섭도 일어나지 않는 것을 확인하였다. 이러한 선택적 공진현상은 하이브리드 로켓의 비선형 연소안정성 발생을 설명할 수 있는 중요한 메카니즘으로 판단된다.

• 한국공간정보시스템학회:학술대회논문집
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• 한국공간정보시스템학회 2004년도 춘계 학술발표회 논문집 제1권1호(통권1호)
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• pp.75-82
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• 2004

Many researcher's efforts have made a significant advancement of space frame structure with various portion, and it becomes the most outsanding one of space structures. However, with the characteristics of thin and long term of spacing, the unstable behavior of space structure is shown by initial imperfection, erection procedure or joint, especially space frame structure represents more. This kind of unstable problem could not be set up clearly and there is a huge difference between theory and experiment. Moreover, the discrete structure such as space frame has more complex solution, this it is not easy to derive the formulation of design about space structure. In this space frame structure, the character of rise-span ratio or load mode is represented by the instability of space frame structure with initial imperfection, and snap-through or bifurcation might be the main phenomenon. Therefore, in this study, space frame structure which has a lot of aesthetic effect and profitable for large space covering single layer is dealt. And because that the unstable behavior due to variation of inner force resistance in the elastic range is very important collapse mechanism, I would like to investigate unstable character as a nonlinear behavior with a geometric nonlinear. In order to study the instability. I derive tangent stiffness matrix using finite element method and with displacement incremental method perform nonlinear analysis of unit space structure, star dome and 3-ring star dome considering rise-span $ratio(\mu}$ and load $ratio(R_L)$ for analyzing unstable phenomenon.

• 대한기계학회논문집A
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• 제35권4호
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• pp.425-431
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• 2011

차량 제동시 디스크와 패드사이의 미끄럼 접촉에 의해 발생하는 마찰열은 재질의 열 탄성 변형을 일으키고, 이는 접촉면의 압력 분포에 영향을 끼친다. 이러한 열탄성 불안정성 (Thermo-Elastic Instability, TEI)은 디스크의 고유 진동모드와 결합되어 열섬 현상 및 열간 저더 진동을 발생시킨다. 본 연구에서는 상용 유한 요소 해석 프로그램인 SAMCEF 를 이용하여 자동차용 통풍식 디스크에 대한 3 차원 열간 저더 해석을 수행하였다. Staggered approach 에 의거한 중간 처리기를 이용하여 구조-동역학 해석 결과와 열 전달 해석 결과를 교환하였다. 디스크 표면에 열섬이 발생하는 것을 확인하였고, 이를 디스크 고유 진동 모드와 비교함으로써 모드 형상과 열섬 분포의 관계를 분석하였다.

• 한국항공우주학회지
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• 제36권7호
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• pp.688-694
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• 2008

볼 베어링과 펌프 비접촉 실의 동특성을 고려하여 고추력 액체 로켓 엔진용 터보펌프의 회전체동역학 해석이 수행되었다. 회전 고유진동수와 감쇠비를 예측하기 위하여 회전속도에 따른 복소 고유치 해석이 수행되었다. 동기 회전체 질량 불평형 응답과 시간 과도 응답 해석을 통하여 회전체의 임계속도와 불안정 운전 시작 속도가 확인되었다. 수치 해석 결과로부터 후방 베어링 강성이 임계속도와 불안정성 예측에 있어서 가장 중요한 인자로 확인되었는데, 이는 1차 모드가 터빈부 회전축 굽힘 모드인 것에 기인한다. 임계속도에 있어서 펌프 실의 영향은 후방 베어링 강성이 감소할수록 그리고 전방 베어링 강성이 증가할수록 확대되는 것으로 나타났다.