• 대한전기학회:학술대회논문집
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• 대한전기학회 1992년도 하계학술대회 논문집 B
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• pp.1247-1249
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• 1992

Oscillations with radio-frequencies are observed in a cesiated variable spacing thermionic diode having a parallel-plane geometry under certain conditions. The emitter is operated over the temperature range from 1300 to 2000 K and collector from 300 to 1050 K. The cesium vapor pressures are in the range of $10^{-3}$ to 3 torr. The interelectrode gap is between 1 mm to 0.08 mm. The oscillations are only observed in two nonoverlapping regimes. The low temperature oscillations (1300 to 1550 K) are inversely proportional to both the cesium vapor pressure and the square of the interelectrode gap. The high temperature oscillations is inversely proportional to the interelectrode gap. However, all these observed oscillations are frequencies of the plasma ion oscillation.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 1996년도 제7회 학술강연회논문집
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• pp.107-116
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• 1996

Numerical simulations have been conducted to characterize unsteady flow structures in an axisymmetric supersonic inlet diffuser with sinusoidal pressure oscillations at the diffuser exit. The formulation is based on the unsteady Navier-Stokes equations and turbulence closure is achieved using a two-layer model with a too-Reynolds-number scheme for the near-wall treatment. The governing equations are formulated in an integral form, and are discretized by the four-stage Runge-Kutta scheme for temporal terms and the Harten-Yee upwind TVD scheme for convective terms. Results indicated that the inlet shock characteristics are significantly modified by acoustic oscillations originating from the combustor. The characteristics of shock/boundarv-layer interactions (such as the size of separation bubble, terminal shock shape, and vorticity intensity) are also greatly iufluenced by the shock oscillation due to acoustic waves.

• 전산구조공학
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• 제8권4호
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• pp.189-198
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• 1995

비압축성 물체를 위한 일반적인 유한요소 공식화는 흔히 사용되는 사각형요소에서조차 압력해의 진동화(oscillations) 또는 pressure modes 현상을 나타낸다. 압력해의 안정화를 위한 규준은 소위 Babuska-Brezzi 안정조건이며, 위의 요소들은 이 조건을 만족시키지 못한다. 본 연구에서는 선형변위해와 상수값의 압력해를 갖는 사각형요소 사용시 압력해를 안정화시키기 위해 요소의 변에서 발생하는 불연속압에 근거한 압력연속여분치를 사용한다. 이 압력여분치를 비압축성 탄성론으로부터 유도되는 Q1P0요소에 적용하며 매개변수의 변화에 따른 수치해의 안정화의 정도를 연구한다. 압력해는 압력 여분치 사용시 안정화될 수 있으며, 해의 안정화는 매개변수에 민감성을 나타내었다.

• 대한기계학회논문집
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• 제18권4호
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• pp.933-945
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• 1994

A shock-wave in a supersonic flow can be theoretically determined by a given pressure ratio at upstream and downstream flowfields, and then the obtained shock-wave is stable in its position. Under the practical situation in which the shock-wave interacts with the boundary layer along a solid wall, it cannot, however, be stable even for the given pressure ratio being independent of time and oscillates around a time-mean position. In the present study, oscillations of a weak normal shock-wave in a supersonic diffuser were measured by a Line Image Sensor(LIS), and they were compared with the data of the wall pressure fluctuations at the foot of the shock-wave interacting with the wall boundary layer. LIS was incorporated into a conventional schlieren optical system and its signal, instantaneous displacement of the interacting shock-wave, was analyzed by a statistical method. The results show that the displacement of an oscillating shock-wave increase with the upstream Mach number and the dominant frequency components of the oscillating shock-wave are below 200 Hz. Measurements indicated that shock-wave oscillations may not entirely be caused by the boundary layer separation. The statistical properties of oscillations appeared, however, to be significantly affected by shock-induced separation of turbulent boundary layer.

• Journal of Mechanical Science and Technology
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• 제16권11호
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• pp.1448-1456
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• 2002

The present study addresses the flow characteristics involved in the self-induced oscillations of the underexpanded jet impinging upon a cylindrical body. Both experiment and computational analysis are carried out to elucidate the shock motions of the self-induced oscillations and to find the associated major flow factors. The underexpanded sonic jet is made from a nozzle and a cylindrical body is placed downstream to simulate the impinging jet upon an obstacle. The computational analysis using TVD scheme is applied to solve the axisymmetric, unsteady, inviscid governing equations. A Schlieren system is employed to visualize the self-induced oscillations generated in flow field. The data of the shock motions are obtained from a high-speed video system. The detailed characteristics of the Mach disk oscillations and the resulting pressure variations are expatiated using the time dependent data of the Mach disk positions. The mechanisms of the self-induced oscillations are discussed in details based upon the experimental and computational results.

• 한국항공우주학회지
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• 제42권1호
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• pp.29-36
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• 2014

하이브리드 로켓 연소에서는 다양한 종류의 저주파수 연소 압력진동이 나타난다. 10Hz 대역의 저주파수 압력진동은 고체연료와 연소가스의 열 관성 차이 때문에 발생하지만 그외의 저주파수 진동은 고체로켓에서 관찰되는 헬름홀츠 및 $L^*$ 모드에 의해 발생하는 것으로 연소실 부피 변화와 밀접한 관련이 있다. 따라서 유동 특성이 고체로켓과 유사한 하이브리드 로켓 연소에서 연소실 부피 변화는 저주파수 특성에 영향을 미치는 중요한 인자이다. 본 연구에서는 연소실과 후연소실의 형상 변화에 따른 연소 압력의 저주파수 특성 변화를 관찰하였다. 특히 주 연소실과 후연소실의 부피 비가 특정한 값이 되면 연소 도중에 10~30Hz 연소 압력 진동의 진폭이 갑자기 증폭되는 연소불안정 현상이 나타났다. 산화제 유량 조절 및 연료 변경에 의한 O/F 비 변화는 연소 압력의 저주파수 증폭과 무관한 것으로 밝혀졌다. 후연소실로 연소가스가 팽창할 때 발생하는 와류 흘림 현상이 저주파수 불안정 현상과 직접적인 관련 있는 것으로 판단되며 이에 관한 연구가 더 필요하다.

• 한국전산구조공학회:학술대회논문집
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• 한국전산구조공학회 1995년도 가을 학술발표회 논문집
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• pp.153-160
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• 1995

Mixed finite element formulations for incompressible materials show pressure oscillations or pressure modes in four-node quadrilateral elements. The criterion for the stability in the pressure solution is the so-called Babufka-Brezzi stability condition, and the four-node elements based on mixed variational principles do not appear to satisfy this condition. In this study, a pressure continuity residual based on the pressure discontinuity at element edges is used to study the stabilization of pressure solutions in bilinear displacement-constant pressure four-node quadrilateral elements. It is shown that the pressure solutions, although stable, exhibit sensitivity to the stabilization parameters.

• International Journal of Aerospace System Engineering
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• 제2권1호
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• pp.58-61
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• 2015

Under the background of combustion instability in solid rocket motor, to study the relationship between pressure oscillations and dynamic process of propellant flames, it is necessary to simulate an oscillation environment with certain frequency, amplitude and duration. This paper presents an experimental installation of pressure oscillation based on pulse-driving technique, with which pressure oscillations features under different pulse-driving conditions were compared and analyzed. For the pulse-driver applied in this paper, a pressure oscillation with 0.15s-0.5s duration, 179Hz-210Hz first order frequency, 0.04MPa-0.35MPa amplitude is simulated. The test results show that an oscillation with higher frequency and lager amplitude can be obtained when pulse-driver is installed on the top of the installation cavity, while on the side, an oscillation with a longer duration and approximate cavity natural frequency can be simulated.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2001년도 제17회 학술발표회 논문초록집
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• pp.5-5
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• 2001

No Abstract, See Full Text

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2003년도 추계학술대회 논문집
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• pp.171-176
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• 2003

Peristaltic mass transfer of fluid in a channel with standing wall oscillations is analyzed. Averaged nonlinear Navier-Stokes equations of motion are examined for a wide range of Reynolds numbers and external pressure drops. Nonpropogating wall oscillations with relatively big amplitudes essentially increase the liquid flow. Most effective intensifying of mass transfer occurred for low Reynolds numbers.