• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.259-264
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• 2005

Measurements of heat release are very important for controling combustion instabilities, which are closely connected with combustion instabilities. $OH^{\ast}$ images were acquired through a ICCD in this study, which were in use as indicating index of the reacting region, global and local heat release rate in the lean premixed combustion. The objectives of this study are to see the effect of equivalence ratio on global heat release rate and local Rayleigh index distribution. The local Rayleigh index distribution was acquired by information from central section of flame. This information was from the line-of-sight images which were inverted by the Abel de-convolution. In each condition, the mean value of heat release increased exponentially with equivalence for a periodic time. Local Rayleigh index distribution cleary showed the region of amplifying or damping the combustion instability as the equivalence ratio increased. This could provide an insight on the region of combustion instability and the structure of flames on the equivalence ratio.

• Journal of the Korean Society of Propulsion Engineers
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• v.1 no.2
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• pp.74-83
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• 1997

The definition of burning admittance and conventional n-$\tau$ stability rating technique are combined to investigate the high frequency combustion instabilities inside the cylindrical combustion chamber. Perturbed flow variables are written as the sum of fluctuating and time-averaged mean quantities on the assumption that the terms of the order higher than unity are sufficiently small, hence linearized governing equations could be formulated. Chamber admittances up and downstream of the flame front calculated with appropriate boundary conditions result in the burning admittance and corresponding n-$\tau$ neutral stability curve. Configurational and operational design factors are tested to detect the unstable wave-induced LOX-RP1 combustion instabilities. Operational design factors, e.g. pressure or O/F ratio, appear less influential to drive high frequency instability while the location of the flame front and configurational factors enhance or deteriorate the stabilities strongly. Conclusively, LOX-RP1 combustion inside the cylindrical combustion chamber is apt to be unstable against long residence time and shortened chamber length.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.2
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• pp.139-146
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• 2021

In hybrid rocket combustion, the oxidizer swirl injection is frequently used to stabilize the combustion as the rotational velocity component affects the boundary layer flow. However, as the swirl strength increases, a problem arises where the combustion performance changes too much. Thus, this study attempts to control the low frequency instability while minimizing the change in combustion performance by adapting attenuated swirl injection with fuel insert used in reference [7]. To this end, a series of experimental tests were performed by varying swirl intensity and the location of the fuel insert. In the tests, the occurrence of combustion instability and combustion performance were closely monitored. The results confirmed that combustion instability was successfully suppressed at the condition of the swirl angle 6 degree and the location of fuel insert 310 mm. And, the changes in combustion pressure, O/F ratio, and fuel regression rate were found as minimal compared to the baseline case. Also the results reconfirmed that the formation of positive coupling between two high frequency oscillations in 500 Hz band, combustion pressure(p') and heat release oscillation(q'), is the necessary and sufficient condition of the occurrence of low frequency instability.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.8
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• pp.677-683
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• 2015

Hybrid rocket combustion displays low frequency instability(LFI, 10~30Hz) at a certain condition. Vortex shedding in the post-chamber is suspected to cause the occurrence of LFI. This study focused on the visualization of flow image using light emissions from high temperature combustion gas. Results shows that combustion pressure oscillates at a frequency of about 18 Hz, which is in phase with oscillations of light emission. Since LFI is not a property of thermo-acoustic instability, this result suggested there exists a physical coupling of pressure fluctuations with light emissions proportional to chemical reaction. Also POD analysis shows that dominant symmetric spatial modes in the stable combustion shift suddenly into asymmetric spatial pattern with the appearance of LFI. Especially, the appearance of mode 3 is a typical change of flow dynamics in unstable combustion representing a rotational fluid motions associated with vortex shedding.

• Journal of the Korea Convergence Society
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• v.10 no.7
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• pp.47-54
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• 2019

The purpose of this study was to investigate the effect of visual conditions on the static balance of stable and unstable surfaces. Thirty healthy adults participated in this study (13 men, 17 women). Visual conditions were set as vertical, horizontal, and diagonal. It was performed on the pad to measure the balance on the unstable support surface. Using the balance measuring instrument, the General Stability Index, Weight Distribution Index, and Weight Distribution was measured. Paired t-tests were used for ground-based comparisons and one-way ANOVAs were used for comparisons within the same ground. The general stability index showed a significant difference according to the horizontal and vertical line directions on the stable support surface(p<.05). According to the comparison between the grounds, the weight distribution index on the unstable support surface showed a significant difference(p<.05). Weight distribution showed significant differences between the left and right eyes on the support surface with the stable and the unstable horizontal visual condition(p<.05). In static balance training, vertical and diagonal visual direction conditions are predicted to be helpful for training.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.128-132
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• 2009

Digital control system for active combustion control of lab-scale combustor equipped with secondary fuel injection is designed. Controllability with adaptive law is revealed with the Cambridge Combustor model and the requirement for control system is derived. The input and output requirements of frequency estimator and fuel supply actuator for the adaptive control law is verified with cold tests. The system can be used as digital based active combustion controller having 150Hz combustion instability.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.6
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• pp.28-36
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• 2018

A study was conducted to apply open-loop control to the combustion instability in a dump combustor using gaseous hydrocarbon fuels. Control power and frequency were varied by employing a loudspeaker under combustion conditions with similar characteristic chemistry times of the fuels. In the case of open-loop control where the frequency was identical to the combustion instability frequency, the open-loop control power affected the control performance. Results obtained from conducted open-loop control tests, where the frequency was different from the combustion instability frequency, show that setting the open-loop control frequency similar to the combustion instability frequency is effective.

• 전기의세계
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• v.9
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• pp.4-10
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• 1962

Relay Servo제어계의 특이한 성질의 하나로, 다른 비선형계에섣 그렇지만 외부의 동작에 의한 것이 아니고, 제어계 자체내의 조건에서 계속적으로 주기적운동, 즉 자려주기진동(Sustained Oscillation)이 발생하는 경우가 있다. 제어계가 자려진동의 상태에 있을 때 그 진폭 및 각주파수는 각 부분의 요소에 의하여 결정되고 고유한 값을 가지게 된다. 이러한 상태는 선형제어계의 입장에서 보며는 불안정상태이나, Relay제어계에서는 이 주기진동이 제어량의 일정목표치에 대한 비율이 미리 규정지은 요구조건에 비하여 실제상 허용할 수 있는 정도면 제어계는 안정하다고 할 수 있다. Relay Servo계의 안정, 불안정은 Describing함수의 방법에 의하여 Nyquist, Attnuation-phase Margin Criteria를 사용하여 Kochenburger, Johnson의 연구에서 규정지었다. Relay-Servo자려진동상태는 제어계의 Gain정수 중에서도 그 종류에 따라 각주파수 및 진폭에 미치는 영향이 달라진다. 본문은 위에 설명한 상태를 알아내기 위하여 간단한 Raly위치제어계를 구성하고 Gain정수를 변화시키면서 자려진동의 각주파수 및 진폭의 변화를 계산하고 기록계의 측정치와 비교검토하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.41-47
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• 2012

It is very important to predict the nonlinear behavior of combustion instability such as transition phenomena and limit cycle amplitude for fully understanding and controlling the instabilities. These nonlinear instability characteristics are highly dependent upon the flames' nonlinear dynamics in a gas turbine premixed combustor. In this study, nonlinear instability TA(Thermo-acoustic) models were introduced by applying the concept of flame describing function to the thermoacoustic analysis method. As a result of model development, for a given combustor length, the growth rate of instability was greatly affected by the change in amplitude, although the instability frequency was not. Further researches under various operating conditions and model validation on limit cycle amplitude are required.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.1
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• pp.24-33
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• 2020

In this study, model combustion tests were conducted to investigate the combustion instability characteristics of swirl coaxial injectors for a liquid rocket engine. To examine the effects of the combustion chamber resonant frequency and the injector mixing conditions, pressure fluctuations in the combustion chamber were measured by changing the combustion chamber length, injector recess length, and propellant mixture ratio. From the test results, the variation in the pressure fluctuations for each experimental condition was confirmed and the combustion stability was evaluated by stability mapping. It was found that the longitudinal mode and Kelvin-Helmholtz instabilities occurred due to the change in the combustion chamber and recess lengths.