• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.445-455
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• 2010

In order to effectively predict thermo-acoustic instability within real combustors of rocket engines and gas turbines, in the present study, the Helmholtz equation in conjunction with the time lag hypothesis is discretized by the finite element method on three-dimensional hybrid unstructured mesh. Numerical nonlinearity caused by the combustion response term is linearized by an iterative method, and the large-scale eigenvalue problem is solved by the Arnoldi method available in the ARPACK. As a consequence, the final solution of complex valued eigenfrequency and acoustic pressure field can be interpreted as resonant frequency, growth rate, and modal shape for acoustic modes of interest. The predictive capabilities of the present method have been validated against two academic problems with complex impedance boundary and premixed flame, as well as an ambient acoustic test for liquid rocket combustion chamber with/without baffle.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.6
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• pp.59-67
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• 2014

Acceptance level random vibration and life firing test for development model of 1 N-class monopropellant thruster have been performed. From the results of random vibration, the natural frequency of the dual thurst module composed of 1 N-class development model thrusters was higher than the part level requirement(>100 Hz) and the structural robustness was verified. Thrust decrease of steady sate was below 7% and thrust instability was within ${\pm}5%$ in the life firing test using over 20 kg propellant throughput. The computerized tomography for catalyst bed showed a less than 7% of catalyst loss and it revealed the design appropriateness of the current thruster development model.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.72-80
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• 2018

Combustion instabilities are caused by the feedback relationship between heat release perturbations and acoustic pressure oscillations in the combustor. Studies on the combustion instability in an annular combustor have recently received great attention due to the enhanced NOx requirement in aero-engines. In this study, a thermoacoustic network model was developed in order to calculate the acoustic characteristics for various modes in the annular combustor. The network model is combined with flame transfer function(FTF) in order to calculate the stability of the combustor. Numerical results are compared with measurement data.

• Journal of the korean Society of Automotive Engineers
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• v.25 no.2
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• pp.35-38
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• 2003

• Journal of KSNVE
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• v.10 no.6
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• pp.991-997
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• 2000

The objective of this study is to examine the onset condition and the frequency characteristics of the low-frequency combustion oscillation in a surface burner. For this purpose, extensive parametric studies have been performed experimentally and the effects of size of each section, the equivalence ratio, and the entrance velocity on oscillatory behavior explored. The experimental results were discussed in comparison with the other combustors associated tilth the low-frequency combustion oscillation. The combustion mode is driven at high combustion rate by the lift of unstable flame near the lower limit of the combustible equivalence ratio. The oscillation frequency is dependent not on the burner geometry but on the equivalence ratio and the combustion load. Low-frequency combustion mode was formed to be divided into two different modes, named C1 and C2 respectively. Two modes occurred individually, simultaneously or transitionally according to the equivalence ratio and combustion load. The characteristics of low-frequency oscillation is different from each other depending on the type of combustors. The surface burner has also its own characteristics of low -frequency oscillation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.36-40
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• 2004

Experimental and numerical studies are carried out for inner flow of small gas turbine engine combustor at normal operating altitude and velocity. First of all inner flow and combustion phenomenon without a load is analyzed for understanding with various back pressure condition due to flight mode of smart UAV.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.70-71
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• 2002

연소실의 세장비(aspect ratio)가 작으면서 추진제의 고 충전을 이용한 단시간 연소 모타는 유도탄의 사출 모타 용으로 사용될 수 있다. 사출 모타는 일반적으로 모타 무게에 대한 제약 조건이 까다롭지 않기 때문에 무게 경량화에 대한 부담은 줄어들지만, 모타의 부피가 커지면 유도탄 발사 장치의 부피가 커지기 때문에 공간적인 측면에서 가능한 작게 하는 것이 시스템 전체의 효율을 증대시킬 수 있다. 또한 사출 모타의 연소 시간이 짧기 때문에(1초 이내) 추진제의 웹 두께가 작으므로 연소실의 주어진 공간에서 추진제를 많이 채우기 위한 방법으로 원통 튜브형 그레인을 여러 개의 다발로 사용하는 방법이 효과적이다. 이러한 관점에서 사출 모타용으로 다발 원통 튜브형 그레인을 설계/제작/연소시험을 하였더니 작은 저주파(약 10Hz)의 연소 불안정 현상이 발생하였다. (그림1). 이러한 주파수 대역은 일반적으로 잘 알려진 연소 불안정 모드 (longitudinal, tangential, and radial mode)와는 다른 아주 특이한 현상이다. 이러한 현상의 주 원인은 연소실 내 압력의 비평형에 의한 현상이라 판단되어 다음과 같은 연구를 수행하였다. 1) 그레인 튜브간의 압력 평형을 원활하게 하기 위하여 그레인에 구멍(홀)을 뚫어서 연소 안정화에 미치는 영향에 대한 연구(그림2), 2) 그레인에 홀을 뚫지 않고 격자와 격자간의 공간을 이용하여 그레인 간에 발생된 저주파의 압력 진동을 산란/소멸 시키는 연소 안정화 연구(그림3).

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.456-466
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• 2010

Typical combustion instability such as DC-Shift found in the hybrid rocket motor is characterized by non-linearity. DC-Shift can occur in two different realizations. One is so-called a positive shift of measured DC voltage where the pressure increase suddenly. The other is a negative shift where the pressure drops abruptly. In the present work, specifically the negative DC-Shift was investigated to analyze the effect of oxidizer flow condition and the resonance between fundamental frequency and other ones, such as Helmholtz frequency, and acoustic frequency. Results show a peak frequency of several hundreds HZ shifts as combustion proceeds. A negative DC-shift was found as the result of phase cancellation between two dominant frequency, combustion frequency and flow related frequency. Still is it required to study further to identify the change of dominance of frequency during the combustion.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.6
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• pp.62-73
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• 2022

This research proposes a method to control combustion instability in a gas turbine combustor having an annular combustor form and compares the effect of flow symmetric braking through nozzle arrangement and the corresponding change in equivalent ratio. To this end, the symmetry breaking effect was confirmed through mode analysis of FFT, Time signal, and phase trajectory. In addition, the unstable area and the stable area were identified through mode analysis, and this was shown on the contour map. The present research shows that instability occurs when the equivalent ratio and the arrangement of the nozzles are symmetry or when the nozzles are continuously arranged, but if the arrangement and equivalent ratio are not symmetry, the combustion instability decreases dramatically even if the difference in the equivalent ratio is small.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.277-280
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• 2009

Mechanism of combustion frequencies occurring during combustion is experimentally investigated in model combustor with V-gutter flameholder. this combustor has a long duct shape with a cross section area of $40{\times}40\;mm$. The v-gutter type flameholder with 14mm width is mounted at the bottom of combustor. Kerosene and methane were used as fuel, and these fuel were injected transversely into air crossflow. It is found that combustion frequencies were considered as 1L longitudinal mode caused by combustor geometry and vortex shedding mode of flameholder. And fuel phase effect and nozzle effect were also observed in the low frequency range.