• Journal of the KSME
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• v.34 no.8
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• pp.632-642
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• 1994

이 글의 앞부분에서는 소각로 관련 선진기술 중에서 소각 연소실부분에 대한 내용을 검토하고, 저공해화를 위한 연소실을 설계할 때 고려해야 할 인자들을 도출한다. 이러한 설계인자들에 대한 정량적인 평가는 설계개념 확인 및 설계인자의 검토를 위한 연소, 유동, 열전달 등 실험실 규모의 실험과 열유동의 전산해석 기법을 활용하여 설계변수의 최적화를 통해 이루어진다. 이 글에서는 컴퓨터. 프로그램을 사용하는 전산유동해석, 축소 모형장치를 사용하는 실험 등 열유동 해석법과 고형 폐기물의 연소특성을 분석하는 실험적.이론적 접근법을 소개한다.

• Journal of the korean Society of Automotive Engineers
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• v.6 no.2
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• pp.1-6
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• 1984

복잡한 연소과정의 예측을 위한 이론적인 연구는 Gosman, Spalding, Patankar등의 수치해석방 법을 이용하여 진행된 것들이 많다. 현재 이분야에 응용되는 일반적인 Program으로는 Boundary Layer Type의 방정식을 이용한 One-Dimensional Program (GENMIX 4, Revised GENMIX) 등이 있으나 Parabolic Type이므로 주방향에 수직된 방향으로 동일한 값이 2개 이상 존재할 수 있는 Elliptic현상을 설명하기에는 어려움이 있다. 그러므로 비록 기억용량(Computation Storage) 및 계산시간(Running Time)에 불리한 점이 있기는 하나 Elliptic상황을 해석해야만 할 경우가 있다. 본 해설은 Patankar의 Elliptic "SIMPLE" Program을 연소 해석과정에 이용되는 방법을 간단한 연소과정의 예로서 설명하는 것으로 연소과정의 연구보다도 Program의 응용성에 중점을 두었다. 따라서 실제의 물리적인 연소 mechanism에서 많은 가정을 도입하여 문제를 단순화 시켰으며 실제의 연소문제에 충분한 접근을 위해서는 turbulence-modeling과 radiation heat flux가 본 해설에 덧붙여져서 논의되어야 한다. 논의되어야 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.419-422
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• 2010

An unsteady numerical combustion analysis was performed to investigate the combustion characteristics of A Dual Combustion Ramjet(DCR) engine using a gas generator. According to a variance of the equivalence ratio of the gas generator, the flow pattern in the combustor was analyzed. A typical acoustic frequency in the combustor was observed by detail analysis of pressure fluctuation at each location of the combustor.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.5
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• pp.35-43
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• 2022

Precise modeling and analysis of closed bomb test(CBT) combustion using solid propellants was performed. The fluid structure interaction(FSI) method was implemented to analyze the gas and solid phases at the same time. The Eulerian analysis method was applied for the gas phase and grain combustion, and the Lagrangian analysis method was implemented for the grain movement. The interaction between the solid phase grains and the combustion gas was fully coupled through the source term. The volume of fluid(VOF) method was used to simulate the burning distance of the grain and the movement of the combustion surface. The force acting on the grain was comprised of the pressure and gravity acting on the grain burning surface, and the grain burning rate and grain movement speed were considered in the velocity term of the VOF. The combustion analysis was performed for both one and three grains, and fairly compared with the experiments. The acoustic field during grain combustion due to pressure fluctuations was also analyzed.

• Journal of the Korean Society for Nondestructive Testing
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• v.23 no.5
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• pp.488-496
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• 2003

To establish nondestructive test method for rocket motor assembly with rubber and aerospace composite materials, practicable quality control acoustic emission test method is presented. Structural analysis for motor assembly is performed by ABAQUS code and analysis output result is confirmed by strain gage and AE data. Various specimens were tested and analyzed using strain gage and acoustic emission data. The hit rate of acoustic emission was closely related with case/rubber debonding. This report also describes practicable acoustic emission nondestructive method for evaluating motor case assembly quality assurance in the industrial field.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.415-418
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• 2006

하이브리드 추진제는 연소 중 연료의 후퇴율 및 연소 면적의 변화로 인해 O/F비가 변화하므로 이로 인해 설계 및 해석에 어려움을 가지게 된다. 본 연구에서는 요구임무를 만족하는 하이브리드 로켓모터에 대한 설계를 수행하였다. 하이브리드 모터의 기초 설계를 실시하고 그 결과를 이용하여, 일정한 산화제 유량이 공급된다는 가정 하에, 연소 시 연소면적변화에 따른 O/F비 변화를 고려한 하이브리드 모터의 내탄도 해석을 실시하였으며, 그 결과를 이용하여 로켓의 외탄도 해석을 실시하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.3
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• pp.8-14
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• 2003

A cooling performance analysis has been made in the 8-channel calorimeter based on sub-scale KSR-III engine. Three-dimensional heat transfer analysis in cooling channels has been performed using the heat flux distribution through the chamber wall predicted from axi-symmetric compressible flow inside the combustion chamber. The heat flux distribution is verified against the published literature. Presented for the development and operation of the calorimeter are the coolant pressure drop, coolant temperature rise and the maximum chamber wall temperature. Required coolant flow rate is determined for given chamber pressure. Cooling performance is also predicted for temperature dependant coolant properties.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.2
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• pp.9-17
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• 2002

For turbulent spray combustion flows a coupled numerical procedure was developed, This method was discretized by using generalized curvilinear coordinates to handle complex geometries. The preconditioning and eigenvalue rescaling techniques were employed to provide efficient convergences over a wide range of subsonic Mach numbers. The accuracy was validated by simulating the laminar cavity flow. The film cooling effect of a liquid rocket engine (KSR-III) were investigated by a spray combustion analysis. The film cooling showed a negative effect on the combustion efficiency. In the combustion chamber wall, the film cooling effect was revealed to be promoted by the production of fuel rich zone.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.9
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• pp.1744-1759
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• 1992

A multidimensional simulation of turbulent flow and combustion with swirl in the cylinder of SI engine is implemented to clarify the effects of swirl. present simulation employs the ICED-ALE numerical technique, the skew-upwind difference scheme, a modified k_.epsilon. turbulence model, a combustion model of Arrhenius type and turbulence-mixing-control type. First, the calculations for swirling flow in an axisymmetric cylinder are carried out. The results are compared with the experimental data to validate the numerical analysis. Second, the calculations for intake, compression and combustion processes in an axisymmetric cylinder are performed. The effects of swirl on turbulent flow and combustion are examined through the parametric study of swirl number 0.0, 0.6, 1.2 and 2.4. As a result, it is numerically shown that the turbulent kinetic energy and the swirl velocity, which are produced during the intake process, affect the combustion process.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.278-281
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• 2004

The purpose of this paper is to show a reliable analytical method to predict the deflections of F/W Composite Motor Case. Structural analysis and testing of a Carbon/Epoxy Composites Motor Case for Pressure Loadings were performed. This paper presents the development of 3-D layered axi-symmetric solid element for finite element analysis. Finite element analyses were preformed considering fiber angle variation in longitudinal and thickness direction by ANSYS. The analytical results agree well with experimental results.