• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.3
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• pp.56-61
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• 2014

Two erosive burning models were applied to compare analysis results of ballistic for the internal ballistics of solid rocket motors. By comparing motor tests with results of analysis, the variance of a grain shape was analyzed and coefficients of erosive burning were drawn. Results of comparison presents that the coefficient of erosive burning was proportional to the change of burning area, while inversely proportional to the change of cross area.

• Proceedings of the KAIS Fall Conference
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• 2002.11a
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• pp.293-296
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• 2002

본 논문에서는 수소/액체연료/공기의 연소특성에 대해 CFD상용프로그램을 사용하여 수치해석을 수행하였다. 먼저 프로그램을 검증하기 위하여 수소/공기의 난류 비예혼합 화염에 대한 반응물과 생성물의 몰분율을 Barlow실험 결과와 비교하였고, X축 방향의 온도분포를 Flury의 실험 값과 비교하여 값이 물리적으로 근사함을 확인하였다. 혼합분율(Mixture Fraction)과 확률밀도함수(PDF)의 접근 방법을 이용하여 화염진단과 오염물질발생에 중요한 역할을 하는 중간 종들의 몰분율을 확인하였다. 수소/액체연료/공기에 대해서는 화염형성에 있어서 가장 중요한 연료와 산화제의 속도비 변화(100,10,1,0.1)로부터 산화제속도가 연료속도 보다 클 경우 고속 측인 산화제에 의해 연료의 확산이 지배되는 현상으로 인하여 화염의 온도분포가 최고가 됨을 확인하였다. 또한, 연소과정 중 발생하는 오염물질의 농도를 수치적으로 해석하여 최저의 오염농도를 가질 수 있는 속도 비를 찾아 낼 수 있었다. 수소/공기와 수소/액체연료/공기의 온도 장 비교를 통하여 수소/액체연료/공기의 혼합물이 대체에너지로서의 가능성을 확인하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.57-60
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• 2008

There exist a lot of factors and restrictions for the design of solid rocket motors like burning rate, of solid propellant, demanded thrust, chamber pressure, diameter, length, weight and acceleration. For the optimization of these factors and restrictions, integrated design software for internal/external ballistic analysis was developed and verified by the performance test of solid rocket motors.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.2
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• pp.54-61
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• 2003

This paper describes a general design procedure of regenerative cooling system for liquid rocket engine(LRE). From this design logic, cooling channels are designed and fabricated. The measured heat flux from firing test is similar to the heat flux predicted by design logic. Therefore, proposed design procedure of cooling channel can be applied to real LRE system. Also the result of firing test indicates that soot from combustion products have strong influence on the cooling characteristics of LRE.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.3
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• pp.61-67
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• 2017

In this study, Burning Area Analysis Program (BAAP) was developed by using VOF method to estimate the burning area of 3D shaped grain. The parametric study of mesh size, burning rate and time interval for numerical calculation was conducted. The result of BAAP is compared with the one from commercial 3D modeling software. Also the internal ballistic analysis was performed using the result of BAAP. In order to estimate the burning area and internal pressure with time, Chemical Equilibrium Analysis (CEA) was conducted with a composition of reduced smoke propellant. As a result, the web-averaged pressure was 5.34 MPa which is similar to the published research result.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.213-216
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• 2010

A typical unsteady internal ballistic analysis model was proposed to take account of the erosive burning for a solid rocket motor. The variance of local velocity and pressure along grain surface are analyzed by using the continuity and momentum equation. The model introduced in this study showed good agreements with the results of previous internal ballistics program. It was investigated that the change of combustion pressure, gas velocity and regrestion rate along the grain axis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.12-12
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• 1998

국제 공동 가스터빈 엔진 개발 프로그램인 ASE120 사업은 항공기용 터보팬 엔진을 Low Emission 산업용 엔진으로의 개조사업으로서 현대우주항공, AlliedSignal, AIDC(대만), SPHT(대만) 등이 참여하고 있다. 본 사업을 통한 주요 개조 부품인 연소기의 경우, 산업용 엔진의 특성상 장시간의 수명이 보장되어야 하고 Dry Low NOx 연소실 형태로 배기가스 규제의 요구조건을 만족하여야 하므로 일반 항공기용 연소기와 구조적으로 첨예한 변화가 발생하여 구조 및 수명해석을 통한 구조적 안전성과 요구 수명에 대한 평가가 절대적으로 요구되었다. 당 엔진의 요구수명은 30년으로 cold section part의 경우 180,000시간, hot section의 경우 90,000시간의 수명을 목표로 개발되었으며, 연소기 최적설계를 위해 구조/수명 해석결과가 개발과정 중 설계에 지속적으로 반영되어 추진되었다. 연소기의 구조해석은 해석용 tool로서 ANSYS53을 활용하였고 수명예측은 AlliedSignal사의 Material Database 및 Inconel사 재질 data를 근간으로 수행하였다.

• Journal of the Korean Society of Combustion
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• v.18 no.3
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• pp.54-60
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• 2013

This paper shows a general development process for aircraft gas turbine combustors. As a first step for developing the preliminary combustor design program, several combustor sizing methodologies using reference area concepts are reviewed. There are three ways to determine the reference area; 1) combustion efficiency approach, 2) pressure loss approach, 3) velocity assumption approach. The current study shows the comparisons of the calculated results of combustor reference values from the pressure loss and velocity assumption approaches. Further works are required to add iterative steps in the program using more reasonable values of pressure loss and velocities, and to evaluate the sizing results using data for actual combustor performance and sizes.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.85-92
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• 2006

A design program has been developed to predict film cooling performance of a liquid rocket engine. A thermal protecting effect of low mixture ratio gas layer has been analysed by CFD. A one-dimensional film cooling model based on the CFD results has been implemented to the previously developed design program of regenerative cooling. Satisfactory agreement has been achieved by comparing the predicted maximum heat flux at the throat of a subscale chamber and the average measured value, and the predicted nozzle average heat flux and the measured value for a full scale chamber with film cooling. It is ascertained that the film cooling is effective to reduce the throat heat flux in rocket engine chamber.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.11
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• pp.1132-1138
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• 2008

A program that can simulate gas generator after burning liquid rocket engines was developed along with presenting the characteristics of the engines. The program was written in Matlab and used GUI interface so that many users can use it without any difficulties. The results of the program was compared with the real engine which was developed by the LRE advanced country. Most of the parameters concurred within 1% error expect for the pressure at the turbopump. The reasons of the large differences were supposed that pressure decreases at the schematics were smaller than that of the real engines.