• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.11a
• /
• pp.405-406
• /
• 2008

Combustor is one of the major component of gas turbine engine and its development is done mostly by performance test. Combustors for aviation gasturbine engines has been successfully tested at the test facility in KARI as well as for stationary gasturbine engines. Full scale combustor test requires large amount of high temperature and pressure air, so the test facility is equipped with big air compressor and heater.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.9 no.4
• /
• pp.137-144
• /
• 2006

The basic data obtained in this research for single element performance were directly applied to the design of injector head(7 elements). Designed performance of the 7-element Swirl Coaxial injector was $245kg_f$ sea level thrust with 20bar combustion chamber pressure. Numerical analysis were performed to obtain the change of spray pattern for the design of injector head, and we confirmed the feasibility and application of those results. Hot tests were performed for the multi-element injector to compare with the performance of the single element injector and those can be applied to the design of scaled liquid rocket engine. The basic data obtained in this research can be directly applied to the real liquid rocket injector design.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.3
• /
• pp.69-76
• /
• 2012

An achieving method of highly progressive pressure gradient is presented to enhance the missile ejection system's performance by using a gas generator in the condition of preventing erosive burning. To obtain and confirm a stable burning, a ground burning test was performed to evaluate the new methods of a radial-hole and a multi-row propellant grain. The test results show that a radial-hole grain takes good effect on erosive burning and not on ejection performance. On the other hand, a multi-row grain which reduces the length-to-diameter ratio(L/D) of grain is very effective to prevent the erosive burning and to enhance the ejection performance simultaneously.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.432-439
• /
• 2011

An achieving method of highly progressive pressure gradient is presented to enhance the missile ejection system's performance by using a gas generator in the condition of preventing erosive burning. To obtain and confirm a stable burning, a ground burning test was performed to evaluate the new methods of a radial-hole and a multi-row propellant grain. The test results show that a radial-hole grain takes good effect on erosive burning and not on ejection performance. On the other hand, a multi-row grain which reduces the legnth-to-diameter ratio(L/D) of grain is very effective to prevent the erosive burning and to enhance the ejection performance simultaneously.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.18 no.2
• /
• pp.52-59
• /
• 2014

The effect of ceramic thermal barrier coating thickness on the cooling performance of a liquid-propellant rocket engine combustor has been investigated through combustion/cooling performance analysis whose results verified against measured data from hot-firing tests. Also have been confirmed the effects of film cooling amount near the face plate on the coolant temperature and on the thermal barrier coating surface temperature. Some important points to be considered for designing cooling schemes for regeneratively cooled rocket engine combustor have been drawn and reviewed from present study and further verification of the analysis tool should be performed in the future.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.7 no.4
• /
• pp.63-72
• /
• 2003

The combustion characteristics of the KSR-III engine were investigated numerically from the viewpoint of performance and combustion field. For numerical analysis of KSR-III engine with hub-and-spoke baffle, 3-D calculation was performed about $30^{\cire}$ section and the prediction of performance was in a good agreement with hot-firing test result. As a result of baffle installed, the performance of KSR-III engine was reduced in comparison with no baffle case and local high temperature region appeared on injector plate, combustion wall and baffle wall, This calculation was used practically as basic data for designing injector plate with film cooling holes and predicting the performance of KSR-III final flight test.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.8
• /
• pp.111-121
• /
• 2005

A 100kW class gas turbine combustor was developed and tested for PPU(Primary Power Unit) of ground vehicle. The combustor which employed annular-reverse type and pressure swirl atomizer was designed through 1-D analysis, 3-D thermal flow analysis and combustor performance was experimentally investigated on the combustor test rig. The test result was satisfactory. The developed combustor was also tested for environmental and endurance specification under engine adopted conditions and the application of a state-of-the-art gas turbine combustor to ground vehicle PPU turned out to be successful.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.05a
• /
• pp.10-13
• /
• 2010

Low pressure combustion tests for TDM(Technology Demonstration Model) of 75 tonf thrust chamber were performed. It has design chamber pressure of 60 bar, propellant mass flow rate of 243.6 kg/s. Due to the limitation of the current firing test facility in Korea, the combustion tests were conducted to verify the operation and the combustion performance at low pressure condition (30 bar, 121.8 kg/s). All the tests had been successfully executed without the damage of the hardware. These test results can be used as fundamental data to predict the combustion performance at design point condition for 75 tonf thrust chamber.

• Proceedings of the Korean Nuclear Society Conference
• /
• 1996.05c
• /
• pp.244-250
• /
• 1996

고리 2호기에서 2주기 동안 연소된 1개 KOFA 연료봉에 대한 조사후 검사결과, 핵분열기체 방출량 및 소결체 밀도가 연료봉 설계코드의 예측범위내에 있음을 확인하였으며, 소결체의 미세구조 및 연료봉내의 축방향 분포 검사를 통해 $UO_2$ 소결체가 아무 이상이 없이 안정적으로 연소되었음을 확인하였다. 단지 1개 연료봉에 대한 조사후 검사만으로는 KOFA 핵연료 $UO_2$ 소결체의 노내 거동을 검증하였다고는 할수 없기 때문에 연소된 핵연료에 대한 지속적인 조사후 검사가 필요한 것으로 사료된다. 특히 한국형원자로의 핵연료인 영광 3호기 핵연료에 대해 조사후 검사를 수행하고, 또한 일부 시험연료봉을 고연소도까지 연소시킨후 조사후 검사를 수행하면, 핵연료의 성능 검증뿐만 아니라 국내 고유의 핵연료 성능자료를 생산하게됨으로써, 앞으로 국내 고유의 고연소도핵연료개발 및 연료봉성능분석코드 개발에 활용할 수 있다.

• Journal of the korean Society of Automotive Engineers
• /
• v.11 no.6
• /
• pp.80-88
• /
• 1989

본 연구에서는 양산중인 배기량 2.4Liter, 간접분사방식의 소형 디젤엔진에서 연소방식을 직접 분사방식으로 연소계를 재설계하여, 간접분사방식과 직접분사방식에 따른 엔진성능상의 차이점을 비교 평가하고, 아울러 직접분사방식에서 연소실 형상과 연소 관련 주요 인자들의 변경시 엔 진성은에 미치는 영향에 대해 고찰하였다. 직접분사방식 엔진은 간접분사방식 엔진에 대해 동 일출력, 동일 Smoke 수준인 경우 10-15%의 연료소비 저감의 효과가 있고, 이에 따라 연소관련 부품의 열부하면에서도 유리하였으나, 소음 및 NOx 배출은 증가하는 것으로 나타났다. 직접분사 연소방식에서는 Deep Bowl 연소실 형태의 Cylindrical Type 과 Re-entrant Type 에서 연비와 Smoke 등을 고려한 최적 분사시기가 Re-entrant Type 에서 4.deg. CA정도 늦었으며, 각기 최적 분사시기에서 스옴, NOx를 비교한 결과 Re-entrant Type이 더 우수하였다.