• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.479-483
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• 2012

This paper describes the development status of rocket engine test facility for the performance evaluation of liquid rocket engine of KSLV-II 1st stage. Design specification and composition of rocket engine test facility are suggested based on the design requirements. The results of the basic design of rocket engine test facility will be used as base data for the detail design and construction of rocket engine ground test facility of KSLV-II 75tonf liquid rocket engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1994.04a
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• pp.23-26
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• 1994

130mm D.B. 추진기관의 고온 시험에서 나타난 극심한 이상 연소 현상을 해결하기 위해 미세한 고체 입자들을 연소 가스에 분산시켜 불안정 연소를 억제하는 particulate damping 효과를 연구하였다. 고체 입자로서 효과적인 것으로 알려진 $K_2$$SO_4$. ZrC, Graphite를 CTPB, HTPB 고분자 물질에 충진시켜 epoxide, isocyanate 반응기와 가교 반응을 일으킴으로써 고무상의 탄성체 성질을 갖게 하는 $K_2$$SO_4$/CTPB, ZrC/Graphite/HTPB, ZrC/Graphite/AP/HTPB, ZrC/AP/HTPB 조성의 연소 안정제를 개발하였다. 이 연소 안정제는 외경 17mm, 길이 1000mm의 안정봉 형태로 제작하여 모타의 중심 cavity에 조립한 후 지상 연소 시험을 통하여 성능을 확인하였다. 시험 결과, 조성에 AP를 포함시켜 연소 안정제에 일정한 연소 속도를 부여하여 추진제 grain 연소 동안 고체 입자를 연소 가스에 분산되게 설계한 ZrC/Graphite/AP/HTPB, ZrC/AP/HTPB 조성의 연소 안정제가 불안정 연소 억제에 효과적인 것으로 나타났다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.405-406
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• 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 Korean Society of Propulsion Engineers
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• v.15 no.1
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• pp.69-75
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• 2011

Firing tests have been carried out for a technology demonstration model of 75-tonf-class combustor which is to be used on the liquid rocket engine of a Korean space launch vehicle. Firing tests were done at 50% of the nominal flow rate because of incapability of the test facility and limit of the test bed strength. Through the low pressure firing tests of 75-tonf-class channel cooling thrust chamber, operability and stability at the ignition and combustion phases were confirmed. Additionally it was foreseen that the 75-tonf-class thrust chamber would satisfy the performance requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.71-74
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• 2010

Using the technology demonstration model of 75-tonf-class combustor which is expected to be used to the rocket engine of a korean space launch vehicle, 2 times of firing tests were carried out. Firing tests were done at 50% of the nominal flow rate because of incapability of the test facility and limit of the test bed strength. Through the low pressure firing tests of 75-tonf-class channel cooling thrust chamber, reliability and stability at the ignition and combustion phases were confirmed. Additionally it was foreseen that the 75-tonf-class thrust chamber would satisfy the performance requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.97-100
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• 2009

Cold flow and ignition tests were performed for a technology demonstration model of a 75-tonf thrust chamber which is a candidate liquid rocket engine for a next Korea Space Launch Vehicle. The test facility was modified to support the new concepts of the thrust chamber such as ignition system, film cooling and LOx leading supply. The hydrodynamic characteristics of the supply pipelines, thrust chamber and igniter as well as the filling time of the propellants were obtained through the cold flow tests on the LOx and kerosene and the ignition cyclogram was determined using the results. The ignition test was successfully accomplished according to the cyclogram and therefore, a basic information was obtained for further hot firing tests.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1999.05a
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• pp.39-44
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• 1999

발전용 연료로 사용하는 석탄은 취급의 어려움과 가스 및 석유에 비해 품질이 낮은 단점이 있으나, 매장량이 풍부하고 가격이 저렴하여 발전용 연료로의 사용은 더욱 증대될 전망이다. 이에 따라 석탄의 안정적 수급 측면에서 구입원의 다양화가 예상되고 있으나, 현재 발전용 연료의 연소특성 평가는 주로 실험실적 기초 시험에 의존함에 따라 정확한 평가가 곤란한 실정이므로 시험연소로를 이용하여 각종 연소특성을 비교 평가하여 탄종별 최적 연소조건 규명과 적정 흔탄비에 대한 Data Base를 구축하고자 한다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1994.04a
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• pp.16-22
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• 1994

2.75인치 MK4/40 및 MK66 추진기관용 연소관의 국산화 개발을 목적으로 가공 열처리와 유동성형 공정을 조합한 열가공 유동성형 공정을 적용하여 치수제어시험을 하고 개발품과 수입 연소관을 비교하여 물성 및 구조시험을 실시하여 그 결과를 비교 분석하였다. 개발된 연소관은 수입연소관에 비하여 제작공정이 단축되었고, 열가공 유동성형 공정보다 치수제어에 유리하며, 내경 및 두께 규격을 만족하였다. 또한 물성 및 구조시험 결과 수입 연소관에 비하여 우수한 성질을 나타내었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.3
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• pp.32-40
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• 2006

Dynamic Radioscopy technique was developed to observe internal phenomena of motors during firings. For use of this technique, generator and image box consisting of conversion screen, mirror, and video camera were designed and fabricated at our laboratory, and static firing tests were conducted to small motors. Protection devices against vibration and noise induced from during combustion were also made and their performances were evaluated with reference to the vibration criteria. Test results have shown that the vibration levels at concerned points were measured less than vibration criteria, and the internal phenomena during firings were also observed clearly.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.163-168
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• 2006

The combustion performance tests of a 30 tonf-class full-scale combustion chamber performed with kerosene as a coolant were described. The combustion chamber has chamber pressure of 53bara and propellant flow mass rate of 90kg/s. Since it was first firing test for 30tonf-class combustion chamber using kerosene cooling, kerosene coolant mass flow rate of 32kg/s which correspond to 120% of design mass flow rate were performed. Then, the firing test with kerosene mass flow rate of 25kg/s were successfully performed. The test results are described and the results showed that the kerosene cooling performance of this combustion chamber is sufficient and the firing test with regenerative cooling is feasible.