• Journal of the Korean Institute of Gas
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• v.25 no.6
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• pp.22-28
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• 2021

Combustion characteristics were examined experimentally for a swirl-stabilized double cone premixed burner nozzle used for industrial gas turbines for power generation. An original model and a variant with a different fuel injection pattern are tested to compare their combustion characteristics such as NOx, CO and stability in pressurized conditions with single burner-flame and in an ambient multi-flame conditions with multi-burners. Test results show that NOx emissions are smaller for the variant, whose number of fuel holes is reduced with the same total area of fuel holes, in ambient and pressurized single-flame conditions with single burner, which results from enhanced fuel/air mixing due to a higher penetration of fuel into the air stream. The multi-burnerflame test results show that NOx emissions are smaller for the variant due to reduced flame interactions, which, on the contrary, slightly reduces the stability margin. On-site test results fromin an actual power plants also show that NOx emissions are reduced for the variant, compared with the original one, which is in agreement with the lab test results stated above.

• Journal of Aerospace System Engineering
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• v.11 no.1
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• pp.8-13
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• 2017

This study was performed to evaluate the turbine performance of a turbopump in the third stage engine of the Korea Space Launch Vehicle-II. The turbine is a supersonic impulse type with a single rotor. One nozzle is for starting and four remaining nozzles are for steady operation. A similarity test was carried out in the high air test facilities at the Korea Aerospace Research Institute. Test results showed that turbine efficiency changed much more from rotational speed variations than by pressure ratio variations. These results showed characteristics similar to other supersonic impulse turbines.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.196-199
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• 2011

Subscale high-pressure injection system which use two-stage light gas gun composed with high-pressure tube, pump tube and launch tube can make supersonic liquid jet. The supersonic liquid jet enhances droplet atomization by shockwave in front of the jet. In this study, the experiments was executed to identify the atomization characteristics of the supersonic liquid jet using straight cone nozzle. SMD which presents the atomization characteristics was decreased from $151.2{\mu}m$ to $52.25{\mu}m$ by increasing of L/d.

• Journal of ILASS-Korea
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• v.9 no.1
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• pp.1-7
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• 2004

This paper describes the characteristics of injection rate and macroscopic behavior of fuel spray injected from common-rail type diesel injectors with different nozzle geometries. The injection rates according to the nozzle geometries were measured at different energizing duration of the injector solenoid and injection pressure by using the Bosch's injection rate meter based on the pressure variation in the tube. The spray behaviors injected from the different nozzles were visualized using the spray visualization system composed of an Ar-ion laser, an ICCD camera, and a synchronization system at various injection and ambient pressures. It is revealed that VCO nozzle has higher spray tip velocity at the early stage of injection duration and wider spray cone angle than the mini-sac nozzles. Also the spray cone angle is increased with the increase of nozzle diameter.

• Proceedings of the Materials Research Society of Korea Conference
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• 2011.05a
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• pp.66.1-66.1
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• 2011

반도체를 비롯하여 LCD, OLED와 같은 디스플레이 (FPD: Flat Panel Display) 분야는 국가 선도 사업으로써 발전을 거듭해오고 있다. 하지만 기술의 성숙도가 높아짐에 따라 최근 중국과 대만 업체와의 경쟁이 심화되고 있으며, 더불어 환경문제가 큰 이슈로 떠오르고 있어 신기술 개발을 통한 생산 수율 향상 및 친환경 공정 개발의 중요성이 커지고 있다. 반도체, 디스플레이 공정에서 생산 수율 저하의 주요 원인으로써 공정 중 발생하는 미세 오염 입자를 들수 있다. 반도체 및 디스플레이 공정에서 세정 기술은 전체 기술의 30% 이상을 차지하며 생산 수율 및 제품의 품질에도 큰 영향을 주는 공정이다. 세정 공정은 일반적으로 습식 세정 공정이 낮은 공정비용을 바탕으로 널리 적용되어 왔으나, 기판의 대형화와 패턴의 미세화에 따라 정밀한 세정 스펙이 요구되며 더불어 막대한 양의 초순수와 화학액의 사용으로 인한 공정비용 증가와 환경 규제 강화에 따른 폐수 처리의 문제에 직면하고 있다. 이에 따라 폐수의 양을 줄이며 건조공정을 필요로 하지 않아 공정비용을 줄일 수 있는 건식 세정 공정에 대한 연구가 활발히 진행 되고 있다. $CO_2$ snow jet 세정 기술은 건식 공정으로써 $CO_2$ 가스를 특수하게 제작된 분사 노즐에서 고압으로 가스를 분사하여 이 때 발생되는 순간적인 감압에 의한 단열 팽창으로 생성된 $CO_2$ snow 입자가 기판 표면의 오염물과 물리적 충돌을 하어 세정이 이루어지는 기술이다. 특히 $CO_2$ 세정은 환경과 인체에 무해하며 공정 후 바로 승화하기 때문에 추가적인 폐수처리 공정 등이 필요하지 않고, 건식 공정으로써 수세(Rinse) 공정을 필요로 하지 않기 때문에, 공정비용을 크게 줄일 수 있으며 물반점 발생을 방지 할 수 있는 친환경 건식 공정으로써의 장점을 가지고 있다. 본 연구에서는 자체적으로 개발한 $CO_2$ snow jet을 바탕으로 하여 다양한 공정조건을 변화시켜 세정효율을 측정하는 한편, 최적화 하기 위한 연구를 진행하였으며 더불어 $CO_2$ snow의 세정력을 정량적으로 평가하기 위한 연구를 진행하였다. 실험을 통해 가장 효과적으로 $CO_2$ snow 입자를 배출 할 수 있는 공정 조건으로써 5 bar의 캐리어 가스 압력을 사용하여, 세정력에 가장 큰 영향을 줄 수 있는 분사 노즐과 기판 사이의 거리 및 분사 노즐의 각도 등을 변화시켜 각 조건에 따른 세정효율을 평가하였다. 세정 오염물은 Silica, PSL 표준 입자(Duke scientific, USA)를 정량적으로 웨이퍼에 오염 시킨 후, 파티클 스캐너(Surfscan 6500, KLA-Tencor, USA)를 이용하여 세정 전 후의 오염입자 개수 변화를 통해 정량적으로 세정효율을 평가하였다. 본 연구를 통하여 $CO_2$ snow jet를 이용한 친환경 고효율 건식 세정 공정 메커니즘을 분석하였으며, 노즐과 기판 사이의 간격 및 분사 노즐의 각도 등을 최적화 한 세정 공정을 얻을 수 있었다.

• Transactions of the Korean Society of Automotive Engineers
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• v.21 no.4
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• pp.89-95
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• 2013

In this work, the evaluation of swirl nozzle injector performance was conducted by investigating effective area ($A_{eff}$), injection mass ($m_{inj}$), injection rate ($Q_{inj}$), and injection delay ($t_{delay}$) under various test conditions. To achieve these, fuel injection analysis system which was composed of fuel supply system, injection system, and control system was installed. At the same time, the swirl nozzle that had 12 orifice hole with $120^{\circ}$ injection angle was used in this work. It was revealed that the difference of injection mass ($m_{inj}$) between base and swirl nozzle injector increased as the injection pressure ($P_{inj}$) and energizing duration ($t_{eng}$) decreased under the same test conditions. The maximum injection rate ($Q_{inj}$) of swirl nozzle injector was higher than base nozzle injector about 2~5%. The injection performance of swirl nozzle was better than base nozzle at low injection pressure ($P_{inj}$) and short energizing duration ($t_{eng}$) conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.128-134
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• 2007

Combustion performance and characteristics of high-pressure subscale liquid rocket combustors were studied experimentally. Four different models of combustor were considered in this paper. The high-pressure subscale combustor is composed of the mixing head, the water cooling cylinder and the nozzle. One model of the combustors employed regenerative cooling combustor in that the kerosene used for the chamber cooling is burned. This combustor was damaged due to a high frequency combustion instability occurred during a firing test. The results of the firing tests, comparison of performance, and characteristics of static and dynamic pressures of the combustors are described.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2011.11a
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• pp.426-429
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• 2011

산불 발생 시 진화를 위해 사용되는 주력 지상 진화장비 중 동력펌프 2종과 진화 차량을 대상으로 수원지로부터 발화 지점까지 진화거리에 따른 주요 성능을 측정하였다. 성능 측정은 분당 토출량, 토출 최대압력, 수평 분사거리, 수직 분사거리의 4개 항목이었으며, 노즐의 종류에 따른 영향을 동시에 고려하였다. 산불 진화 시 적정 거리를 측정한 결과 소형펌프의 경우 600m, 중형펌프의 경우 800~1000m 정도인 것으로 나타났다. 또한 분당 토출량은 3가지 펌프 모두 50m에서 1000m로 연결할 경우 52~62% 감소가 일어나며, 최대 토출압력은 26~30% 상승되어 부하 발생시 고압호스의 파손 우려도 있는 것을 알 수 있었다. 실험을 통해 소형펌프의 경우는 주 산불진화에 적합하지 않으며, 중형펌프의 경우 고압호스의 성능에 따라서 1000m이상의 거리에서도 사용이 가능할 것으로 사료된다.

• Journal of Advanced Navigation Technology
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• v.22 no.2
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• pp.90-95
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• 2018

In the solid rocket motor (SRM), a thrust of rocket is generated by a nozzle so it is very important device. The nozzle of SRM is a condition of high temperature and high pressure so occurs the erosion by combustion gas. The liquid rocket propulsion systems (LRPSs) cools the nozzle by the fuel and oxidizer but SRM does not cool the nozzle. This paper deal with the development of the oxy-acetylene torch tester and investigate the thermochemical erosion properties for the thermal insulation materials of the graphite rocket nozzle throat through the experiment. The results of experiments are compared with the results of Theoretical model and identify the key factors affecting of erosion. The results is in good agreement with the experimental data.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.163-172
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• 2002

The turbine system composed of a nozzle and a rotor is used to drive turbopumps while gas passes through the nozzle, potential energy is converted to kinematic energy, which forces the rotor blades to spin. In this study, an aerodynamic design of a turbine system is investigated using compressible fluid dynamic theories with some pre-determined design requirements (i.e.,pressure ratio, rotational speed, required power etc.) obtained from a liquid rocket engine (L.R.E.) system design. For simplicity of a turbine system, impulse-type rotor blades for open type L.R.E. have been chosen. Usually, the open-type turbine system requires low mass flow rate compared to the close-type system. In this study, a partial admission nozzle is adopted to maximize the efficiency of the close-type turbine system. A design methodology of the a turbine system has been introduced. Especially, a partial admission nozzle has been designed by means of simple empirical correlations between efficiency and configuration of the nozzle. Finally, a turbine system design for a 10 ton thrust level of L.R.E is presented.