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Flow Characteristics of Liquid Ramjet Engines using Two Color PIV
Ahn, Kyubok,Yoon, Youngbin 서울대학교 항공우주신기술연구소 2001 항공우주신기술연구소 연구보고 Vol.2 No.2
A two color PIV technique has been developed for visualization of complex and high speed flow in a ramjet combustor. Two color PIV has the advantages that velocity distributions in high speed flowfields can be measured simply by varying the time interval between two different laser beams and a directional ambiguity problem can be solved by color separation, and then a signal-to-noise ratio can be increased through nearly perfect cross-correlation. As a basic research of the ramjet engine, a 2-D shaped combustor with two symmetric air intakes has been manufactured and an experimental study has been conducted using a two color PIV technique. The flow characteristics such as recirculation zones, intake air mixing and turbulent kinetic energy have been investigated varying inlet angles and dome heights. It was found that the primary recirculation zone is affected mainly by the dome height, whereas the secondary recirculation zone is influenced by the air inlet angle.
75톤급 엔진 1/2.5-scale 연소기 압력 섭동 분석
안규복(Kyubok Ahn),강동혁(Donghyuk Kang),김문기(Munki Kim),임병직(Byoungjik Lim),김종규(Jong-Gyu Kim),이광진(Kwang-Jin Lee),서성현(Seonghyeon Seo),한영민(Yeoung-Min Han),최환석(Hwan-Seok Choi) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.5
본 논문에서는 75톤급 액체로켓엔진 1/2.5-scale 연소기의 연소시험에서 얻어진 동적특성 결과에 대해 기술하였다. 엔진 시동 구간 및 연소실 압력에 따른 동적특성 변화를 살펴보기 위해 연소실 압력 30 bar와 60 bar 상태에서 연소시험이 수행되었으며 이에 따른 연소기의 연소안정성을 검토하였다. In the paper, the dynamic characteristics obtained from hot-firing tests of 1/2.5-scale thrust chamber for 75 tonf-class liquid rocket engine were described. To investigate the dynamic characteristics by engine start transient period and chamber pressure variation, hot-firing tests were performed in the chamber pressures of 30 bar and 60 bar. According to these variations, combustion stability in the combustion chamber was examined.
안규복(Ahn, Kyubok) 한국산학기술학회 2015 한국산학기술학회논문지 Vol.16 No.5
100톤급 굴삭기에 장착할 수 있는 초대형 유압브레이커 개발을 수행하였다. 유압브레이커 설계에 앞서 타격에너지, 분당 타격수 등의 성능을 예측할 수 있는 유압브레이커 해석 방법에 대해 연구하였다. 해석 결과를 바탕으로 초대형 유압브 레이커의 설계 및 제작이 이루어졌으며, 유압브레이커가 성공적으로 작동함을 확인하였다. 실제 유압브레이커 작동 시 타격 에너지와 분당 타격수를 측정하여, 해석 결과와 비교하였다. 분당 타격수 해석 결과는 큰 오차 없이 실험 결과를 잘 예측하였 지만, 타격에너지 해석 결과는 실제 실험 결과와 매우 큰 차이가 나타남을 확인하였다. 초대형 유압브레이커를 성공적으로 개발하였으며, 향후 마찰, 유압회로 등을 고려하여 타격에너지 해석 방법을 보완할 예정이다. Development of a extra-large hydraulic breaker, which could be used for a 100 ton-class excavator were carried out Hot-firing tests were carried out. Before designing a hydraulic breaker, the analysis method to predict the performance such as impact energy and impact rate were studied. Based on the analysis result, the design and manufacture of a extra-large hydraulic breaker were performed, and the breaker were confirmed to operate successfully. The data of impact energy and impact rate were measured during the operation of the breaker, and were compared with the analysis result. The analysis result of impact rate anticipated well the test data, but that of impact energy showed a large difference with the test data. The extra-large hydraulic breaker were successfully developed and the analysis method of impact energy will be updated taking into account friction, hydraulic circuit, etc.
안규복(Kyubok Ahn),강동혁(Donghyuk Kang),김문기(Munki Kim),임병직(Byoungjik Lim),김종규(Jong-Gyu Kim),서성현(Seonghyeon Seo),최환석(Hwan-Seok Choi) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
추력 75톤급 액체로켓엔진용 가스발생기의 초기 검증을 위해 축소형 모델에 대한 연소시험이 수행되었다. 본 논문에서는 축소형 가스발생기 연소시험 중 발생한 저주파 연소불안정에 대하여 분석을 수행하였다. Hot-firing tests were performed on a sub-scale gas generator for development of a 75 ton-class liquid rocket engine. This paper deals with the analysis results of low-frequency combustion instability that encountered during combustion tests of the gas generator.