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초음속 엔진 모델 연소기에서의 연소불안정 및 제어 시험 기법
최호진(Hojin Choi),황용석(Yongseok Hwang),진유인(Youin Jin),박익수(Iksoo Park),윤현걸(Hyungull Yoon),강상훈(Sanghun Kang),이양지(Yangji Lee) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.5
초음속 엔진으로부터 구성한 모델 연소기를 설계/제작하여 연소시험 중 발생하는 연소불안정을 측정하고 화염안정화 장치를 이용하여 2차 연료를 분사하는 방법으로 연소불안정을 능동제어하는 기법에 관해 연구하였다. 연소실 압력측정이나 화염의 광학적 계측을 통해 연소불안정 주파수를 검출하였고, 고속으로 운용할 수 있는 마그네틱 밸브를 구동기로 선정하여 밸브 후단 압력 및 2차 분사되는 연료의 분무의 광학적 계측을 통해 연료 변조 특성을 확인하였다. The method of test for observing the combustion instability and controling the instability actively by using secondary injection of fuel through flame stabilizer was studied by constructing model combustor of supersonic engine. The frequency of combustion instability was detected by measuring the pressure of combustor using pressure sensor and by optical sensing of flame intensity. Electro-magnetic valve was adopted as actuator for active control and the characteristics of modulated fuel was studied by measured pressure of valve outlet and scattering signal of spray at secondary fuel injection.
Mach 4 Scramjet Testing in a Shock Tunnel
Gisu Park(박기수),Jongryul Byun(변종렬),Hojin Choi(최호진),Youin Jin(진유인),Kiyoung Hwang(황기영) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.5
The shock tunnel is known to be uniquely capable of simulating flow-field environments that can replicate supersonic/hypersonic flight conditions. As a consequence of the strong interest in hypersonic aerospace planes and research in Republic of Korea, attention has been given on this type of facility and the intermediate-sized shock tunnel has lately been built at KAIST. This paper discusses the performance of our tunnel and some of the recent progress made on the Mach 4 scramjet testing.
Characteristic Study of Fuel Injection into a Supersonic Flow in a Shock Tunnel
Gisu Park(박기수),Hojin Choi(최호진),Jongryul Byun(변종렬),Youin Jin(진유인),Kiyoung Hwang(황기영) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.5
Flow features of helium and ethylene transverse jets exposed in a supersonic flow have been examined experimentally. Flow visualization images were obtained in a shock tunnel using a Schlieren technique. Both the helium and the ethylene experimental data showed that jets weekly penetrate deep into the crossflow just downstream of the injection port when the velocity shear is strong at high Reynolds number. At sufficient distance downstream from the injection port, however, the jets seem to recovered their momentum and the deviations from the existing data were found to be small.