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스크램제트 엔진 흡입구 시험을 위한 자유제트형 지상추진시험설비의 마하 5 성능 검증
이양지,양인영,이경재,오중환,최진 한국추진공학회 2022 한국추진공학회지 Vol.26 No.1
In order to perform the scramejt engine intake ground test using the Scramjet Engine Test Facility(SETF) of the Korea Aerospace Research Institute. we introduced the test availability check procedure that is generally conducted. The design process of the newly manufactured Mach 5 nozzle for the scramjet intake test was summarized, a device for checking the core flow distribution of the nozzle was explained, and the core flow test analysis results were written. Through a series of test results, it was confirmed that the intake was located in the new Mach 5 nozzle core. 한국항공우주연구원 스크램제트 엔진 시험설비를 활용한 스크램제트 엔진 흡입구 지상 시험을 수행하기 위하여 일반적으로 진행하는 시험 가능 여부 확인 절차를 소개하였다. 스크램제트 흡입구 시험을 수행하기 위하여 새롭게 제작된 마하 5 노즐의 설계 과정을 정리하였으며, 노즐의 코어 유동 분포를 확인하기 위한 장치를 설명하고 코어 유동 시험 분석 결과를 기록하였다. 일련의 시험 결과를 통하여 흡입구가 신규 마하 5 노즐 코어에 위치하는 것을 확인하였다.
자유제트형 지상추진 시험설비를 사용한 스크램제트 엔진 흡입구의 마하 5 성능시험
이양지,양인영,이경재,오중환,최진,Lee, Yang Ji,Yang, Inyoung,Lee, Kyung Jae,Oh, Jung Hwan,Choi, Jin 한국추진공학회 2022 한국추진공학회지 Vol.26 No.4
The performance analysis test of the scramjet engine intake was conducted under the Mach 5 condition of the scramjet engine test facility, a free-jet ground test facility of the Korea Aerospace Research Institute. A pitot/static pressure rake installed at the rear of the isolator was designed and manufactured to measure the total pressure recovery rate and mass capture ratio, which are typical performance factors of the scramjet engine intake. The effect of the rake mounted at the rear of the isolator on the intake, the performance analysis measured by the rake, and the change in wall static pressure distribution according to the angle of attack were performed. Finally, the point at which the intake unstart occurred was confirmed by using the rear back pressure adjusting device, which simulates pressure rise in the combustor, and the results are summarized in this paper.
Starting characteristics of the hypersonic wind tunnel with the mach number variation
이양지,강상훈,양수석,권세진 대한기계학회 2014 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.28 No.6
The scramjet engine test facility (SETF) of the Korea Aerospace Research Institute is a blow-down, high enthalpy wind tunnel with afree-jet test cell. The free-jet test sections can reduce choking and test larger models compared with solid wall test sections, but the facilityneeds an excessive starting pressure ratio and is highly unpredictable because of the free-jet space. An air ejector system was designedto simulate a Mach 3.5 test condition. Quasi one-dimensional and computational analyses of the ejector were performed. The test resultsof the ejector well agree with the analysis results. The SETF showed a normal-shock efficiency of 58% at the Mach 3.5 condition. The airejector system was modified to conduct a scramjet intake test with a Mach 6.7 condition. The normal-shock efficiency of the SETF was40% with the Mach 6.7 condition. There was almost no change in the starting pressure ratio due to blockage.
경계층 배출을 적용한 스크램제트 엔진 흡입구의 성능 분석
이양지,양인영,이경재,이상훈,오중환,최진 한국추진공학회 2024 한국추진공학회지 Vol.28 No.1
스크램제트 엔진 흡입구의 램프와 격리부에 다수의 다공 홀을 배치하고 이를 통한 경계층 배출이 흡입구의 성능에 미치는 영향을 분석하는 연구를 수행하였다. 본 연구는 경계층 배출 홀의 유/무, 다공도, 그리고 밀집도를 변수로 하였으며, 경계층 배출 미적용(기준형상) 포함 7개 형상을 시험하였다. 결과적으로 기준형상 대비 경계층 배출 형상들이 시동 영역 확장 및 전반적인 성능 지표가 개선되었다. 전압력 회복률과 격리부 출구 마하수 등 전반적인 성능을 분석했을 때 가장 좋은 성능을 보인 형상은 다공도가 가장 낮은 지름 1 mm, 폭 10 mm로 경계층 배출 유량이 작은 것이 흡입구 성능개선에 유리함을 확인하였다. 밀집도는 중앙 편중보다 균등하게 A study was conducted to analyze the effect of boundary layer bleeding on the performance of the intake by multiple bleeding holes in the ramp and isolator of a scramjet intake. In this study, the presence/absence of bleeding holes, porosity and the degree of concentration of bleeding holes were used as variables, and 7 configurations including baseline(no bleed holes) were tested. As a result, compared to the baseline, the boundary layer bleeding configurations expanded the starting range of an intake and improved performance indicators. The configuration that showed the best performance was 1 mm in diameter and 10 mm in width with the lowest porosity. It is judged that it would be advantageous to distribute the bleeding holes more evenly rather than centrally or to place them on the side walls where the boundary layer is expected to develop.A study was conducted to analyze the effect of boundary layer bleeding on the performance of the intake by multiple bleeding holes in the ramp and isolator of a scramjet intake. In this study, the presence/absence of bleeding holes, porosity and the degree of concentration of bleeding holes were used as variables, and 7 configurations including baseline(no bleed holes) were tested. As a result, compared to the baseline, the boundary layer bleeding configurations expanded the starting range of an intake and improved performance indicators. The configuration that showed the best performance was 1 mm in diameter and 10 mm in width with the lowest porosity. It is judged that it would be advantageous to distribute the bleeding holes more evenly rather than centrally or to place them on the side walls where the boundary layer is expected to develop.
수소와 메탄 연료를 사용한 에어 터보 램제트 엔진의 성능해석
이양지,차봉준,양수석,이대성,김형진 한국군사과학기술학회 2003 한국군사과학기술학회지 Vol.6 No.3
The present work was conducted to achieve the better understanding of the performance analysis technique for the expander type air turbo ramjet engine. For this purpose, the performance analysis was carried out using a small engine(8.0kN thrust) with two types of fuels. From this analysis, at the same input condition, the thrust of methane-fueled engine was 25% lower than that of hydrogen. In addition, the case of methane shows the inapplicable engine performance cycle.(i.e., The compressor work exceeds the turbine output power) These results come mainly from the different heating value of each fuel and specific heat. This analysis also shows that, to build a same performance cycle as the hydrogen case, the methane-fueled engine requires increased air and fuel flow rates, increased turbine expansion ratio, and decreased compressor pressure ratio.