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Performance Analysis of Air Turbo Ramjet using $H_2$ and $CH_4$  

이양지 (한국항공우주연구원)
차봉준 (한국항공우주연구원)
양수석 (한국항공우주연구원)
이대성 (한국항공우주연구원)
김형진 (일본 동북대학교 기계공학과)
Publication Information
Journal of the Korea Institute of Military Science and Technology / v.6, no.3, 2003 , pp. 103-110 More about this Journal
Abstract
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.
Keywords
Air Turbo Ramjet; High-Speed Propulsion; Engine Performance Analysis; Precooler; Heating Value;
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  • Reference
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