Performance Analysis of Air Turbo Ramjet using <TEX>$H_2$</TEX> and <TEX>$CH_4$</TEX>

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Journal of the Korea Institute of Military Science and Technology 2003;6(3):103-110.

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

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수소와 메탄 연료를 사용한 에어 터보 램제트 엔진의 성능해석

이양지, 차봉준, 양수석, 이대성, 김형진

¹한국항공우주연구원
²일본 동북대학교 기계공학과

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.

Key Words: Air Turbo Ramjet, High-Speed Propulsion, Engine Performance Analysis, Precooler, Heating Value