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논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2014.5
- 수록면
- 294 - 304 (11page)
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초록· 키워드
오류제보하기
A comparative study with kerosene and hydrogen fuel in a model scramjet combustor has been carried out numerically under both cold flow and hot flow conditions. The effect of the two fuels on the flow field properties for the same fuel air equivalence ratio of 0.5 in a cavity based combustion mechanism at a freestream Mach number of 2.08 has also been probed. The investigation has been carried out in a two dimensional numerical model where a cavity of length to depth (L/D) ratio of 2 is mounted on one of the walls of the flow channel. Changes in total pressure loss, fuel-air mixing and combustion efficiency were investigated for different fuels. Dependency of flow and performance characteristics on fuel properties was clearly evident from the results.
목차
ABSTRACT
1. Introduction
2. Test Setup
3. Numerical Procedure
4. Results
5. Conclusions
References
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