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Thermodynamic analysis on optimum performance of scramjet engine at high Mach numbers

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  • Zhang, Duo
  • Yang, Shengbo
  • Zhang, Silong
  • Qin, Jiang
  • Bao, Wen

Abstract

In order to predict the maximum performance of scramjet engine at flight conditions with high freestream Mach numbers, a thermodynamic model of Brayton cycle was utilized to analyze the effects of inlet pressure ratio, fuel equivalence ratio and the upper limit of gas temperature to the specific thrust and the fuel impulse of the scramjet considering the characteristics of non-isentropic compression in the inlet. The results show that both the inlet efficiency and the temperature limit in the combustor have remarkable effects on the overall engine performances. Different with the ideal Brayton cycles assuming isentropic compression without upper limit of gas temperature, both the maximum specific thrust and the maximum fuel impulse of a scramjet present non-monotonic trends against the fuel equivalence ratio in this study. Considering the empirical design efficiencies of inlet, there is a wide range of fuel equivalence ratios in which the fuel impulses remain at high values. Moreover, the maximum specific thrust can also be achieved with a fuel equivalence ratio near this range. Therefore, it is possible to achieve an overall high performance in a scramjet at high Mach numbers.

Suggested Citation

  • Zhang, Duo & Yang, Shengbo & Zhang, Silong & Qin, Jiang & Bao, Wen, 2015. "Thermodynamic analysis on optimum performance of scramjet engine at high Mach numbers," Energy, Elsevier, vol. 90(P1), pages 1046-1054.
    • Handle: RePEc:eee:energy:v:90:y:2015:i:p1:p:1046-1054
    DOI: 10.1016/j.energy.2015.08.017
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    References listed on IDEAS

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    Cited by:

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