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Thermodynamic analysis on specific thrust of the hydrocarbon fueled scramjet

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  • Yang, Qingchun
  • Chang, Juntao
  • Bao, Wen

Abstract

The aim of this work is to provide an upper estimate of the theoretical maximum specific thrust of the hydrocarbon fueled scramjet. An idealized thermodynamic cycle analysis is carried out to evaluate the performance of scramjet engines at different flight conditions, inlet pressure ratio and fuel equivalence ratio. Contrary to known Brayton cycles for the gas-turbine and ramjet engine, the inherent total pressure loss with heating must be taken into account in the high speed flow of the scramjet. The results show that the specific thrust initially grows asymptotically with fuel equivalence ratio, then reaches a maximum, and finally reduces rapidly for a given flight Mach number. The optimum inlet pressure ratio and fuel equivalence ratio at which the value of the specific thrust attains a maximum are presented. Variations of maximum specific thrust with freestream Mach numbers and material temperature limit are analyzed respectively.

Suggested Citation

  • Yang, Qingchun & Chang, Juntao & Bao, Wen, 2014. "Thermodynamic analysis on specific thrust of the hydrocarbon fueled scramjet," Energy, Elsevier, vol. 76(C), pages 552-558.
    • Handle: RePEc:eee:energy:v:76:y:2014:i:c:p:552-558
    DOI: 10.1016/j.energy.2014.08.052
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    References listed on IDEAS

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    Citations

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    Cited by:

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    3. Li, Chaolong & Xia, Zhixun & Ma, Likun & Chen, Binbin & Feng, Yunchao & Zhang, Jiarui & Duan, Yifan, 2023. "Performance analysis on the specific impulse and specific thrust of scramjet with a quasi-one-dimensional model," Energy, Elsevier, vol. 267(C).
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    5. 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.
    6. Ma, Guangwei & Zhao, Guoyan & Sun, Mingbo & Xiong, Dapeng & Li, Fan & Liu, Mingjiang & Wang, Hongbo, 2024. "On compression level of hypersonic airflow in high-mach scramjet," Energy, Elsevier, vol. 295(C).
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    8. Feng, Yu & Liu, Yuna & Cao, Yong & Gong, Keyu & Liu, Shuyuan & Qin, Jiang, 2020. "Thermal management evaluation for advanced aero-engines using catalytic steam reforming of hydrocarbon fuels," Energy, Elsevier, vol. 193(C).
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    10. Seyedmatin, Pourya & Karimian, Saeed & Rostamzadeh, Hadi & Amidpour, Majid, 2020. "Electricity and hydrogen co-production via scramjet multi-expansion open cooling cycle coupled with a PEM electrolyzer," Energy, Elsevier, vol. 199(C).
    11. Yu, Xuanfei & Wang, Cong & Yu, Daren, 2019. "Precooler-design & engine-performance conjugated optimization for fuel direct precooled airbreathing propulsion," Energy, Elsevier, vol. 170(C), pages 546-556.
    12. Tian, Ke & Tang, Zicheng & Wang, Jin & Ma, Ting & Zeng, Min & Wang, Qiuwang, 2022. "Numerical investigation of pyrolysis and surface coking of hydrocarbon fuel in the regenerative cooling channel," Energy, Elsevier, vol. 260(C).
    13. Zhang, Tiantian & Wang, Zhenguo & Huang, Wei & Ingham, Derek & Ma, Lin & Porkashanian, Mohamed, 2020. "An analysis tool of the rocket-based combined cycle engine and its application in the two-stage-to-orbit mission," Energy, Elsevier, vol. 193(C).
    14. Zhang, Duo & Qin, Jiang & Feng, Yu & Ren, Fengzhi & Bao, Wen, 2014. "Performance evaluation of power generation system with fuel vapor turbine onboard hydrocarbon fueled scramjets," Energy, Elsevier, vol. 77(C), pages 732-741.
    15. Qin, Jiang & Cheng, Kunlin & Zhang, Silong & Zhang, Duo & Bao, Wen & Han, Jiecai, 2016. "Analysis of energy cascade utilization in a chemically recuperated scramjet with indirect combustion," Energy, Elsevier, vol. 114(C), pages 1100-1106.
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