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Thermodynamic assessment on performance extremes of the fuel indirect precooled cycle for hypersonic airbreathing propulsion

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  • Yu, Xuanfei
  • Wang, Cong
  • Yu, Daren

Abstract

Fuel indirect precooled cycles (IPC) are attractive candidate to enable next generation reusable launch vehicle. Thermodynamic analysis was carried out to bound the performance of this innovative propulsion concept. A unified model which can represent the core working principle of the whole engine family was proposed to make the analysis possible, with which the conditions in determining the performance boundaries of the family were derived, and new efficiency figure (i.e., EoP) for the precooling-compression sub-cycle (PCS) was defined. Numerical method for the model was developed also to perform the parametric analysis. The results show that the cycle performance is bounded by two extremes, with the upper and lower of which are defined by the EoP of 100% and 0 respectively. For real engines, the state of the art design practice gives an EoP level of 10–30%. Moreover, it indicates that fuel properties possess remarkable effects on the PCS, whereas hydrogen shows the best application potential. From the standpoint of system overall design, optimum choice for the EoP and fuel equivalence ratio are proposed, with the performance superiority of the IPC over the Brayton cycles is revealed, and the impacts of the intake and combustor performance on the extremes are clarified.

Suggested Citation

  • Yu, Xuanfei & Wang, Cong & Yu, Daren, 2019. "Thermodynamic assessment on performance extremes of the fuel indirect precooled cycle for hypersonic airbreathing propulsion," Energy, Elsevier, vol. 186(C).
    • Handle: RePEc:eee:energy:v:186:y:2019:i:c:s0360544219314434
    DOI: 10.1016/j.energy.2019.07.102
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    Citations

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    Cited by:

    1. 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).
    2. Lv, Chengkun & Xu, Haiqi & Chang, Juntao & Wang, Youyin & Chen, Ruoyu & Yu, Daren, 2022. "Mode transition analysis of a turbine-based combined-cycle considering ammonia injection pre-compressor cooling and variable-geometry ram-combustor," Energy, Elsevier, vol. 261(PB).
    3. Ambe Verma, Kumari & Murari Pandey, Krishna & Ray, Mukul & Kumar Sharma, Kaushal, 2021. "Effect of transverse fuel injection system on combustion efficiency in scramjet combustor," Energy, Elsevier, vol. 218(C).
    4. Wang, Cong & Yu, Xuanfei & Ha, Chan & Liu, Zekuan & Fang, Jiwei & Qin, Jiang & Shao, Jiahui & Huang, Hongyan, 2023. "Thermodynamic analysis for a novel chemical precooling turbojet engine based on a multi-stage precooling-compression cycle," Energy, Elsevier, vol. 262(PA).
    5. Wang, Cong & Yu, Xuanfei & Pan, Xin & Qin, Jiang & Huang, Hongyan, 2022. "Thermodynamic optimization of the indirect precooled engine cycle using the method of cascade utilization of cold sources," Energy, Elsevier, vol. 238(PB).
    6. Yu, Xuanfei & Wang, Cong & Yu, Daren, 2020. "Series view method based thermodynamic modeling and analysis for innovative precooled aeroengines with different turbine-compressor coupling schemes," Energy, Elsevier, vol. 205(C).
    7. 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).
    8. Wang, Cong & Feng, Yu & Liu, Zekuan & Wang, Yilin & Fang, Jiwei & Qin, Jiang & Shao, Jiahui & Huang, Hongyan, 2022. "Assessment of thermodynamic performance and CO2 emission reduction for a supersonic precooled turbine engine cycle fueled with a new green fuel of ammonia," Energy, Elsevier, vol. 261(PA).

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