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Precooler-design & engine-performance conjugated optimization for fuel direct precooled airbreathing propulsion

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

Abstract

Design study of the precooling heat exchanger specified for high speed airbreathing propulsion was carried out from the perspective of overall engine performance. The precooler proposed for the SABRE engine was adopted as the representative configuration for evaluation. Design procedure of the precooler was developed and incorporated into a cycle analysis model such that the variation in engine performance can be assessed as the design inputs is altered. By means of the differential-evolution algorithm, the design characteristics of the precooler were clarified through the idea of Pareto-Optimality. Precooler total mass and axial length, together with engine specific impulse, was included as optimization objectives on account of the results of parametric analysis. Pareto-optimal-fronts were obtained with the influence of some key design parameters such as the precooling temperature and the intake efficiency was analyzed. The results show that precooler design is a tradeoff between the optimization objectives considered. Selection of a larger precooling temperature helps to increase engine specific impulse and reduce the mass of precooler, although engine specific thrust is decreased slightly, whereas larger intake efficiency is extremely preferred for precooled cycles from not only the performance side of the engine, but more importantly, the geometry side of the precooler.

Suggested Citation

  • 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.
    • Handle: RePEc:eee:energy:v:170:y:2019:i:c:p:546-556
    DOI: 10.1016/j.energy.2018.12.192
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    References listed on IDEAS

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    Citations

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    Cited by:

    1. Lv, Chengkun & Huang, Qian & Lan, Zhu & Chang, Juntao & Yu, Daren, 2023. "Parametric optimization and exergy analysis of a high mach number aeroengine with an ammonia mass injection pre-compressor cooling cycle," Energy, Elsevier, vol. 282(C).
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    3. Li, Hui & Zou, Zhengping & Chen, Yiming & Du, Pengcheng & Fu, Chao & Wang, Yifan, 2023. "Experimental insights into thermal performance of a microtube precooler with drastic coolant properties variation and precooling impacts on turbojet engine operation," Energy, Elsevier, vol. 278(PA).
    4. 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).
    5. Pan, Xin & Xiong, Yuefei & Wang, Cong & Qin, Jiang & Zhang, Silong & Bao, Wen, 2022. "Performance analysis of precooled turbojet engine with a low-temperature endothermic fuel," Energy, Elsevier, vol. 248(C).
    6. 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).
    7. Cheng, Kunlin & Qin, Jiang & Zhang, Duo & Bao, Wen & Jing, Wuxing, 2022. "Performance evaluation for a combined power generation system of closed-Brayton-cycle and thermoelectric generator with finite cold source at room temperature on hypersonic vehicles," Energy, Elsevier, vol. 254(PC).

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