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Overall performance design of paralleled heat release and compression system for hypersonic aeroengine

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  • Dong, Pengcheng
  • Tang, Hailong
  • Chen, Min
  • Zou, Zhengping

Abstract

The hydrogen powered hypersonic precooled combined cycle engine is an ideal candidate for next generation high speed clean civil aviation propulsion. It utilizes the energy inside the high speed air flow to power the air compression, in order to improve engine performance. Paralleled heat release and compression system, with several separated channels, is proved to be a crucial component to guarantee the favourable performance of the hypersonic precooled combined cycle engine. The system can sharply reduce the fuel consumption and cycle compressor pressure ratio (over 34% reduction in fuel consumption and over 45% reduction in cycle compressor pressure ratio, compared with ordinary single-route flow path design). The system is theoretically and quantitatively analysed. Operation mechanism, parameters design, feasibility and installing effects of the system are discussed. A performance simulation model is built for the paralleled system. The equivalent component method is proposed for measuring its effect on the engine overall performance. Inside the system, higher compression efficiency, lower pressure loss, more branches, higher heat transfer capacity and heat exchanger effectiveness can enhance the performance, while the feasible region, weight and size effects, and technical risks cannot be ignored either. For the engine, the installation of the paralleled system remarkably improves the engine performance and simplifies the compressor design. The paralleled system, with its advantage of coolant flow and compression work reduction, also can be beneficial to other applications in energy and power field.

Suggested Citation

  • Dong, Pengcheng & Tang, Hailong & Chen, Min & Zou, Zhengping, 2018. "Overall performance design of paralleled heat release and compression system for hypersonic aeroengine," Applied Energy, Elsevier, vol. 220(C), pages 36-46.
    • Handle: RePEc:eee:appene:v:220:y:2018:i:c:p:36-46
    DOI: 10.1016/j.apenergy.2018.03.062
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    References listed on IDEAS

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    Cited by:

    1. Deng, Li & Chen, Min & Tang, Hailong & Zhang, Jiyuan, 2024. "Performance evaluation of multicombustor engine for Mach3+-Level propulsion system," Energy, Elsevier, vol. 295(C).
    2. Zhang, Jiyuan & Tang, Hailong & Chen, Min, 2019. "Linear substitute model-based uncertainty analysis of complicated non-linear energy system performance (case study of an adaptive cycle engine)," Applied Energy, Elsevier, vol. 249(C), pages 87-108.
    3. Wang, Cong & Cheng, Kunlin & Qin, Jiang & Shao, Jiahui & Huang, Hongyan, 2022. "Performance comparison of three chemical precooled turbine engine cycles using methanol and n-decane as the precooling fuels," Energy, Elsevier, vol. 249(C).
    4. 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.
    5. 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).
    6. 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).
    7. Xin Meng & Zhili Zhu & Min Chen & Yihao Xu, 2021. "A Matching Problem between the Front Fan and Aft Fan Stages in Adaptive Cycle Engines with Convertible Fan Systems," Energies, MDPI, vol. 14(4), pages 1-33, February.
    8. Wang, Busheng & Xuan, Yimin, 2023. "An integrated model for energy management of aero engines based on thermodynamic principle of variable mass systems," Energy, Elsevier, vol. 276(C).

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