新型氢能超音速混合推进系统总体性能及匹配机理分析

  • 李富霖 ,
  • 陈敏 ,
  • 唐海龙 ,
  • 郑俊超 ,
  • 张纪元
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  • 1. 北京航空航天大学 能源与动力工程学院
    2. 能源与动力工程学院仿真中心
    3. 北京航空航天大学
    4. 清华大学
    5. 北京航空航天大学,航空发动机研究院

收稿日期: 2025-12-30

  修回日期: 2026-05-10

  网络出版日期: 2026-05-14

基金资助

国家自然科学基金资助项目;航空发动机气动热力国家级重点实验室基金;航空发动机气动热力国家级重点实验室基金

Overall Performance and Matching Mechanism Analysis of a Novel Hydrogen Supersonic Hybrid Propulsion System

  • LI Fu-Lin ,
  • CHEN Min ,
  • TANG Hai-Long ,
  • ZHENG Jun-Chao ,
  • ZHANG Ji-Yuan
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  • 1.
    2. Beihang University
    3. Tsinghua University

Received date: 2025-12-30

  Revised date: 2026-05-10

  Online published: 2026-05-14

摘要

超音速民机由于其广泛的应用潜力,近年来受到了越来越多的关注。然而,目前的推进循环方案在满足超音速民机的性能需求方面面临显著挑战,主要矛盾在于无法协调高速与低速运行相互冲突的循环参数要求。本研究提出了一种以混排涡扇发动机为基底,集成氢能、间冷换热和高温燃料电池的新型超音速民机用混合推进系统,并对这一新型推进概念建立了性能仿真模型,分析了这种新型热-电耦合循环的匹配机理。该推进循环结合了传统燃气轮机与电力推进的优点,间冷模块缓解了压气机出口温度超限问题,热电耦合的设计还缓解了大功率需求状态下发动机热端部件的高气动负荷和热负荷,降低热端部件设计难度并提高工作裕度。本文对这一构型的平衡运行方程进行了数学推导,并在新发展的基于非线性部件的混合推进系统性能模型的基础上,探索部件匹配原理的物理本质。同时,对这一新型推进系统的关键设计参数优化选取方法进行了探究,并给出了基于上述方法得到的最佳总体性能设计方案及总体性能计算结果。

本文引用格式

李富霖 , 陈敏 , 唐海龙 , 郑俊超 , 张纪元 . 新型氢能超音速混合推进系统总体性能及匹配机理分析[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33307

Abstract

In recent years, supersonic civil aircraft have garnered increasing interest for their broad potential applications. However, existing propulsion cycle concepts encounter significant challenges in meeting the performance demands of such aircraft, primarily due to the conflicting requirements of cycle parameters for high and low-speed operations. To address this issue, a novel hybrid propulsion system for supersonic civil aircraft is proposed, incorporating a hybrid turbofan engine that integrates hydrogen, intercooling heat transfer, and high-temperature fuel cells. This propulsion cycle amalgamates the benefits of conventional gas turbines and electric propulsion. The intercooling module mitigates issues related to compressor outlet temperature surpassing limits, while the thermoelectric coupling design alleviates high aerodynamic and thermal loads on engine components during high power demands. Consequently, this design reduces the complexity of hot-end component design and enhances operational flexibility. This study mathematically derives the equilibrium equations for this configuration and delves into the physical underpinnings of the component matching principle using a novel performance model based on nonlinear components for the hybrid propulsion system. Additionally, it explores an optimization approach for key design parameters of the new propulsion system, presenting an optimal overall performance design scheme and performance calculations based on the aforementioned methodologies.

参考文献

[1]Ding Y B, Yue X K, Chen G S, Si J S.Review of con-trol and guidance technology on hypersonic vehicle[J].Chinese Journal of Aeronautics, 2022, 35(7):1-18
[2]Kurzke J.The mission defines the cycle: turbojet, turbofan and variable cycle engines for high speed propulsion[J]. NATO Science and Technology Organ-ization, RTO-EN-AVT-185, 2010.
[3]Tang M, Chase R.The quest for hypersonic flight with air-breathing propulsion[C]//15th AIAA Interna-tional Space Planes and Hypersonic Systems and Technologies Conference. 2008: 2546.
[4]Wang Z G, Wang Y, Zhang J Q, Zhang B C.Overview of the key technologies of combined cycle engine precooling systems and the advanced applications of micro-channel heat transfer[J]. Aerospace Science and Technology, 2014, 39: 31-39.[J].Aerospace Science and Technology, 2014, 39:31-39
[5]Dong P C, Tang H L, Chen M, Zou Z P.Overall per-formance design of paralleled heat release and com-pression system for hypersonic aeroengine[J]. Ap-plied Energy, 2018, 220: 36-46.
[6]Lee D J, Yan J, Chou S K, et al.Clean, efficient, af-fordable and reliable energy for a sustainable fu-ture[J]. Energy Conversion and Management, 2015, 102: 1-3.
[7]Sun Y C, Smith H.Review and prospect of supersonic business jet design[J]. Progress in Aerospace Sciences, 2017, 90: 12-38.
[8]Willis E A, Welliver A D.Supersonic variable-cycle engines[C]//Propulsion Conf. 1976 (NASA-TM-X-73524).
[9]Chen M, Deng L, Zhang J, et al.Review on the de-velopment status and performance deign of adaptive cycle engines[J].Propulsion and Power Research, 2025, 14(1):35-63
[10]Johnson J E.Variable cycle engine developments[J]. Developments in High-Speed-Vehicle Pro-pulsion Systems, 1995, 165: 121-122.[J].Developments in High-Speed-Vehicle Pro-pulsion Systems, 1995, 165:121-122
[11]Deng L, Chen M, Tang H L, Zhang J Y.Performance evaluation of multicombustor engine for Mach3+-Level propulsion system[J]. Energy, 2024, 295: 130992.
[12]Dai J, Zuo Q R.Key technologies for thermodynamic cycle of precooled engines: A review[J]. Acta Astro-nautica, 2020, 177: 299-312.
[13]Varvill R, Bond A.The Skylon spaceplane: progress to realisation[J].Journal of the British Interplanetary Society, 2008, 61(10):412-418
[14]Varvill R.Heat exchanger development at Reaction Engines Ltd[J].Acta Astronautica, 2010, 66(9-10):1468-1474
[15]Sato T, Taguchi H, Kobayashi H, et al.Development study of a precooled turbojet engine[J].Acta Astro-nautica, 2010, 66(7-8):1169-1176
[16]Taguchi H, Harada K, Kobayashi H, et al.Mach 4 wind tunnel experiment of hypersonic pre-cooled tur-bojet engine[C]//19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. 2014: 2790.
[17]Taguchi H, Hongoh M, Kojima T, et al.Mach 4 per-formance evaluation of hypersonic pre-cooled turbo-jet engine[C]//22nd AIAA International space Planes and hypersonics systems and Technologies Confer-ence. 2018: 5203.
[18]Taguchi H, Hongoh M, Kojima T, et al.Mach 4 Pro-pulsive Performance Evaluation of Hypersonic Pre-Cooled Turbojet Engine[C]//23rd AIAA International Space Planes and Hypersonic Systems and Technolo-gies Conference. 2020.
[19]Taguchi H, Kobayashi H, Kojima T, et al.Perfor-mance evaluation of hypersonic pre-cooled turbojet engine[C]//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. 2015: 3593.
[20]Li H, Zou Z, Chen Y, et al.Experimental insights into thermal performance of a microtube precooler with drastic coolant properties variation and precooling impacts on turbojet engine operation[J]. Energy, 2023, 278: 127916.
[21]Jiang G H, Chen M, Tang H L, et al.Matching mech-anism of a novel variable cycle propulsion concept with hydrogen intercooling[J]. Energy, 2025: 134682.
[22]Li F, Chen M, Tang H, et al.Analysis of overall per-formance and matching mechanism of a novel hy-drogen mixed-flow turbofan hybrid electric propul-sion system[J]. Energy, 2025: 139163.
[23]Yin F J, Rao A G.A review of gas turbine engine with inter-stage turbine burner[J]. Progress in Aerospace Sciences, 2020, 121: 100695.
[24]Wei Z Y, Jafari S, Zhang S, et al.Hybrid Wiener mod-el: an on-board approach using post-flight data for gas turbine aero-engines modelling[J]. Applied Ther-mal Engineering, 2021, 184: 116350.
[25]Yin F J, Rao A G.Off-design performance of an inter-stage turbine burner turbofan engine[J].Journal of Engineering for Gas Turbines and Power, 2017, 139(8):082603-
[26]Lyu Y, Tang H L, Chen M.A study on combined vari-able geometries regulation of adaptive cycle engine during throttling[J].Applied Sciences, 2016, 6(12):374-
[27]Zhang J Y, Tang H L, Chen M.Linear substitute mod-el-based uncertainty analysis of complicated non-linear energy system performance (case study of an adaptive cycle engine)[J]. Applied Energy, 2019, 249: 87-108.
[28]Kurzke J.Advanced user-friendly gas turbine perfor-mance calculations on a personal computer[M]. American Society of Mechanical Engineers, 1995.
[29]Kurzke J.How to get component maps for aircraft gas turbine performance calculations[M]. American Society of Mechanical Engineers, 1996.
[30]骆广琦等.航空燃气涡轮发动机数值仿真[M]. 北京: 国防工业出版社, 2007: 49-81.
[31]龚昊.间冷回热涡扇发动机循环参数优化及间冷回热器设计方法研究[D]. 西安: 西北工业大学, 2017: 38-41.
[32]Walsh P P, Fletcher P.Gas Turbine Performance (2nd edition) [M]. UK: Blackwell Science Ltd, Oxford, 2004: 241-246.
[33]徐乐根, 毛军逵, 梁凤丽, 等.直接氨-混合动力系统性能及航空应用[J].航空动力学报, 2024, 39(4):170-184
[34]Ji Z, Qin J, Cheng K, et al.A comprehensive evaluation of ducted fan hybrid engines integrated with fuel cells for sustainable aviation[J]. Renewable and Sus-tainable Energy Reviews, 2023, 185: 113567.[J].Renewable and Sustainable Energy Reviews, 2023, 185(113567):-
[35]Guo F, Qin J, Ji Z, et al.Performance analysis of a turbofan engine integrated with solid oxide fuel cells based on Al-H2O hydrogen production for more elec-tric long-endurance UAVs[J]. Energy Conversion and Management, 2021, 235: 113999.[J].Energy Conversion and Management, 2021, 235(113999):-
[36]姬志行, 王占学, 程莉雯, 等.燃料电池燃气涡轮航空混合推进系统总体性能及匹配分析[J].航空学报, 2024, 45(10):165-178
[37]Dooner DB.Kinematic Geometry of Gearing[M]. 1st ed. Wiley, 2012: 43-49.
[38]Pellegrino G, Vagati A, Boazzo B, et al.Comparison of induction and PM synchronous motor drives for EV application including design examples[J].IEEE Transactions on industry applications, 2012, 48(6):2322-2332
[39]Zheng J C, Chen M, Tang H L.Matching mechanism analysis on an adaptive cycle engine[J].Chinese Journal of Aeronautics, 2017, 30(2):706-718
[40]朱之丽, 陈敏, 唐海龙等.航空燃气涡轮发动机工作原理及性能(第3版)[M]. 上海: 上海交通大学出版社, 2023: 22-28.
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