Abstract The precooled combined cycle engines were proposed to overcome the limitation of Mach number due to high-temperature inlet. However, there has been little discussion about the thermodynamic cycle of these engines. Therefore, the current research progress and key technologies in the precooled engine thermodynamic cycle are analyzed and summarized in detail in this study. The main precooled engines, specifically ATREX and SABRE, are compared. The engine precooling cycle can be divided into direct and indirect precooling cycles. By comparing the performance of the direct precooling cycle ATREX engine in the non-precooling and precooling modes, the advantages of this engine in terms of specific thrust, compressor boost ratio, and flight Mach number are examined. The SABRE engine with an indirect precooling cycle not only solves the problem of hydrogen embrittlement of the precooler, but also achieves higher thrust and specific impulse than the ATREX engine. However, the ATREX engine with a direct precooling cycle is simpler in structure and has less adjusting variables, and thus, it is suitable for application in high-speed aircraft with a low flow rate. In addition, comparing the precooling cycle working mediums, the hydrogen medium shows excellent performance but has a limited aircraft flight range. Conversely, the use of a hydrocarbon fuel in the aircraft results in a longer flight range but with relatively low performance. Therefore, a development trend toward multi-fuel hybrid use can be expected.

    Highlights According to the precooling mode, the main pre-cooed engines are classified. The thermal cycles of engine are divided into direct and indirect precooling cycle. Compared with SABRE, ATREX is more suitable to be used as power unit of small flow and high-speed aircraft. The performances of various precooled fuels are compared and analyzed. A combination of multiple fuels may provide more balance and better overall performance than a single fuel.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Key technologies for thermodynamic cycle of precooled engines: A review


    Beteiligte:
    Jian, Dai (Autor:in) / Qiuru, Zuo (Autor:in)

    Erschienen in:

    Acta Astronautica ; 177 ; 299-312


    Erscheinungsdatum :

    2020-07-25


    Format / Umfang :

    14 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Cryogenic Heat Exchangers - Key Technologies for Precooled Turbojet Engines

    Folomeev, E.A. / Svetlakov, E.A. / Galkin, S.M. et al. | SAE Technical Papers | 1991


    Thermal Management of Precooled ATREX Engine with Expander Cycle

    Kobayashi, H. / Tanatsugu, N. / Sato, T. et al. | British Library Conference Proceedings | 1999


    Hydrogen Fueled Precooled Airbreathing Engines for Hypersonic Aircraft and Spaceplanes

    Hendrick, P. / Verstraete, D. | British Library Conference Proceedings | 2011


    Hypersonic Vehicle/Deeply Precooled Combined Cycle Engine Integration Analysis

    Zheng, Shangzhe / Chen, Yuchun / Wang, Jiahui et al. | IEEE | 2022


    New Defrosting Method Using Jet Impingement for Precooled Turbojet Engines

    Fukiba, Katsuyoshi / Inoue, Shou / Ohkubo, Hidetoshi et al. | AIAA | 2009