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    Comprehensive Performance Analysis of the Turbofan With a Multi-Annular Rotating Detonation Duct Burner

    Source: Journal of Engineering for Gas Turbines and Power:;2020:;volume( 142 ):;issue: 002
    Author:
    Ji, Zifei
    ,
    Zhang, Huiqiang
    ,
    Wang, Bing
    ,
    He, Wei
    DOI: 10.1115/1.4045518
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The performance analysis of mixed-exhaust turbofan engine with multi-annular rotating detonation duct burner (RDDB) is conducted for the first time, considering that the flow path of the bypass duct is ideal for a rotating detonation combustor (RDC). The configuration of the multi-annular rotating detonation combustor is constructed aiming at the advantages of a wider operation range and uniform outlet parameters over the single-annular one. Then, a parametric analysis model of the mixed-exhaust turbofan engine with a rotating detonation duct burner is developed. Thereafter, the effects of duct burner parameters on the engine performance and operating characteristics are investigated. The mixed-exhaust turbofan engine with a rotating detonation duct burner shows superior overall performance to that of one with an isobaric afterburner (ICAB) over a wide operation range. The separate-exhaust rotating detonation duct burner can hold characteristics that are higher than those of the mixed-exhaust one at lower values of fan pressure ratio, while the mixed-exhaust one corresponds to lower values of turbine inlet temperature. When the rotating detonation duct burner is “on,” the low-pressure rotor operating line moves toward the surge line on the low corrected shaft speed side but away from the surge line on the high corrected shaft speed side.
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      Comprehensive Performance Analysis of the Turbofan With a Multi-Annular Rotating Detonation Duct Burner

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    http://yetl.yabesh.ir/yetl1/handle/yetl/4273595
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    contributor authorJi, Zifei
    contributor authorZhang, Huiqiang
    contributor authorWang, Bing
    contributor authorHe, Wei
    date accessioned2022-02-04T14:24:22Z
    date available2022-02-04T14:24:22Z
    date copyright2020/01/10/
    date issued2020
    identifier issn0742-4795
    identifier othergtp_142_02_021007.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4273595
    description abstractThe performance analysis of mixed-exhaust turbofan engine with multi-annular rotating detonation duct burner (RDDB) is conducted for the first time, considering that the flow path of the bypass duct is ideal for a rotating detonation combustor (RDC). The configuration of the multi-annular rotating detonation combustor is constructed aiming at the advantages of a wider operation range and uniform outlet parameters over the single-annular one. Then, a parametric analysis model of the mixed-exhaust turbofan engine with a rotating detonation duct burner is developed. Thereafter, the effects of duct burner parameters on the engine performance and operating characteristics are investigated. The mixed-exhaust turbofan engine with a rotating detonation duct burner shows superior overall performance to that of one with an isobaric afterburner (ICAB) over a wide operation range. The separate-exhaust rotating detonation duct burner can hold characteristics that are higher than those of the mixed-exhaust one at lower values of fan pressure ratio, while the mixed-exhaust one corresponds to lower values of turbine inlet temperature. When the rotating detonation duct burner is “on,” the low-pressure rotor operating line moves toward the surge line on the low corrected shaft speed side but away from the surge line on the high corrected shaft speed side.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleComprehensive Performance Analysis of the Turbofan With a Multi-Annular Rotating Detonation Duct Burner
    typeJournal Paper
    journal volume142
    journal issue2
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.4045518
    page21007
    treeJournal of Engineering for Gas Turbines and Power:;2020:;volume( 142 ):;issue: 002
    contenttypeFulltext
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