The invention provides a combustion chamber, a gas turbine engine, and a combustion organization method. Wherein the combustion chamber comprises a graded fuel nozzle and a main swirler, and the main swirler and the graded fuel nozzle are coaxially arranged in the radial direction; the graded fuel nozzle comprises a central nozzle, a pre-combustion-stage swirler and an oil collecting ring; the main swirler comprises a U-shaped guide plate, a main combustion stage swirler and a main swirler outer ring; wherein the U-shaped guide plate, the main combustion stage cyclone, the main swirler outer ring and the oil collecting ring provide a main combustion stage channel; after air flow is baffled by the U-shaped guide plate, a pneumatic trapped vortex area is formed on the outer side of the main combustion stage channel, and an acceleration area is formed on the inner side of the main combustion stage channel.

    本发明提供燃烧室、燃气涡轮发动机、燃烧组织方法。其中,燃烧室包括分级燃油喷嘴以及主涡流器,所述主涡流器与所述分级燃油喷嘴径向同轴地布置;所述分级燃油喷嘴包括中心喷嘴、预燃级旋流器、集油环;所述主涡流器包括U型导流板、主燃级旋流器、主涡流器外环;其中,所述U型导流板、主燃级旋流器、主涡流器外环、集油环提供主燃级通道;其中,气流经过U型导流板折流后在主燃级通道外侧形成气动驻涡区域,在主燃级通道内侧形成加速区。


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    Titel :

    Combustion chamber, gas turbine engine, combustion organization method


    Weitere Titelangaben:

    燃烧室、燃气涡轮发动机、燃烧组织方法


    Beteiligte:
    KO HYUN-JI (Autor:in) / CHEN PAN (Autor:in) / JIA SHAOHUA (Autor:in) / XU RONG (Autor:in)

    Erscheinungsdatum :

    09.05.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F23R Erzeugen von Verbrennungsprodukten hohen Druckes oder hoher Geschwindigkeit, z.B. Gasturbinenbrennkammern , GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS



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