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    • 7. 发明授权
    • Combustion chamber of a gas turbine working on liquid fuel
    • 燃气轮机燃油室用于液体燃料
    • US06378310B1
    • 2002-04-30
    • US09238586
    • 1999-01-28
    • Jean-Hervé Le GalPatrick FlamentGérard MartinGuy GriencheGérard Schott
    • Jean-Hervé Le GalPatrick FlamentGérard MartinGuy GriencheGérard Schott
    • F02C100
    • F23R3/44F23C7/004F23D11/38F23R3/14F23R3/28F23R3/58
    • A combustion chamber of a gas turbine working on liquid fuel includes a tubular enclosure (2) having at least one pressurized air inlet, a liquid fuel injection means (6) positioned on or in proximity to the longitudinal axis (XX′) of the tubular enclosure, and an outlet to the turbine. The fuel injection means (6) includes a series of orifices (62) arranged so as to create separate fuel jets, the jets being arranged in the direction of the generatrices of a cone with an angle ranging between 30° and 60° at the vertex thereof. The chamber includes at least two types of pressurized air inlets placed close to each other, the first one (7) taking in the air helically around the longitudinal axis of the combustion chamber, the second air inlet (8) being tangential to enclosure (2) so as to create, around the fuel jets, counterrotating flows intended to improve mixing of the air and of said fuel. The assembly preferably works at a pressure ranging between 2 and 30 bars and with a fuel/air ratio ranging between 0.4 and 0.8.
    • 工作在液体燃料上的燃气轮机的燃烧室包括具有至少一个加压空气入口的管状外壳(2),位于管状的纵向轴线(XX')上或附近的液体燃料喷射装置(6) 外壳和到涡轮机的出口。 燃料喷射装置(6)包括一系列孔口(62),其布置成产生单独的燃料喷嘴,喷射器沿锥体的母线方向布置,其顶点的角度在30°和60°之间 其中。 该室包括彼此靠近放置的至少两种类型的加压空气入口,第一个(7)以螺旋形方式围绕燃烧室的纵向轴线吸入空气,第二空气入口(8)与外壳(2)相切 ),以便在燃料喷嘴周围产生用于改善空气和所述燃料混合的逆转流。 该组件优选地在2和30巴之间的压力下工作,燃料/空气比范围在0.4和0.8之间。