SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A TURBOMACHINE
    22.
    发明申请
    SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A TURBOMACHINE 审中-公开
    用于减少涡轮机燃烧动力学的系统和方法

    公开(公告)号:US20100192577A1

    公开(公告)日:2010-08-05

    申请号:US12363955

    申请日:2009-02-02

    IPC分类号: F02C7/24 F02C7/22

    摘要: A turbomachine includes a combustion chamber, and at least one pre-mixer mounted to the combustion chamber. The at least one pre-mixer includes a main body having a first end portion that extends to a second end portion. The first end portion is configured to receive an amount of fuel and an amount of air and the second end portion defines an exit plane from which a fuel-air mixture discharges into the combustion chamber. The turbomachine also includes a combustion dynamics reduction system operatively coupled to the at least one pre-mixer. The combustion dynamics reduction system includes at least one of a boundary layer perturbation mechanism and an acoustic wave introduction system which disrupt a flow pattern of the fuel-air mixture within the at least one pre-mixer.

    摘要翻译: 涡轮机包括燃烧室,以及安装在燃烧室上的至少一个预混合器。 所述至少一个预混合器包括具有延伸到第二端部的第一端部的主体。 第一端部构造成接收一定量的燃料和一定量的空气,并且第二端部限定了燃料 - 空气混合物从该出口平面排出到燃烧室中。 涡轮机还包括可操作地耦合到至少一个预混合器的燃烧动力学降低系统。 燃烧动力学降低系统包括边界层扰动机构和声波引入系统中的至少一个,其破坏在至少一个预混合器内的燃料 - 空气混合物的流动模式。