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    Gas turbine combustor
    3.
    发明公开
    Gas turbine combustor 审中-公开

    公开(公告)号：EP1775516A3

    公开(公告)日：2010-06-30

    申请号：EP06255344.1

    申请日：2006-10-17

    申请人： United Technologies Corporation

    发明人： Burd, Steven W. ,  Sowa, William ,  Cheung, Albert K. ,  Kramer, Stephen K. ,  Hokes, James ,  Smith, Reid Dyer Curtis

    IPC分类号： F23R3/50

    CPC分类号： F23R3/50

    摘要： A combustor assembly (12) includes a convergent segment (34) followed by a divergent segment (36) to advantageously improve combustion. The combustor assembly includes a first segment (34) beginning at a forward end (24) that transitions to a second segment (36) past a transition segment (58) in a direction along a combustor axis (22) toward an aft end (26). The reduction in cross-sectional area within the first segment (34) provides desirable fuel and air mixing properties. The convergent first segment (34) in combination with the divergent second segment (36) decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

    Gas turbine combustor
    4.
    发明公开
    Gas turbine combustor 有权
    Gasturbinenbrennkammer

    公开(公告)号：EP1795809A2

    公开(公告)日：2007-06-13

    申请号：EP06255163.5

    申请日：2006-10-06

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Burd, Steven W ,  Cheung, Albert K ,  Dempsey, Dae K ,  Hoke, James B ,  Kramer, Stephen K ,  Ols, John T ,  Smith, Reid Dyer Curtis ,  Sowa, William A

    IPC分类号： F23R3/50 ,  F23R3/04

    CPC分类号： F23R3/50 ,  F23R3/04 ,  Y02T50/675

    摘要： A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.

    摘要翻译： 燃气涡轮发动机具有燃烧器模块，该燃烧器模块包括环形燃烧器，该环形燃烧器具有限定具有长度L的环形燃烧室的衬套组件。衬套组件包括径向内衬，围绕内衬的径向外衬套和隔板 具有高度H1，其在内衬套的各个前端和外衬套之间延伸。 燃烧器具有在内衬和外衬里内部的各个后端处的出口高度H3。 环形燃烧器具有小于或等于1.7的值的比率H1 / H3。 环形燃烧器也可以具有小于或等于6.0的值的比例L / H3。

    Gas turbine combustor
    5.
    发明公开
    Gas turbine combustor 审中-公开
    燃气轮机燃烧室

    公开(公告)号：EP1775516A2

    公开(公告)日：2007-04-18

    申请号：EP06255344.1

    申请日：2006-10-17

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Burd, Steven W. ,  Sowa, William ,  Cheung, Albert K. ,  Kramer, Stephen K. ,  Hokes, James ,  Smith, Reid Dyer Curtis

    IPC分类号： F23R3/50

    CPC分类号： F23R3/50

    摘要： A combustor assembly (12) includes a convergent segment (34) followed by a divergent segment (36) to advantageously improve combustion. The combustor assembly includes a first segment (34) beginning at a forward end (24) that transitions to a second segment (36) past a transition segment (58) in a direction along a combustor axis (22) toward an aft end (26). The reduction in cross-sectional area within the first segment (34) provides desirable fuel and air mixing properties. The convergent first segment (34) in combination with the divergent second segment (36) decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

    摘要翻译： 一个燃烧器组件（12）包括一个收敛段（34），后面跟着一个扩张段（36），以有利地改善燃烧。 燃烧器组件包括在前端（24）开始的第一部分（34），该第一部分在沿着燃烧器轴线（22）的方向上朝向后端（26）过渡到经过过渡部分（58）的第二部分（36） ）。 第一段（34）内的横截面积的减小提供了期望的燃料和空气混合特性。 会聚的第一部分（34）与发散的第二部分（36）结合减少了燃烧室内燃料 - 空气混合物的停留时间，这减少了来自燃烧室组件的不希望的排放物的产生。