公开(公告)号：EP2400219A2

公开(公告)日：2011-12-28

申请号：EP11250599.5

申请日：2011-06-20

申请人： United Technologies Corporation

发明人： Smith, Graig F. ,  Alholm, Hannes A. ,  Eastwood, Jonathan J. ,  Duhamel, Dennis J. ,  Burns, David A ,  Barnett, Claude I.Jr ,  Danburg. Randy J. ,  Melman, Jeffrey D. ,  Wiley, David R. ,  Pacheco-Tougas, Monica

IPC分类号： F23R3/00

CPC分类号： F23R3/002 ,  F23R2900/00017 ,  F23R2900/00018

摘要： A combustor liner cap assembly (130) is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate (34) having a plurality of fuel nozzle openings (35) and a plurality of open ended premix tubes (30) extending aft from the tube plate (34). Each premix tube (30) has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. The forward end of each premix tube extends at least to a forward face of the tube plate. Each premix tube may be fixed to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing.

摘要翻译： 燃烧器衬套盖组件（130）被提供用于燃气轮机的多燃料喷嘴燃烧室。 燃烧器衬套组件包括具有多个燃料喷嘴开口（35）和从管板（34）后面延伸的多个开放式预混合管（30）的管板（34）。 每个预混管（30）具有前端具有前边缘，前端被接收在对应的一个燃料喷嘴开口中。 每个预混管的前端至少延伸到管板的前面。 每个预混管可以固定到预混合管前端的前边缘的管板，例如通过焊接或钎焊冶金结合。