公开(公告)号：US20150354826A1

公开(公告)日：2015-12-10

申请号：US14727977

申请日：2015-06-02

Applicant: ALSTOM Technology Ltd

Inventor： Uwe RÜDEL ,  Urs BENZ ,  Christoph APPEL ,  Ivan LENUZZI

IPC: F23R3/50 ,  F23R3/00 ,  F23R3/60 ,  F02C3/14 ,  F02C7/18 ,  F23R3/16 ,  F02C3/04

CPC classification number: F23R3/50 ,  F01D9/023 ,  F02C3/04 ,  F02C3/14 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/30 ,  F23R3/002 ,  F23R3/16 ,  F23R3/48 ,  F23R3/60 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02E20/16

Abstract: The invention relates to an annular combustion chamber of a gas turbine having a machine axis. The combustion chamber includes at least two zones. A first zone receives the fuel/air mixture of a plurality of burners. A second zone guides the hot gases being produced by the burners from the first zone to an entrance of a turbine section of said gas turbine. An annular transition liner includes a plurality of liner segments located at the transition between said first zone and second zone. Each of the liner segments includes with respect to the axial hot gas flow a leading edge, a trailing edge, and two sidewalls, and is provided with axial mounting means at the leading and trailing edges, such that the liner segment can be installed in axial direction and is axially fixed by respective segments of the neighboring first zone. Local spacer ribs are provided at the leading edge of the liner segments in order to establish a gap of minimum width between the liner segments and the fixing segments of the neighboring first zone.

Abstract translation: 本发明涉及具有机器轴线的燃气轮机的环形燃烧室。 燃烧室包括至少两个区域。 第一区域接收多个燃烧器的燃料/空气混合物。 第二区域将由燃烧器产生的热气体从第一区域引导到所述燃气涡轮机的涡轮机部分的入口。 环形过渡衬套包括位于所述第一区和第二区之间的过渡处的多个衬垫段。 每个衬里段相对于轴向热气流包括前缘，后缘和两个侧壁，并且在前缘和后缘处设置有轴向安装装置，使得衬套段可以安装在轴向 方向并且由邻近的第一区的相应段轴向地固定。 局部间隔肋设置在衬垫段的前缘处，以便建立衬垫段与相邻第一区的固定段之间的最小宽度的间隙。