AXIAL FUEL STAGING SYSTEM FOR GAS TURBINE COMBUSTORS

The invention provides an axial fuel staging system for gas turbine combustors. The gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner 40 defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing 130 radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly 160 mounted to the liner, and an injector unit 110 attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. 本公开提供一种用于燃气涡轮机燃烧器的轴向燃料分级系统。所述燃烧器包括：头端，所述头端包括一次燃料喷嘴；衬里，所述衬里限定位于所述头端附近的一次燃烧区域以及下游二次燃烧区域；前壳体，所述前壳体位于所述衬里的至少一部分的径向外部并且围绕所述衬里的至少一部分；以及所述轴向燃料分级系统。所述轴向燃料分级系统包括多个燃料喷射组件。每个燃料喷射组件包括安装到所述衬里的套管组件，以及附接到所述前壳体的喷射器单元。所述套管组件的套管延伸穿过所述衬里中的套管孔。