Patent ID: 8365533
Filing Date: 2013-02-05
Classification: F02C,F05D,F23R

Abstract:
1. A gas turbine combustion system comprising: a supporting fuel manifold including a plurality of fuel nozzle support openings and a plurality of fuel line passages, the plurality of fuel nozzle support openings arranged as one or more concentric arrays surrounding a center nozzle support opening, the fuel support manifold defining at least part of a combustion zone; an aft case defining a central longitudinal axis, the supporting fuel manifold being connected to the aft case; a center nozzle supported in the center nozzle support opening, the center nozzle sharing the central longitudinal axis with the aft case; a plurality of fuel nozzles, each of the fuel nozzles being supported in a respective one of the plurality of fuel nozzle support openings; and a plurality of fuel lines communicating with the plurality of fuel line passages, the plurality of fuel lines delivering fuel to the plurality of fuel nozzles via the plurality of fuel line passages.