Universal Multi-Nozzle Combustion System and Method

摘要

A gas turbine combustion system includes a supporting fuel manifold including a plurality of fuel nozzle support openings and a plurality of fuel line passages, and an aft case defining at least part of a combustion zone. The supporting fuel manifold is connected to the aft case. A plurality of fuel nozzles are supported one each in the plurality of fuel nozzle support openings, and a plurality of fuel lines communicate with the plurality of fuel line passages. The plurality of fuel lines deliver fuel to the plurality of fuel nozzles via the plurality of fuel line passages.