Patent ID: 8286414

Claim:
A gas turbine combustor provided with a plurality of fuel nozzles and a pressure control system for controlling fuel supply pressure to said fuel nozzles, comprising: fuel pipes defining a path for gas fuel to flow from an upstream fuel inlet to said fuel nozzles, including a main fuel pipe and a distribution fuel pipe to said fuel nozzles; a fuel flow rate control valve for controlling fuel flow in said distribution fuel pipe to said fuel nozzles; and a pressure control valve disposed in said main fuel pipe, upstream from said fuel flow rate control valve, wherein said pressure control system is a non-transitory tangible memory device operatively coupled to said pressure control valve and to said fuel flow rate control valve to control a pressure downstream of said pressure control valve and flow through said fuel flow rate control valve, said control system selectively setting a fuel pressure reference for control of the pressure control valve based on a compressor discharge pressure, CPD.