Patent ID: 8499542

Claim:
A fuel system for a gas turbine comprising: a fuel supply; a multistage combustor having fuel injectors organized operatively in stages including a first stage having a first fuel injector and a second fuel injector; a first stage fuel metering module fluidly connecting the fuel supply to the first and second fuel injectors; and a flow balancing valve fluidly connecting the first stage fuel metering module and the first and second fuel injectors, the flow balancing valve including: a first pressure feedback line fluidly connected to a first burn line, and a first metering port fluidly located in the first burn line and connected to the first fuel injector; a first input line connecting the first stage fuel metering module to the first burn line; a second pressure feedback line fluidly connected to a second burn line, and a second metering port fluidly located in the second burn line and connected to the second fuel injector; a second input line connecting the first stage fuel metering module to the second burn line; first and second annuli fluidly connected to the first and second pressure feedback lines, respectively; first and second lands fluidly connected to the first and second annuli, respectively; and a metering land attached between the first and second lands, the metering land located between and defining sizes of the first metering port and the second metering port, wherein an increase in pressure differential between the first pressure feedback line and the second pressure feedback line causes a compensatory movement in the metering land to balance fuel flow for the first fuel injector and the second fuel injector.