Patent ID: 6883329

Claim:
A method of providing a generally consistent fluid flow from a plurality of nozzles to a gas turbine combustor, said method comprising the steps: providing an end cover fixed to said gas turbine combustor, said end cover having a first face, a second face, a first thickness therebetween, a fluid inlet, a manifold in fluid communication with said fluid inlet, a plurality of feed passages in fluid communication with said manifold, and a plurality of nozzle mounts fixed to said second face and in fluid communication with said feed passages; providing a plurality of nozzles each having a nozzle inlet and plurality of injector holes having an effective flow area; providing a fluid medium having a first pressure, a first temperature, and a first flow rate to said fluid inlet of said end cover; determining a second pressure of said fluid medium at each of said nozzle inlets; determining a second temperature of said fluid medium at each of said nozzle inlets; utilizing said second pressure, a predetermined external pressure, said effective flow area, and said second temperature, to determine a second flow rate for each of said plurality of nozzles; utilizing said first flow rate and said second flow rates, to place each of said nozzles at said nozzle mounts, such that each of said nozzles injects said fluid medium to said gas turbine combustor at a generally consistent third flow rate.