Method of fuel nozzle sizing and sequencing for a gas turbine combustor

A method of providing a gas turbine engine having a generally consistent flow of fluid to a plurality of combustors distributed about said engine, said method comprising the steps:

• providing a plurality of combustors arranged about a gas turbine engine, each of said combustors having an end cover, 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, a plurality of nozzle mounts fixed to said second face and in fluid communication with said feed passages, and a plurality of nozzles fixed to said plurality of nozzle mounts, such that each of said end covers has a known assembly flow rate;
• providing a supply system having a supply inlet, main supply tube, and a plurality of conduits extending from said main supply tube, each of said conduits having a conduit inlet adjacent said main supply tube, a conduit exit proximate said fluid inlet of said end cover, and an effective flow area;
• providing a fluid medium having a first pressure, a first temperature, and a first flow rate to said supply inlet;
• determining a second pressure of said fluid medium at each of said conduit exits;
• determining a second temperature of said fluid medium at each of said conduit exits;
• utilizing said second pressure, said second temperature, and said effective flow area, to determine a second flow rate for each of said conduits;
• utilizing said first flow rate, said second flow rates, and said assembly flow rates, to place each of said end covers about said gas turbine engine and in fluid communication with said supply system such that each of said end covers injects said fluid medium to each of said combustors at a generally consistent third flow rate.