Patent ID: 8429917

Claim:
A method for delivering fuel in a gas turbine engine including a can annular combustor array that includes at least one combustor level subset within the array supplied by an independent fuel delivery system, said method comprising: supplying fuel to a first combustor level subset through a primary staging valve that controls fuel flow to the entire first combustor subset, wherein the primary staging valve is oriented between a fuel pump and a primary manifold, wherein the primary manifold is coupled to the first combustor subset; and supplying fuel to a second combustor level subset through a secondary staging valve that controls fuel flow to the entire second combustor subset, wherein the secondary staging valve is oriented between the fuel pump and a secondary manifold, wherein the secondary manifold is coupled to the second combustor subset, and wherein a computer controller controls the first and second staging valves such that the first and second staging valves are selectively closeable independent of each other, opening the first staging valve and closing the second stage valve in a first operating mode such that fuel is channeled only to the first combustor subset, wherein the first operating mode is an engine startup operating mode; and opening the first and second staging valves in a second operating mode such that fuel is channeled independently via the fuel delivery system to the first and second combustor subsets, wherein the second operating mode is a base load operating mode.