The present invention relates to fuel delivery systems for gas turbine engines and particularly to liquid fuel control valves for industrial gas turbine engines.
An industrial gas turbine typically includes a combustor section including combustion cans, e.g., cylindrical combustion chambers, arranged in an annular array around the casing of the gas turbine. Fuel pipes deliver liquid fuel to each the combustion cans. The fuel valves may also pass water to the combustion cans to purge the fuel system the combustion cans to purge the fuel system.
Fuel valves coupled to the fuel pipes turn-on and turn-off the flow of fuel to the combustion cans. Each combustion can has at least one associated fuel valve. There may be more than one fuel valve associated with each combustion can if the can has primary and secondary fuel nozzles, and if fuel flows from multiple sources to the combustion can.
The fuel valves, fuel pipes and other fuel system components form a complex web near around the combustion section of the gas turbine. There is a long felt need to simplify and reduce the components that form the web around the combustion section.