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A gas turbine combustion system having: a plurality of combustion chambers; a plurality of fuel nozzles for each of combustion chamber; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers; each of the manifolds having fuel trim control valves fo

A gas turbine combustion system having: a plurality of combustion chambers; a plurality of fuel nozzles for each of combustion chamber; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers; each of the manifolds having fuel trim control valves for the fuel nozzles, wherein the fuel trim control valves are mounted on the multiple manifolds for metering the fuel to the fuel nozzles in the combustion chambers, and a trim valve controller automatically actuates one or more of the fuel trim valves to adjust fuel to the fuel nozzles based on gas turbine operating conditions.

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What is claimed is: 1. A gas turbine combustion system comprising: a plurality of combustion chambers; a plurality of fuel nozzles for each of said combustion chambers; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers, wherein the manifolds

What is claimed is: 1. A gas turbine combustion system comprising: a plurality of combustion chambers; a plurality of fuel nozzles for each of said combustion chambers; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers, wherein the manifolds have differing fuel flow capacities; the manifolds having a flow metering devices for the fuel nozzles, wherein the flow metering devices are mounted on the manifolds for metering the fuel to the fuel nozzles in the combustion chambers, and a flow metering controller automatically actuating one or more of the flow metering devices to adjust fuel to the fuel nozzles based on gas turbine operating conditions. 2. The gas turbine of claim 1 wherein the gas turbine is an industrial gas turbine and is adapted to drive a utility power generator. 3. The gas turbine of claim 1 wherein the flow metering devices are fuel trim control valves. 4. The gas turbine of claim 1 wherein the flow metering devices are adjustable fuel orifices. 5. The gas turbine of claim 1 wherein the gas turbine operating conditions further comprises a profile of exhaust gas temperatures and wherein said controller correlates certain regions of the profile of the exhaust gas temperatures to one or more of the combustion chambers and the controller actuates the fuel trim valves to modify the profile of exhaust gas temperatures. 6. The gas turbine of claim 1 wherein the gas turbine operating conditions further comprises dynamic pressure oscillations in the combustion chambers. 7. The gas turbine of claim 6 wherein the controller actuates the flow metering devices to reduce variations in the dynamic pressure oscillations in the combustion chambers. 8. The gas turbine combustion system of claim 1 wherein the gas turbine operating conditions further comprises a profile of emission levels and wherein said controller correlates certain regions of the profile of the emission levels to one or more of the combustion chambers and the controller actuates the flow metering devices to modify the profile of emission levels. 9. The gas turbine combustion system of claim 1 wherein each of said multiple fuel nozzles includes a supply line coupling said nozzles to said flow metering devices. 10. The gas turbine combustion system comprising: a plurality of combustion chambers; a plurality of fuel nozzles for each of Said combustion chambers; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion clambers; the manifolds having a flow metering devices for the fuel nozzles, wherein the flow metering devices are mounted on the manifolds for metering the fuel to the fuel nozzles in the combustion chambers, and a flow metering controller automatically actuating one or more of the flow metering devices to adjust fuel to the fuel nozzles based on gas turbine operating conditions, wherein the manifolds each comprise a nested arrangement of fuel supply lines connecting the manifold to one of the fuel nozzles, and wherein the flow metering devices are each mounted on a respective fuel supply line. 11. A gas turbine combustion system comprising: a plurality of combustion chambers; plurality of fuel nozzles for each of said combustion chambers; a plurality of manifolds for supplying fuel to at least one of said fuel nozzles in each of the combustion chambers, wherein the manifold have differing fuel flow capacities and each of the manifolds has mounted thereon flow metering devices for said fuel nozzles; a plurality of sensors for measuring a condition of exhaust gas from the combustion chambers, and a controller automatically actuating one of the flow metering devices, separately from another one of the flow metering devices, to adjust fuel flow to the fuel nozzles based on exhaust gas data collected from the sensors. 12. The gas turbine combustion system of claim 11 wherein the flow metering devices are fuel trim control valves. 13. The gas turbine combustion system of claim 11 wherein the flow metering devices are adjustable fuel orifices. 14. The gas turbine of claim 11 wherein the sensors comprise thermocouples arranged in an array to sense exhaust temperatures at different regions of the exhaust gas, and said controller correlates the sensed exhaust temperatures to individual chambers of the combustion chambers. 15. The gas turbine of claim 11 wherein said gas turbine further comprises an exhaust outlet whereby said thermocouples are mounted adjacent said exhaust outlet. 16. The gas turbine combustion system of claim 11 wherein the sensors comprise emission sensors arranged in an array to sense emission levels at different regions of the exhaust gas, and said controller correlates the sensed emission levels to individual chambers of the combustion chambers. 17. The gas turbine combustion system of claim 11 wherein said flow metering devices are mounted on fuel supply lines of the manifolds. 18. A gas turbine combustion system comprising: a plurality of combustion chambers; a plurality of fuel nozzles for each of said combustion chambers, and; a plurality of manifolds for supplying fuel to at least one of said fuel nozzles in each of the combustion chambers, wherein said manifolds have differing fuel flow capacities and each of the manifolds has mounted thereon flow metering devices for metering flow to said fuel nozzles. 19. The gas turbine combustion system of claim 18 wherein the flow metering devices are orifice plates. 20. The gas turbine combustion system of claim 18 wherein the flow metering devices are fuel trim valves.