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A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with

A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with the fuel nozzle for observing combustor flame characteristics. The optical sensor array includes a plurality of sapphire rods positioned to be close enough to the combustor flame to oxidize soot deposits thereon.

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What is claimed is: 1. A fuel injector for a gas turbine combustor, comprising: a) a fuel nozzle for injecting fuel into a gas turbine combustor; and b) optical sensing means operatively associated with the fuel nozzle for observing characteristics of a combustor flame, the optical sensing means in

What is claimed is: 1. A fuel injector for a gas turbine combustor, comprising: a) a fuel nozzle for injecting fuel into a gas turbine combustor; and b) optical sensing means operatively associated with the fuel nozzle for observing characteristics of a combustor flame, the optical sensing means including an optical rod formed from a material capable of withstanding temperatures associated with flame exposure, the optical rod extending from a surface of the fuel nozzle and having an optical surface positioned in such a manner so as to gain flame exposure sufficient to oxidize soot deposits thereon. 2. A fuel injector for a gas turbine combustor as recited in claim 1, wherein the optical rod is an optically transparent sapphire rod. 3. A fuel injector for a gas turbine combustor as recited in claim 1, wherein the optical rod is located at least partially within a viewing port formed in the fuel nozzle and extends to a location that enables the optical surface to be in close proximity to the combustor flame. 4. A fuel injector for a gas turbine combustor as recited in claim 3, wherein the optical rod extends at an angle relative to a central axis of the nozzle. 5. A fuel injector for a gas turbine combustor as recited in claim 1, wherein the optical surface of the optical rod is coated with a catalyst that enhances oxidation of soot. 6. A fuel injector for a gas turbine combustor as recited in claim 1, wherein the optical surface of the optical rod is configured to act as a diffuser. 7. A fuel injector for a gas turbine combustor as recited in claim 1, wherein the optical surface of the optical rod is a frosted surface. 8. A fuel injector for a gas turbine combustor as recited in claim 7, wherein the optical surface of the optical rod is ground to form the frosted surface. 9. A fuel injector for a gas turbine combustor as recited in claim 1, wherein the optical rod has a polished optical end in communication with a fiber optic bundle. 10. A fuel injector for a gas turbine combustor, comprising: a) a fuel nozzle for injecting fuel into a gas turbine combustor; and b) optical sensing means operatively associated with the fuel nozzle for observing characteristics of a combustor flame, the optical sensing means including an optical rod formed from a material capable of withstanding temperatures associated with flame exposure, the optical rod having an optical surface positioned in such a manner so as to gain flame exposure sufficient to oxidize soot deposits thereon, wherein the optical rod is located at least partially within a viewing port formed in the fuel nozzle and extends from a surface of the fuel nozzle to a location that enables the optical surface to be in close proximity to the combustor flame. 11. A fuel injector for a gas turbine combustor as recited in claim 10, wherein the optical rod is an optically transparent sapphire rod. 12. A fuel injector for a gas turbine combustor as recited in claim 10, wherein the optical rod extends at an angle relative to a central axis of the nozzle. 13. A fuel injector for a gas turbine combustor as recited in claim 10, wherein the optical surface of the optical rod is coated with a catalyst that enhances oxidation of soot. 14. A fuel injector for a gas turbine combustor as recited in claim 10, wherein the optical surface of the optical rod is configured to act as a diffuser. 15. A fuel injector for a gas turbine combustor as recited in claim 10, wherein the optical surface of the optical rod is a frosted surface. 16. A fuel injector for a gas turbine combustor as recited in claim 10, wherein the optical rod has a polished optical end in communication with a fiber optic bundle.