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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 located within the fuel noz

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 located within the fuel nozzle for observing combustion conditions within the combustor.

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What is claimed is: 1. A fuel injector for a gas turbine combustor, comprising: a) a feed arm including means for mounting the injector within the combustor; b) a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion, wherein the fuel nozzle includes a leading

What is claimed is: 1. A fuel injector for a gas turbine combustor, comprising: a) a feed arm including means for mounting the injector within the combustor; b) a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion, wherein the fuel nozzle includes a leading edge having a plurality of spaced apart viewing ports formed therein; and c) optical sensing means embedded in the viewing ports of the fuel nozzle for observing combustion conditions within the combustor. 2. A fuel injector as recited in claim 1, wherein the fuel nozzle has a central axis and includes an outer swirler, wherein the outer swirler includes the leading edge of the fuel nozzle, and wherein the plurality of spaced apart viewing ports are located around the leading edge of the outer swirler. 3. A fuel injector as recited in claim 2, wherein the leading edge of the outer swirler includes three viewing ports spaced equidistant from one another. 4. A fuel injector as recited in claim 2, wherein the optical sensing means includes a plurality of optical fiber bundles, and wherein an optical fiber bundle is accommodated within each viewing port. 5. A fuel injector as recited in claim 4, wherein each optical fiber bundle includes a plurality of optical fibers that extend generally parallel to the central axis of the nozzle. 6. A fuel injector as recited in claim 4, wherein the optical fibers are treated to withstand operating temperatures within the combustor. 7. A fuel injector as recited in claim 6, wherein the optical fibers are provided with a metal coating. 8. A fuel injector as recited in claim 4, wherein each optical fiber bundle is disposed within a temperature resistant guide tube. 9. A fuel injector as recited in claim 8, wherein each guide tube is formed from stainless steel. 10. A fuel injector as recited in claim 8, wherein each guide tube is cemented within a corresponding viewing port in a manner that accommodates thermal expansion and contraction. 11. A fuel injector as recited in claim 4, wherein each optical fiber bundle has a field of view of between about 14�� and 30�� relative to axis of fiber. 12. A fuel injector as recited in claim 8, wherein a lens is provided at the distal end of the guide tube for modifying the field of view of the optical fiber bundle disposed therein. 13. A fuel injector as recited in claim 8, wherein a window is provided at the distal end of the guide tube to seal the interior of the guide tube and protect the optical fiber bundle disposed therein. 14. A fuel injector as recited in claim 8, wherein distal end portions of the optical fibers of an optical fiber bundle are splayed radially outwardly to enhance the field of view of the optical fiber bundle. 15. A fuel injector as recited in claim 4, wherein the optical sensing means further includes at least one optical fiber mounted along the axis of the nozzle. 16. A fuel injector as recited in claim 1, wherein the optical sensing means communicates with means for processing optical signals. 17. A fuel injector as recited in claim 16, wherein the means for processing optical signals includes means for detecting combustion instabilities based upon conditions observed by the optical sensing means within the fuel nozzle. 18. A fuel injector as recited in claim 17, wherein the means for detecting combustion instabilities communicates with means for modulating the rate of fuel flow to the fuel injector to reduce detected combustion instabilities. 19. A fuel injector as recited in claim 4, wherein the optical fibers are UV enhanced fibers. 20. A fuel injector as recited in claim 4, wherein the optical fibers are IR enhanced fibers. 21. A fuel injector for a gas turbine combustor, comprising: a) a feed arm including means for attaching the fuel injector to the combustor; and b) a fuel nozzle having an upstream end associated with the feed arm and a downstream end for issuing fuel into the combustor, the fuel nozzle including a leading edge having a plurality of spaced apart viewing ports containing an optical sensor array for viewing conditions within the combustor downstream from said nozzle. 22. A fuel injector as recited in claim 21, wherein the fuel nozzle has a central axis and includes an outer swirler, wherein the outer swirler includes the leading edge of the fuel nozzle, and wherein the plurality of spaced apart viewing ports are located around the leading edge of the outer swirler. 23. A fuel injector as recited in claim 22, wherein the optical sensor array includes a plurality of optical fiber bundles, and wherein an optical fiber bundle is accommodated within each viewing port. 24. A fuel injector as recited in claim 23, wherein the optical fibers in each optical fiber bundle are treated to withstand operating temperatures within the combustor. 25. A fuel injector as recited in claim 23, wherein each optical fiber bundle is disposed within a temperature resistant guide tube. 26. A fuel injector as recited in claim 23, wherein the optical sensor array further includes at least one optical fiber are mounted along the axis of the nozzle. 27. A fuel injector as recited in claim 23, wherein the optical fibers are UV enhanced fibers. 28. A fuel injector as recited in claim 23, wherein the optical fibers are IR enhanced fibers. 29. A system for stabilizing combustion in a gas turbine engine, the system comprising: a) an optical sensing array embedded within a leadirnz edge of a fuel injector for observing conditions within a combustion chamber of a gas turbine engine; b) means for detecting combustion instabilities based upon conditions observed by the optical sensing array; and c) means for modulating a fuel flow rate to reduce detected combustion instabilities. 30. A system as recited in claim 29, wherein the means for detecting combustion instabilities includes means for detecting changes in flame intensity at levels indicative of flame instability. 31. A system as recited in claim 29, wherein the means for detecting combustion instabilities includes means for detecting spectral radiation indicative of fuel contaminants effecting fuel heat values. 32. A system as recited in claim 29, wherein the means for detecting combustion instabilities includes means for detecting spectral radiation indicative of chemical emissions effecting flame temperature, NOx, CO and fuel/air ratio. 33. A system as recited in claim 29, wherein the means for modulating fuel flow to reduce detected combustion instabilities includes a fuel control system operatively associated with a fuel pump.