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A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle. A mounting flange assembly concentrically surrounds the cylindrical outer sleeve

A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle. A mounting flange assembly concentrically surrounds the cylindrical outer sleeve. A plurality of struts on an outer surface of the cylindrical outer sleeve support the mounting flange assembly. A plurality of flanges are on the outer surface of the cylindrical outer sleeve; and a plurality of support rods having first ends are adjustably supported by respective flanges. A combustor for a gas turbine includes a combustion liner cap assembly, a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings, and a center fuel nozzle supported in the center fuel nozzle opening. Second ends of the plurality of support rods adjustably contact the center fuel nozzle.

대표청구항 ▼

1. A combustion liner cap assembly, comprising: a cylindrical outer sleeve, the cylindrical outer sleeve comprising a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around a center fuel nozzle located within the center fuel nozzle opening;a mounting flange assembly c

1. A combustion liner cap assembly, comprising: a cylindrical outer sleeve, the cylindrical outer sleeve comprising a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around a center fuel nozzle located within the center fuel nozzle opening;a mounting flange assembly concentrically surrounding the cylindrical outer sleeve;a plurality of struts on an outer surface of the cylindrical outer sleeve that support the mounting flange assembly;a plurality of flanges on the outer surface of the cylindrical outer sleeve; anda plurality of support rods having first ends adjustably supported by respective flanges and second ends contacting the center fuel nozzle. 2. A combustion liner cap assembly according to claim 1, wherein the flanges are threaded and the first ends of the support rods are threaded into the flanges. 3. A combustion liner cap assembly according to claim 1, further comprising a sleeve provided in the center fuel nozzle opening, the sleeve comprising a plurality of apertures in an outer surface, each configured to receive a respective second end of one of the plurality of support rods. 4. A combustion liner cap assembly according to claim 3, further comprising a plurality of support plates configured to support the sleeve on the cylindrical outer sleeve. 5. A combustion liner cap assembly according to claim 3, wherein the second ends of the support rods comprise at least one of bare metal, a wire mesh or wear coating. 6. A combustor for a gas turbine, comprising: a combustion liner cap assembly, the combustion liner cap assembly comprising a cylindrical outer sleeve, the cylindrical outer sleeve comprising a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle,a mounting flange assembly concentrically surrounding the cylindrical outer sleeve,a plurality of struts on an outer surface of the cylindrical outer sleeve that support the mounting flange assembly,a plurality of flanges on the outer surface of the cylindrical outer sleeve, anda plurality of support rods having first ends adjustably supported by respective flanges;a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings; anda center fuel nozzle supported in the center fuel nozzle opening,wherein second ends of the plurality of support rods adjustably contact the center fuel nozzle. 7. A combustor according to claim 6, wherein the flanges are threaded and the first ends of the support rods are threaded into the flanges. 8. A combustor according to claim 6, further comprising a sleeve provided in the center fuel nozzle opening, the sleeve comprising a plurality of apertures in an outer surface, each configured to receive a respective second end of one of the plurality of support rods. 9. A combustor according to claim 8, further comprising a plurality of support plates configured to support the sleeve on the cylindrical outer sleeve. 10. A combustor according to claim 8, wherein the second ends of the support rods comprise at least one of bare metal, a wire mesh or a wear coating. 11. A combustor according to claim 6, wherein the center fuel nozzle comprises at least one swirling vane, and the second ends of the plurality of support rods adjustably contact the center fuel nozzle adjacent the at least one swirling vane. 12. A method of adjusting frequencies of a plurality of fuel nozzles in a combustor of a gas turbine comprising a a combustion liner cap assembly, the combustion liner cap assembly comprising a cylindrical outer sleeve, the cylindrical outer sleeve comprising a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle, a mounting flange assembly concentrically surrounding the cylindrical outer sleeve, a plurality of struts on an outer surface of the cylindrical outer sleeve that support the mounting flange assembly, a plurality of flanges on the outer surface of the cylindrical outer sleeve, and a plurality of support rods having first ends adjustably supported by respective flanges, the combustor further comprising a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings, and a center fuel nozzle supported in the center fuel nozzle opening, the method comprising: adjusting contact between second ends of the support rods and the center fuel nozzle. 13. A method according to claim 12, wherein the flanges are threaded and the first ends of the support rods are threaded into the flanges. 14. A method according to claim 12, wherein the combustor further comprises a sleeve provided in the center fuel nozzle opening, the sleeve comprising a plurality of apertures in an outer surface configured to receive respective second ends of the support rods. 15. A method according to claim 12, wherein the combustor further comprises a plurality of support plates configured to support the sleeve on the cylindrical outer sleeve. 16. A method according to claim 12, wherein the second ends of the support rods comprise bare metal, a wire mesh or a wear coating. 17. A method according to claim 12, wherein the center fuel nozzle comprises at least one swirling vane, and the second ends of the plurality of support rods adjustably contact the center fuel nozzle adjacent the at least one swirling vane. 18. A method according to claim 12, wherein adjusting the contact between the second ends of the support rods and the center fuel nozzle comprises adjusting the contact so that the frequency of the fuel nozzles is above all combustion and rotor tones, and the amplitude response is sufficiently dampened.