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A system, one embodiment, includes an annular seal configured to seal a turbine fuel nozzle to a turbine combustor, wherein the annular seal includes a first annular seal portion having an inner annular surface, a first base portion, and a first peripheral portion opposite from the first base portio

A system, one embodiment, includes an annular seal configured to seal a turbine fuel nozzle to a turbine combustor, wherein the annular seal includes a first annular seal portion having an inner annular surface, a first base portion, and a first peripheral portion opposite from the first base portion. The embodiment also includes the first annular seal portion configured to couple to a second annular seal portion having an outer annular surface, a second base portion, and a second peripheral portion opposite from the second base portion. Further, the embodiment includes the first and second peripheral portions sealable by a weld.

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1. A system, comprising: a turbine combustor;a fuel nozzle; andan annular seal, comprising:a first annular seal portion protruding from a base of the turbine combustor, wherein an inner circumference of the first annular seal portion has a first cylindrical surface that is perpendicular to the base;

1. A system, comprising: a turbine combustor;a fuel nozzle; andan annular seal, comprising:a first annular seal portion protruding from a base of the turbine combustor, wherein an inner circumference of the first annular seal portion has a first cylindrical surface that is perpendicular to the base;a second annular seal portion protruding from an exterior of the fuel nozzle, wherein an outer circumference of the second annular seal portion has a second cylindrical surface that extends a distance along the first cylindrical surface in a common direction away from the base to peripheral portions of the respective first and second annular seal portions; anda weld between the first and second annular seal portions, wherein the weld is located at the peripheral portions of the first and second annular seal portions, away from the base. 2. The system of claim 1, wherein the first annular seal portion comprises an L-shaped cross-section and the second annular seal portion comprises a U-shaped cross-section. 3. The system of claim 1, wherein the first annular seal portion comprises an L-shaped cross-section and the second annular seal portion comprises a rectangular cross-section. 4. The system of claim 1, wherein the first and second annular seal portions comprise opposite lips extending toward one another at the peripheral portions, and the weld secures the opposite lips to one another. 5. The system of claim 1, comprising a plurality of fuel nozzles, including the fuel nozzle, coupled to the base of the turbine combustor, wherein each of the fuel nozzles comprises a respective one of the first or second annular seal portions. 6. The system of claim 1, wherein the first and second annular seal portions are configured to enable multiple iterations of material removal to enable multiple weld severances and re-welds without removing material from the fuel nozzle and turbine combustor. 7. The system of claim 1, wherein the common direction is generally parallel to an axis of the fuel nozzle. 8. A system, comprising: an annular seal configured to seal a turbine fuel nozzle to a turbine combustor, wherein the annular seal comprises:a first annular seal portion having an inner annular surface, a first base portion, and a first peripheral portion opposite from the first base portion;wherein the first annular seal portion is configured to couple to a second annular seal portion having an outer annular surface, a second base portion, and a second peripheral portion opposite from the second base portion;wherein the first base portion is configured to be coupled to the turbine combustor and the second base portion is configured to be coupled to the fuel nozzle;wherein the inner and outer annular surfaces extend a distance along one another in a common direction to the first and second peripheral portions; andwherein the first and second peripheral portions are sealable by a weld. 9. The system of claim 8, wherein the first and second annular seal portions are configured to enable multiple iterations of material removal to enable multiple weld severances and re-welds without removing material from the fuel nozzle and turbine combustor. 10. The system of claim 8, wherein the first annular seal portion comprises an L-shaped cross-section. 11. The system of claim 8, wherein the first annular seal portion is coupled to the turbine combustor and the inner annular surface is generally perpendicular to a surface of the turbine combustor and is generally parallel to the outer annular surface. 12. The system of claim 8, wherein the first and second annular seal portions are axially separable from one another while coupled to the fuel nozzle and turbine combustor within the weld. 13. The system of claim 8, wherein the first and second annular seal portions do not overlap in an axial direction relative to one another. 14. The system of claim 8, wherein the first base portion is coupled to the turbine combustor, the second base portion is coupled to the fuel nozzle, and the first and second peripheral portions are offset from a surface of the turbine combustor and an exterior surface of the fuel nozzle. 15. The system of claim 8, wherein the first annular seal portion comprises an L-shaped cross-section and the second annular seal portion comprises a U-shaped cross-section. 16. The system of claim 8, wherein the common direction is generally parallel to an axis of the turbine fuel nozzle. 17. A system, comprising: a first annular seal portion comprising an inner circumference, wherein the first annular seal portion protrudes in a generally perpendicular direction away from a base of a turbine combustor;a second annular seal portion comprising an outer circumference generally parallel to and extending a distance along the inner circumference in a common direction away from the base, wherein the second annular seal portion protrudes away from an exterior of a fuel nozzle; anda weld between the first and second annular seal portions configured to seal a the fuel nozzle to the turbine combustor, wherein the weld is located at peripheral portions of the first and second annular seal portions away from the base and the exterior. 18. The system of claim 17, wherein the first annular seal portion comprises an L-shaped cross-section and the second annular seal portion comprises a rectangular shaped cross-section. 19. The system of claim 17, wherein the first annular seal portion comprises an L-shaped cross-section and the second annular seal portion comprises a U-shaped cross-section or another L-shaped cross-section. 20. The system of claim 17, wherein the first and second annular seal portions are configured to enable multiple iterations of material removal to enable multiple weld severances and re-welds without removing material from the fuel nozzle and turbine combustor. 21. The system of claim 17, wherein the first and second annular seal portions do not overlap in an axial direction relative to one another. 22. The system of claim 17, wherein a surface of the second annular circumference is generally parallel to an exterior surface of the turbine fuel nozzle and is generally parallel to a surface of the first annular circumference. 23. The system of claim 17, wherein the common direction is generally parallel to an axis of the fuel nozzle.