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A combustor for a gas turbine including a casing, a flow sleeve at least partially disposed within the casing, a combustion liner at least partially disposed within the flow sleeve, a liner stop feature extending from the combustion liner, and a liner guide stop including a first end separated from

A combustor for a gas turbine including a casing, a flow sleeve at least partially disposed within the casing, a combustion liner at least partially disposed within the flow sleeve, a liner stop feature extending from the combustion liner, and a liner guide stop including a first end separated from a second end, the second end configured to be at least partially engaged with the liner stop feature, wherein the liner guide stop extends through the casing and the flow sleeve.

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1. A method for assembling a combustor of a gas turbine, the combustor including a casing, a flow sleeve, and a combustion liner, the method comprising: a. inserting the combustion liner into the combustor casing such that the combustion liner is concentrically arranged within the flow sleeve, the c

1. A method for assembling a combustor of a gas turbine, the combustor including a casing, a flow sleeve, and a combustion liner, the method comprising: a. inserting the combustion liner into the combustor casing such that the combustion liner is concentrically arranged within the flow sleeve, the combustion liner including at least one liner stop feature extending therefrom;b. aligning the liner stop feature with an alignment sleeve as the combustion liner is inserted into the combustor casing, the alignment sleeve coupled to the flow sleeve and extending radially inward from an inner surface of the flow sleeve;c. inserting a liner guide stop through the casing and the flow sleeve, the liner guide stop extending between a first end and a second end; andd. engaging the second end of the liner guide stop with the liner stop feature;e. wherein engaging the second of the liner guide stop with the liner stop feature comprises one of: i) inserting the second end of the liner guide stop into a slot formed in the liner stop feature, wherein the slot formed in the liner stop feature opens through a downstream end of the liner stop feature;ii) inserting the liner stop feature into a slot formed in the second end of the liner guide stop, wherein the slot formed in the second end of the liner guide stop opens through an upstream end of the second end of the liner guide stop; oriii) screwing the second end of the liner guide stop into threaded engagement with the liner stop feature. 2. The method of claim 1, further comprising coupling the first end of the liner guide stop to an outer surface of the casing. 3. The method of claim 2, wherein coupling the liner guide stop to the outer surface of the casing comprises at least one of bolting, screwing or welding the liner guide stop to the outer surface of the casing. 4. The method of claim 1, further comprising inserting a collar through at least one of the casing or the flow sleeve, wherein the collar at least partially surrounds the liner guide stop. 5. A combustor for a gas turbine comprising: a. a casing;b. a flow sleeve at least partially disposed within the casing, the flow sleeve having an inner surface;c. an alignment sleeve coupled to the flow sleeve, the alignment sleeve extending radially inward from the inner surface of the flow sleeve;d. a combustion liner at least partially disposed within the flow sleeve;e. a liner stop feature extending from the combustion liner, the liner stop feature having an upstream end and a downstream end, the downstream end positioned adjacent the alignment sleeve; andf. a liner guide stop including a first end separated from a second end, the second end configured to be at least partially engaged with the liner stop feature, wherein the liner guide stop extends through the casing and the flow sleeve;g. wherein the at least partial engagement of the liner stop feature with the second end of the liner guide stop comprises one of: i) the liner stop feature being disposed in a slot formed in the second end of the liner guide stop, wherein the slot formed in the second end of the liner guide stop opens through an upstream end of the second end of the liner guide stop;ii) the second end of the liner guide stop being disposed in a slot formed in the liner stop feature, wherein the slot formed in the liner stop feature opens through a downstream end of the liner stop feature; oriii) the second end of the liner guide stop being in threaded engagement with the liner stop feature. 6. The combustor of claim 5, wherein the alignment sleeve is at least partially arcuate, triangular or rectangular shaped. 7. A combustor for a gas turbine comprising: a. a casing;b. a flow sleeve at least partially disposed within the casing, the flow sleeve defining a passage extending radially through the flow sleeve;c. a collar inserted into the passage, the collar coupled to the flow sleeve such that the collar is movable within the passage;d. a combustion liner at least partially disposed within the flow sleeve;e. a liner stop feature extending from the combustion liner; andf. a liner guide stop including a first end separated from a second end, the second end configured to be at least partially engaged with the liner stop feature, wherein the liner guide stop extends through the casing and the flow sleeve, and wherein the collar at least partially surrounds the liner guide stop;g. wherein the at least partial engagement of the liner stop feature with the second end of the liner guide stop comprises one of: i) the liner stop feature being disposed in a slot formed in the second end of the liner guide stop, wherein the slot formed in the second end of the liner guide stop opens through an upstream end of the second end of the liner guide stop;ii) the second end of the liner guide stop being disposed in a slot formed in the liner stop feature, wherein the slot formed in the liner stop feature opens through a downstream end of the liner stop feature; oriii) the second end of the liner guide stop being in threaded engagement with the liner stop feature. 8. The combustor of claim 7, wherein the liner guide stop is coupled to an outer surface of the casing. 9. The combustor of claim 7, wherein the first end of the liner guide stop is configured to screw into a passage at least partially defined by the casing. 10. The combustor of claim 7, wherein the liner guide stop includes a flange at the first end, the flange configured to be coupled with an outer surface of the casing. 11. The combustor of claim 7, wherein the second end of the liner guide stop defines at least one of an arcuate, a triangular or a rectangular shape.