| 摘要 |
A combustor (10) for a gas turbine including a casing (12), a flow sleeve (14) at least partially disposed within the casing (12), a combustion liner (16) at least partially disposed within the flow sleeve (14), a liner stop feature (48) extending from the combustion liner (16), and a liner guide stop (22) including a first end (24) separated from a second end (26), the second end (26) configured to be at least partially engaged with the liner stop feature (48), wherein the liner guide stop (22) extends through the casing (12) and the flow sleeve (14). |
