| 主权项 |
1. A system for providing fuel to a combustor of a gas turbine, the system comprising:
a. an annular fuel distribution manifold, the fuel distribution manifold at least partially defining a fuel plenum, the fuel distribution manifold having a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange; b. a late lean injector (LLI) injection assembly that extends downstream from the fuel distribution manifold, the LLI injection assembly having a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone, a late lean (LLI) injector that extends substantially radially through the unibody liner and that provides for fluid communication through the unibody liner into the secondary combustion zone; and c. a fluid conduit that extends between the LLI injector and the fuel distribution manifold, the fluid conduit being in fluid communication with the fuel plenum; d. wherein the LLI assembly further includes a flow sleeve that circumferentially surrounds at least a portion of the unibody liner, the flow sleeve being radially separated from the unibody liner to at least partially define an annular cooling flow passage therebetween, wherein the LLI injector extend through the flow sleeve. |
