| 摘要 |
A modular combustion liner cap assembly (42) for use in a multi-nozzle combustor of a gas turbine includes a substantially cylindrical first sleeve (46) having a rearward end and a forward end; a rear plate (48) fixed to the rearward end of the sleeve (46), the rear plate (48) provided with a first plurality of openings (52) for receiving a corresponding number of fuel nozzles (32); a forward plate subassembly (68) fixed to the forward end of the sleeve (46), the forward plate provided with a second plurality of openings (80) in substantial alignment with the first plurality of openings in the rear plate (48); a plurality of open ended premix tubes having forward and rearward ends, each tube (96) extending axially within the sleeve (46) between the rear plate (48) and the forward plate assembly (68), each premix tube (96) supported within a corresponding one of the first plurality of openings (52) at its rearward end and a corresponding one of the second plurality of openings (80) at its forward end.
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