Gas turbine combustor liner cap assembly

A combustor liner cap assembly for use in a multiple fuel nozzle combustor of a gas turbine comprising:

• a substantially cylindrical, longitudinally extending sleeve having a forward end and an aft end;
• a tube plate fixed to the forward end of the sleeve, said tube plate having a forward face, a plurality of fuel nozzle openings, a plurality of first countersunk surfaces in the forward face, each first countersunk surface surrounding a corresponding one of the plurality of fuel nozzle openings, and a plurality of second countersunk surfaces, each second countersunk surface formed within a corresponding one of the plurality of first countersunk surfaces and surrounding a corresponding one of the plurality of fuel nozzle openings;
• a plurality of open ended premix tubes extending aft from the tube plate, each premix tube having a forward end having a forward edge, the forward end received in a corresponding one of the fuel nozzle openings and disposed with the forward edge flush with the first countersunk surface in the forward face of the tube plate, each premix tube brazed to the tube plate along an interface of the premix tube and the tube plate between an aft surface of the tube plate and the second countersunk surface.

A combustor liner cap assembly for use in a multiple fuel nozzle combustor of a gas turbine comprising:

• a tube plate having a plurality of fuel nozzle openings, the nozzle openings being threaded;
• and
• a plurality of open ended premix tubes associated with said plurality of fuel nozzle openings and extending from the tube plate, each premix tube being threaded on a forward end, the forward end having a forward edge, the forward end received in a corresponding one of the fuel nozzle openings and secured to the tube plate by a threaded connection away from the forward edge of the forward end of the premix tube.