Gas turbine combustor liner cap assembly
A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.
1. 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;
a plurality of open ended premix tubes associated with said plurality of fuel nozzle openings, each premix tube having a forward end having a forward edge, the forward end of each premix tube secured to the tube plate away from the forward edge of the forward end of the premix tube; and
a plurality of nozzle guides, each one of the plurality of nozzle guides being associated with a respective one of the plurality of open ended premix tubes and being fixed thereto with a retaining member the plurality of nozzle guides being in floating relationship to the tube plate.
2. The combustor liner cap assembly as recited in claim 1 wherein each premix tube is metallurgically bonded to the tube plate aft of the forward edge of the forward end of the premix tube.
3. The combustor liner cap assembly as recited in claim 2 wherein each premix tube is welded to the tube plate.
4. The combustor liner cap assembly as recited in claim 2 wherein each premix tube is brazed to the tube plate.
5. The combustor liner cap assembly as recited in claim 1 wherein each premix tube is threaded into the tube plate.
6. The combustor liner cap assembly as recited in claim 1 further comprising:
a substantially cylindrical, longitudinally extending sleeve having a forward end and an aft end, the tube plate fixed to the forward end of the sleeve; and
an aft plate fixed to the aft end of the sleeve and having a plurality of fuel nozzle openings, each fuel nozzle opening receiving an aft end of a corresponding one of the plurality of premix tubes in a sliding relationship.
7. 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 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 and a radial flange extending about the forward end of the premix tube, the forward end received in a corresponding one of the fuel nozzle openings and extending beyond a forward face of the tube plate, each premix tube fixed to the tube plate aft of the forward edge of the forward end of the premix tube; and
a plurality of open ended nozzle guides each having a radial flange, each one of the plurality of open ended nozzle guides being associated with a respective one of the plurality of premix tubes; and
a plurality of retaining members, each of the plurality of retaining members being associated with a respective one of each premix tube and nozzle guide assembly, each retaining member having a longitudinally extending leg mounted to the radial flange on the forward end of the premix tube and a tip flange extending radially over the radial flange of the nozzle guide.
8. The combustor liner cap assembly as recited in claim 7 wherein the radial flange of each premix tube has a face surface flush with a face surface of the premix tube and an under surface.
9. The combustor liner cap assembly as recited in claim 8 wherein the forward end of each premix tube extends beyond the forward face of the tube plate by a distance of at least about 12.7 millimeters (about 0.5 inch) as measured from the under surface of the radial flange of the premix tube to the forward face of the tube plate.
10. The combustor liner cap assembly as recited in claim 9 wherein the forward end of each premix tube extends beyond the forward face of the tube plate by a distance ranging from about 12.7 millimeters (about 0.5 inch) to about 25.4 millimeters (about 1.0 inch) as measured from the under surface of the radial flange of the premix tube to the forward face of the tube plate.
11. The combustor liner cap assembly as recited in claim 10 wherein each premix tube is welded to the tube plate.
12. The combustor liner cap assembly as recited in claim 8 wherein the first end of each nozzle guide is assembled in floating relationship in abutment with a corresponding one of the plurality of premix tubes.
13. 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.
14. The combustor liner cap assembly as recited in claim 13 wherein each of the plurality of second countersunk surfaces is formed as a chamfer relative to a corresponding one of the plurality of the first countersunk surfaces.
15. The combustor liner cap assembly as recited in claim 13 wherein each premix tube includes a radially outwardly directed circumferentially extending lip located aft of the forward end of the premix tube, the lip having a face surface abutting the aft surface of the tube plate.
16. The combustor liner cap assembly as recited in claim 13 further comprising a plurality of open-ended nozzle guides, each nozzle guide having a first end having a radial base flange, the first end of each nozzle guide assembled in floating relationship in abutment with a corresponding one of the plurality of first countersunk surfaces.
17. The combustor liner cap assembly as recited in claim 16 further comprising a plurality of retaining plate sectors secured to the tube plate, each retaining plate sector disposed between a corresponding pair of nozzle guides and overlaps a portion of the radial base flange of each of the corresponding pair of nozzle guides.
18. 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.
19. The combustor liner cap assembly as recited in claim 18 further comprising a plurality of open-ended nozzle guides, each nozzle guide disposed in abutment with a corresponding one of the plurality of nozzle openings.