Gas turbine combustor and operating method for gas turbine combustor
View Patent ↗Disclosed is a gas turbine combustor equipped with a burner constructed to fire a plurality of combustors at the same time at a fuel/air ratio suitable for gas turbine ignition. A plurality of supports mounted for fixing an air injection hole plate to the combustor are provided at substantially the same phase position as that of cross fire tubes, and combustion air allocations are adjusted. Thus, flame propagation during gas turbine ignition is accelerated and all combustor cans are fired. In addition, porous plates are disposed downstream of the supports and the combustion air allocations are readjusted. Furthermore, air injection holes proximate to the cross fire tubes are particularly reduced in diameter to further adjust the combustion air allocations.
1. A gas turbine combustor comprising:
a combustion chamber that burns a fuel and air to generate combustion gases;
a fuel header with a plurality of fueling nozzles disposed thereupon to inject the fuel;
an air injection hole plate with a plurality of air injection holes formed therein to deliver to the combustion chamber the air along with the fuel injected from the fueling nozzles;
cross fire tubes that each transport the combustion gases to an adjacent combustor and ignite the adjacent combustor during gas turbine ignition; and
supports for fixing the air injection hole plate to the fuel header,
wherein the supports are provided so as to be at the same phase position as that of the cross fire tubes,
wherein the supports have a width greater than an inside diameter of the cross fire tubes adapted for obstructing air flowing into the air injection hole plate such that a fuel/air ratio is increased downstream the supports and at the same phase position of the cross fire tubes.
2. The gas turbine combustor according to claim 1 , further comprising:
a firing burner that supplies and burns the fuel during gas turbine ignition; and
a non-firing burner inactivated during gas turbine ignition;
wherein:
part of the non-firing burner is formed by a row of the air injection holes annularly arranged around an outer circumference of the firing burner; and
at the same phase position as that in which the cross fire tubes are disposed, the non-firing burner has a region particularly large in hole pitch between adjacent air injection holes arranged in the row of the air injection holes that forms part of the non-firing burner.
3. The gas turbine combustor according to claim 1 , further comprising porous plates placed downstream of the supports so as to extend in a direction parallel to a flow of air moving from an outer circumferential side of the air injection hole plate, towards an inner circumferential side thereof.
4. The gas turbine combustor according to claim 1 , wherein a plurality of air injection holes arranged at the same phase position as that of the cross fire tubes have a diameter smaller than that of the other air injection holes.
5. The gas turbine combustor according to claim 1 , wherein the supports are porous plates.
6. A method for operating a gas turbine combustor comprising a combustion chamber that burns a fuel and air to generate combustion gases, a fuel header with a plurality of fueling nozzles disposed thereupon to inject the fuel, an air injection hole plate with a plurality of air injection holes formed therein to deliver to the combustion chamber the air along with the fuel injected from the fueling nozzles, cross fire tubes that each transport the combustion gases to an adjacent combustor and ignite the adjacent combustor during gas turbine ignition, and supports for fixing the air injection hole plate to the fuel header, the supports being provided so as to be at a same phase position as that of the cross fire tubes, the supports having a width greater than an inside diameter of the cross fire tubes, the method comprising:
supplying the combustion gases generated in the combustion chamber to an adjacent combustor via the cross fire tubes provided at the same phase position as that of the supports; and
obstructing air flowing through the supports into the air injection hole plate such that a fuel/air ratio is increased downstream the supports and at the same phase position of the cross fire tubes.