Pilotless catalytic combustor
View Patent ↗A pilotless catalytic combustor ( 10 ) including a basket ( 12 ) having a central axis ( 14 ) and a central core region ( 16 ) disposed along a portion of the central axis. Catalytic combustion modules ( 18 ) are circumferentially disposed about the central axis radially outward of the central core region for receiving a fuel flow ( 20 ) and a first portion of an oxidizer flow ( 22 ), and discharge a partially oxidized fuel/oxidizer mixture ( 24 ) at respective exit ends ( 26 ). A base plate ( 30 ) is positioned in the central core region upstream of the exit ends of the catalytic combustion modules, the baseplate defining a recirculation zone ( 32 ) near the respective exit ends for stabilizing oxidation in the burnout zone. A method of staged fueling for a pilotless catalytic combustor includes providing fuel to at least one of the modules during start up and progressively providing fuel to other modules as a load on the turbine engine is increased.
1. A catalytic combustor comprising:
a plurality of catalytic combustion modules circumferentially disposed about a central axis radially outward of a central core region, for receiving a fuel flow and an oxidizer flow and for discharging a partially oxidized fuel/oxidizer mixture at respective exit ends, the central core region containing no burner apparatus;
a burnout zone disposed downstream of the exit ends for receiving the partially oxidized fuel/oxidizer mixture and for completing oxidation of the partially oxidized fuel/oxidizer mixture; and
a base plate positioned in the central core region upstream of the respective exit ends of the plurality of catalytic combustion modules, the baseplate and the respective exit ends defining a recirculation zone for the partially oxidized fuel/oxidizer mixture for stabilizing oxidation in the burnout zone.
2. The combustor of claim 1 , wherein the recirculation zone is disposed along the central axis.
3. The combustor of claim 1 , further comprising a fuel flow controller for independently controlling the fuel flow to at least one of the catalytic combustion modules independently of other catalytic combustion modules, the fuel flow controller responsive to a turbine load condition.
4. The combustor of claim 1 , the base plate further comprising an aperture for allowing passage of a portion of the oxidizer flow into the burnout zone bypassing the plurality of catalytic modules.
5. The combustor of claim 1 , further comprising an igniter positioned proximate the baseplate.
6. The combustor of claim 1 , wherein the base plate is positioned about one to two inches (2.54 to 5.08 centimeters) upstream of the respective exit ends.
7. A gas turbine engine comprising:
a compressor;
a turbine; and
a catalytic combustor comprising a plurality of catalytic combustion modules circumferentially disposed about a central axis radially outward of a central core region, for receiving a fuel flow and an oxidizer flow and for discharging a partially oxidized fuel/oxidizer mixture at respective exit ends, the central core region containing no burner apparatus; a burnout zone disposed downstream of the exit ends for receiving the partially oxidized fuel/oxidizer mixture and for completing oxidation of the partially oxidized fuel/oxidizer mixture; and a base plate positioned in the central core region upstream of the respective exit ends of the plurality of catalytic combustion modules, the baseplate and the respective exit ends defining a recirculation zone for the partially oxidized fuel/oxidizer mixture for stabilizing oxidation in the burnout zone.
8. The gas turbine engine of claim 7 , wherein the recirculation zone is disposed along the central axis.
9. The gas turbine engine of claim 7 , further comprising a fuel flow controller for independently controlling the fuel flow to at least one of the catalytic combustion modules independently of other catalytic combustion modules, the fuel flow controller responsive to a turbine load condition.
10. The gas turbine engine of claim 7 , the base plate further comprising an aperture for allowing passage of a portion of the oxidizer flow into the burnout zone bypassing the plurality of catalytic modules.
11. The gas turbine engine of claim 7 , further comprising an igniter positioned proximate the baseplate.
12. The gas turbine engine of claim 7 , wherein the base plate is positioned about one to two inches (2.54 to 5.08 centimeters) upstream of the respective exit ends.