Method and system for porous flame holder for hydrogen and syngas combustion
A fuel nozzle assembly for a combustor in a gas turbine including: a gaseous fuel passage and a fuel nozzle at a distal end of the passage; an air tube concentric with the fuel nozzle and defining an air passage between the air tube and the fuel nozzle, wherein the air tube includes a distal section extending axially beyond the fuel injection nozzle; a first fuel-air mixing zone inside the distal section of the air tube, wherein the first fuel-air mixing zone is downstream of the fuel injection nozzle; a flame holder including a porous structure with thermal barrier coating and micro swirlers and defining a downstream end of the first fuel-air mixing zone, wherein fuel and air from the first fuel-air mixing zone pass through the porous structure of the flame holder and into a combustion zone of the combustor.
1. An air fuel assembly for a combustor in a gas turbine, the assembly comprising:
a gaseous fuel injection nozzle assembly having a center axis and including a gaseous fuel passage extending along the center axis, and a fuel nozzle at a distal end of the gaseous fuel passage, wherein said gaseous fuel injection nozzle assembly continuously injects gaseous fuel into the gaseous fuel passage;
an air tube concentric with the fuel injection nozzle assembly and defining an air passage between the air tube and the fuel injection nozzle assembly, wherein the air tube includes a distal section extending axially beyond the fuel injection nozzle and includes a compressed air inlet adapted to receive compressed air from a compressor in the gas turbine;
a first fuel-air mixing zone in the distal section of the air tube and downstream of the fuel injection nozzle,
a flame holder comprising a porous structure connected to the distal section of the air tube and defining a downstream end of the first fuel-air mixing zone, wherein, prior to and upstream from combustion, fuel and air from the first fuel-air mixing zone pass through the porous structure of the flame holder and into a combustion zone of the combustor and continuous combustion of the fuel and air first occurs in the combustion zone.
2. An air fuel assembly as in claim 1 wherein the porous structure is seated in an outlet of the distal section of the air tube.
3. An air fuel assembly as in claim 1 wherein the porous structure spans an entirety of an outlet of the distal section of the air tube.
4. An air fuel assembly as in claim 1 wherein the porous structure is a honeycomb structure.
5. An air fuel assembly as in claim 1 wherein the porous structure includes air and fuel mixture flow passages, wherein the flow passages are skewed with respect to the center axis.
6. An air fuel assembly as in claim 5 wherein the flow passages impart swirl to the air fuel mixture passing through the flame stabilizer.
7. An air fuel assembly as in claim 1 wherein the porous structure includes a thermal barrier coating on surfaces facing the combustion zone.
8. An air fuel assembly as in claim 1 wherein the porous structure comprises a second fuel-air mixing zone wherein fuel and air mix while passing through the porous structure.