Fuel nozzle cap

Abstract

Certain embodiments include a first individual sector having a first outer perimeter configured to fit together with outer perimeters of a plurality of individual sectors to form a combustor cap assembly of a turbine combustor, wherein the first individual sector comprises a first inner perimeter configured to fit about a nozzle outer perimeter of a first fuel nozzle, and the first individual sector is configured to fixedly attach to the first fuel nozzle.

1 . A system, comprising:
 a turbine combustor, comprising:
 a plurality of fuel nozzles; and 
 a combustor cap assembly comprising a plurality of individual sectors supporting the plurality of fuel nozzles, wherein each sector of the plurality of individual sectors is fixedly attached to a respective fuel nozzle of the plurality of fuel nozzles. 
   
     
     
         2 . The system of  claim 1 , wherein each sector of the plurality of individual sectors comprises a wedge-shaped outer perimeter. 
     
     
         3 . The system of  claim 2 , wherein each sector of the plurality of individual sectors comprises a circular inner perimeter that extends around a circular outer perimeter of the respective fuel nozzle of the plurality of fuel nozzles. 
     
     
         4 . The system of  claim 3 , wherein each fuel nozzle of the plurality of fuel nozzles comprises an air conduit having at least one swirl vane, and each fuel nozzle comprises at least one fuel outlet configured to output a fuel flow into an air flow passing through the air conduit. 
     
     
         5 . The system of  claim 1 , wherein each sector of the plurality of individual sectors comprises at least one hula seal disposed between each pair of abutting sectors of the plurality of individual sectors, or at least one hula seal disposed between each sector and a liner surrounding the combustor cap assembly, or at least one hula seal disposed between each sector and a central fuel nozzle. 
     
     
         6 . The system of  claim 5 , wherein the at least one hula seal is configured to maintain a seal while damping vibration and/or allowing movement due to thermal expansion or contraction of the plurality of individual sectors. 
     
     
         7 . The system of  claim 1 , wherein the plurality of fuel nozzles comprises a plurality of peripheral fuel nozzles disposed about a central fuel nozzle, and each peripheral fuel nozzle is fixedly attached to one of the plurality of individual sectors. 
     
     
         8 . The system of  claim 1 , wherein each sector of the plurality of individual sectors comprises at least one coolant inlet and at least one coolant outlet configured to pass a cooling air flow. 
     
     
         9 . The system of  claim 8 , wherein the at least one coolant outlet of each sector of the plurality of individual sectors is disposed in a front plate configured to face a combustion chamber of the turbine combustor, and the at least one coolant outlet is configured to pass the cooling air flow through the front plate into the combustion chamber. 
     
     
         10 . The system of  claim 8 , wherein the at least one coolant inlet of each sector of the plurality of individual sectors comprises a first coolant inlet and a second coolant inlet, the first coolant inlet is configured to receive a first cooling air flow from an air flow region between a liner and a flow sleeve of the turbine combustor, and the second coolant inlet is configured to receive a second cooling air flow that is different than the first cooling air flow. 
     
     
         11 . The system of  claim 1 , wherein each sector of the plurality of individual sectors comprises a first front plate and a second front plate, each sector of the plurality of individual sectors is configured to receive a cooling air flow and direct the cooling air flow through apertures of the first and second front plates, wherein the first front plate is configured to impinge the cooling air flow on the second front plate. 
     
     
         12 . The system of  claim 1 , comprising a turbine engine having the turbine combustor. 
     
     
         13 . A system, comprising:
 a first fuel nozzle; and   a first individual sector having a first outer perimeter configured to fit together with outer perimeters a plurality of individual sectors to form a combustor cap assembly of a turbine combustor, wherein the first individual sector comprises a first inner perimeter that fits about a nozzle outer perimeter of the first fuel nozzle, and the first individual sector is fixedly attached to the first fuel nozzle.   
     
     
         14 . The system of  claim 13 , wherein the first outer perimeter comprises a wedge-shaped outer perimeter. 
     
     
         15 . The system of  claim 13 , wherein the first outer perimeter comprises at least one hula seal. 
     
     
         16 . The system of  claim 13 , wherein the nozzle outer perimeter comprises a circular outer perimeter, and the first inner perimeter comprises a circular inner perimeter. 
     
     
         17 . The system of  claim 13 , wherein the first individual sector has a front plate configured to face a combustion chamber of the turbine combustor, and the front plate has a plurality of cooling outlets to pass a cooling air flow into the combustion chamber. 
     
     
         18 . The system of  claim 13 , wherein the first fuel nozzle comprises an air conduit having at least one swirl vane, and the first fuel nozzle comprises at least one fuel outlet configured to output a fuel flow into an air flow passing through the air conduit. 
     
     
         19 . A system, comprising:
 a first individual sector having a first outer perimeter configured to fit together with outer perimeters of a plurality of individual sectors to form a combustor cap assembly of a turbine combustor, wherein the first individual sector comprises a first inner perimeter configured to fit about a nozzle outer perimeter of a first fuel nozzle, and the first individual sector is configured to fixedly attach to the first fuel nozzle.   
     
     
         20 . The system of  claim 19 , comprising the combustor cap assembly including the plurality of individual sectors, wherein each sector of the plurality of individual sectors comprises a wedge-shaped outer perimeter having at least one hula seal.