Faceted dome assemblies for gas turbine engine combustors

Abstract

A dome assembly for a gas turbine engine includes a plurality of faceted segments and a plurality of openings. The plurality of faceted segments are coupled together to form a dome structure that is configured to be disposed between an inner liner and an outer liner that circumscribes the inner liner. The plurality of openings are each opening formed within a respective faceted segment, and are configured to at least partially house an atomizer therein. Each faceted segment is at least substantially flat.

1 . A dome assembly for a gas turbine engine, the dome assembly comprising:
 a plurality of faceted segments coupled together to form a dome structure that is configured to be disposed between an inner liner and an outer liner that circumscribes the inner liner; and   a plurality of openings, each opening formed within a respective faceted segment and configured to at least partially house an atomizer therein;   wherein each faceted segment is at least substantially flat.   
   
   
       2 . The dome assembly of  claim 1 , wherein:
 each faceted segment is configured to have a heat shield disposed proximate thereto; and   a gap is formed between the faceted segment and at least a portion of the heat shield disposed proximate thereto, the gap being at least substantially uniform in size.   
   
   
       3 . The dome assembly of  claim 2 , wherein each faceted segment further comprises a blocking mechanism configured to minimize rotation of the heat shield disposed proximate thereto. 
   
   
       4 . The dome assembly of  claim 3 , wherein each heat shield has a plurality of mating slots, and the blocking mechanism for each faceted segment comprises three clocking tabs, each clocking tab configured to be disposed against one of the plurality of mating slots of a respective heat shield. 
   
   
       5 . A combustor for a gas turbine engine, comprising:
 an inner liner;   an outer liner circumscribing the inner liner; and   a dome assembly coupled to and disposed between the inner liner and the outer liner, the dome assembly comprising a plurality of faceted segments, each faceted segment being at least substantially flat.   
   
   
       6 . The combustor of  claim 5 , wherein each faceted segment includes an opening, the opening configured to allow an atomizer to be placed at least partially within the opening. 
   
   
       7 . The combustor of  claim 5 , wherein the dome assembly further comprises:
 a first wall coupling the plurality of faceted segments to the inner liner; and   a second wall coupling the plurality of faceted segments to the outer liner.   
   
   
       8 . The combustor of  claim 5 , further comprising:
 a heat shield unit disposed proximate one of the faceted segments.   
   
   
       9 . The combustor of  claim 8 , wherein the heat shield unit comprises a plurality of heat shields, each heat shield disposed proximate a respective faceted segment. 
   
   
       10 . The combustor of  claim 9 , wherein a gap is formed between the dome assembly and a portion of the heat shield unit, the gap being at least substantially uniform in size. 
   
   
       11 . The combustor of  claim 9 , wherein each faceted segment further comprises a blocking mechanism configured to minimize rotation of the heat shield disposed proximate thereto. 
   
   
       12 . The combustor of  claim 11 , wherein each heat shield has a plurality of mating slots, and the blocking mechanism for each faceted segment comprises three clocking tabs, each clocking tab configured to be disposed against one of the plurality of mating slots of a respective heat shield. 
   
   
       13 . The combustor of  claim 5 , wherein the dome assembly further comprises:
 a first wall coupling the plurality of faceted segments to the inner liner; and   a second wall coupling the plurality of faceted segments to the outer liner.   
   
   
       14 . A gas turbine engine, comprising:
 a compressor having an inlet and an outlet and operable to supply compressed air;   a combustor coupled to receive at least a portion of the compressed air from the compressor and operable to supply combusted air, the combustor comprising:
 an inner liner; 
 an outer liner circumscribing the inner liner; and 
 a dome assembly coupled to and disposed between the inner liner and the outer liner, the dome assembly comprising a plurality of faceted segments, each faceted segment being at least substantially flat; and 
   a turbine coupled to receive the combusted air from the combustor.   
   
   
       15 . The gas turbine engine of  claim 14 , wherein each faceted segment includes an opening, the opening configured to allow an atomizer to be placed at least partially within the opening. 
   
   
       16 . The gas turbine engine of  claim 14 , further comprising:
 a heat shield unit disposed proximate one of the faceted segments.   
   
   
       17 . The gas turbine engine of  claim 16 , wherein the heat shield unit comprises a plurality of heat shields, each heat shield disposed proximate a respective faceted segment. 
   
   
       18 . The gas turbine engine of  claim 16 , wherein a gap is formed between the dome assembly and a portion of the heat shield unit, the gap being at least substantially uniform in size. 
   
   
       19 . The gas turbine engine of  claim 17 , wherein each faceted segment further comprises a blocking mechanism configured to minimize rotation of the heat shield disposed proximate thereto. 
   
   
       20 . The gas turbine engine of  claim 19 , wherein each heat shield has a plurality of mating slots, and the blocking mechanism for each faceted segment comprises three clocking tabs, each clocking tab configured to be disposed against one of the plurality of mating slots of a respective heat shield.