Additive single-piece bore-cooled combustor dome

Abstract

Methods and apparatus for an additive, single-piece, bore-cooled combustor dome or liner are disclosed. An example combustor dome forms an integral part including: a plurality of first openings; a plurality of second openings; and a plurality of passages formed in the combustor dome connecting respective ones of the plurality of first openings with respective ones of the plurality of second openings. The combustor dome is configured to allow air to enter through the plurality of first openings and travel through the plurality of passages to exit through the plurality of second openings, the air to transfer heat from the combustion section.

1 . A combustor dome for a combustion section of a turbine engine, the combustor dome forming an integral part of a material, the combustor dome comprising:
 a plurality of first openings;   a plurality of second openings; and   a plurality of passages formed in the combustor dome connecting respective ones of the plurality of first openings with respective ones of the plurality of second openings, each passage extending through the material of the combustor dome from the respective first opening to the respective second opening, the respective passage including a first portion extending along a first axis within the material of the combustor dome and a second portion extending along a second axis within the material of the combustor dome,   wherein the combustor dome is configured to allow air to enter through the plurality of first openings and travel through the plurality of passages to exit through the plurality of second openings, the air to transfer heat from the combustion section.   
     
     
         2 . The combustor dome of  claim 1 , wherein the combustor dome is formed from additive manufacturing. 
     
     
         3 . The combustor dome of  claim 1 , wherein the material includes at least one of a cobalt alloy or a nickel alloy. 
     
     
         4 . The combustor dome of  claim 1 , further including a ferrule. 
     
     
         5 . The combustor dome of  claim 1 , further connected to an igniter port. 
     
     
         6 . The combustor dome of  claim 1 , wherein a size of the plurality of first openings and a size of the plurality of second openings corresponds to an amount of air flow and cooling to be provided by the combustor dome. 
     
     
         7 . The combustor dome of  claim 1 , wherein a size of the plurality of passages is customizable based on at least one of aerodynamics or heat transfer. 
     
     
         8 . A combustion section of a turbine engine, the combustion section comprising:
 a combustion chamber; and   a combustor dome enclosing at least a portion of the combustion chamber, the combustor dome formed of a material and including:
 a plurality of first openings; 
 a plurality of second openings; and 
 a plurality of passages formed in the combustor dome connecting respective ones of the plurality of first openings with respective ones of the plurality of second openings, each passage extending through the material of the combustor dome from the respective first opening to the respective second opening, the respective passage including a first portion extending along a first axis within the material of the combustor dome and a second portion extending along a second axis within the material of the combustor dome, 
   wherein the combustor dome is configured to allow air to enter through the plurality of first openings and travel through the plurality of passages to exit through the plurality of second openings, the air to transfer heat from the combustion chamber.   
     
     
         9 . The combustion section of  claim 8 , wherein the combustor dome is formed from additive manufacturing. 
     
     
         10 . The combustion section of  claim 8 , wherein the material includes at least one of a cobalt alloy or a nickel alloy. 
     
     
         11 . The combustion section of  claim 8 , further including a ferrule. 
     
     
         12 . The combustion section of  claim 11 , wherein the ferrule is integrated with the combustor dome. 
     
     
         13 . The combustion section of  claim 8 , further including an igniter port. 
     
     
         14 . The combustion section of  claim 8 , wherein a size of the plurality of first openings and a size of the plurality of second openings corresponds to an amount of air flow and cooling to be provided by the combustor dome. 
     
     
         15 . The combustion section of  claim 8 , wherein a size of the plurality of passages is customizable based on at least one of aerodynamics or heat transfer. 
     
     
         16 . A combustor liner of a turbine engine, the combustor liner comprising:
 an inlet means;   an outlet means; and   a passage means connecting the inlet means to the outlet means within the combustor liner,   wherein the inlet means, the outlet means, and the passage means are formed integral to the combustor liner and allow air to travel from the inlet means to the outlet means via the passage means, the passage means extending through material of the combustor liner from the inlet means to the outlet means, the passage means including a first portion extending along a first axis and a second portion extending along a second axis.   
     
     
         17 . The combustor liner of  claim 16 , wherein the combustor liner is formed from additive manufacturing. 
     
     
         18 . The combustor liner of  claim 16 , wherein a size of the inlet means and a size of the outlet means corresponds to an amount of air flow and cooling to be provided by the combustor liner. 
     
     
         19 . The combustor liner of  claim 16 , wherein a size of the passage means is customizable based on at least one of aerodynamics or heat transfer. 
     
     
         20 . The combustor liner of  claim 16 , further connected to a fuel-air entry means.