Gas turbine engine component cooling circuit

Abstract

A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling circuit disposed inside of the body portion. The cooling circuit includes a first baffle received within a first core cavity that extends inside of the body portion, a second baffle received within a second core cavity that extends inside of the body portion, and a first rib disposed between the first core cavity and the second core cavity. The first baffle is in fluid communication with the second baffle through the first rib.

1 . A component for a gas turbine engine, comprising:
 a body portion; and   a cooling circuit disposed inside of said body portion, wherein said cooling circuit includes:
 a first baffle received within a first core cavity that extends inside of said body portion; 
 a second baffle received within a second core cavity that extends inside of said body portion; and 
 a first rib disposed between said first core cavity and said second core cavity, wherein said first baffle is in fluid communication with said second baffle through said first rib. 
   
     
     
         2 . The component as recited in  claim 1 , wherein the component is a vane. 
     
     
         3 . The component as recited in  claim 1 , wherein the component is a blade. 
     
     
         4 . The component as recited in  claim 1 , wherein said first rib includes a plurality of openings that fluidly connect said first core cavity and said second core cavity. 
     
     
         5 . The component as recited in  claim 4 , wherein said plurality of openings are positioned in a staggered relationship across a radial span of said first rib. 
     
     
         6 . The component as recited in  claim 4 , wherein said plurality of openings each axially extend through said first rib in a direction that extends from a leading edge toward a trailing edge of said body portion. 
     
     
         7 . The component as recited in  claim 1 , wherein said first baffle and said second baffle each include a plurality of feed openings that extend through said first baffle and said second baffle. 
     
     
         8 . The component as recited in  claim 7 , wherein said plurality of feed openings extend through each wall of said first baffle and said second baffle. 
     
     
         9 . The component as recited in  claim 1 , wherein a space extends between an interior wall of said first core cavity and said first baffle. 
     
     
         10 . The component as recited in  claim 1 , wherein said cooling circuit includes a third baffle received within a third core cavity that extends inside of said body portion. 
     
     
         11 . The component as recited in  claim 10 , wherein said third baffle is in fluid communication with said second baffle through a second rib. 
     
     
         12 . The component as recited in  claim 10 , wherein said cooling circuit includes a trailing edge cavity in fluid communication with said third core cavity. 
     
     
         13 . A gas turbine engine, comprising:
 a compressor section;   a combustor section in fluid communication with said compressor section;   a turbine section in fluid communication with said combustor section; and   wherein at least one of said compressor section and said turbine section includes at least one component having a body portion and a cooling circuit disposed inside of said body portion, wherein said cooling circuit includes:
 a first baffle received within a first core cavity that extends inside of said body portion; 
 a second baffle received within a second core cavity that extends inside of said body portion; and 
 a first rib disposed between said first core cavity and said second core cavity, wherein said first baffle is in fluid communication with said second baffle through said first rib. 
   
     
     
         14 . The gas turbine engine as recited in  claim 13 , wherein said at least one component is a vane. 
     
     
         15 . The gas turbine engine as recited in  claim 13 , wherein said first rib includes a plurality of openings. 
     
     
         16 . The gas turbine engine as recited in  claim 13 , wherein said first baffle and said second baffle each include a plurality of feed openings that extend through said first baffle and said second baffle. 
     
     
         17 . The gas turbine engine as recited in  claim 13 , wherein said cooling circuit includes a third baffle received within a third core cavity that extends inside of said body portion. 
     
     
         18 . A method of cooling a component of a gas turbine engine, comprising the steps of:
 feeding a cooling airflow into a first core cavity of a body portion of the component; and   expelling the cooling airflow from the body portion through a second core cavity that is in fluid communication with the first core cavity.   
     
     
         19 . The method as recited in  claim 18 , wherein the step of feeding includes:
 communicating the cooling airflow through a plurality feed openings in a first baffle positioned within the first core cavity; and   impingement cooling at least one interior wall of the body portion with the cooling airflow that is communicated through the plurality of feed openings prior to the step of expelling.   
     
     
         20 . The method as recited in  claim 18 , comprising the step of:
 communicating the cooling airflow through a first rib that is disposed between the first core cavity and the second core cavity prior to the step of expelling.