Gas turbine engine component with flow separating rib

Abstract

A component according to an exemplary aspect of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion.

What is claimed is: 
     
         1 . A component, comprising:
 a wall that extends about a cooling cavity, wherein said cooling cavity is a dual-fed cavity that is fed from at least two different locations; and   a rib that separates said cooling cavity into a first portion and a second portion that is fluidly isolated from said first portion.   
     
     
         2 . The component as recited in  claim 1 , wherein said component is one of a vane, a blade, a blade outer air seal (BOAS), and a liner. 
     
     
         3 . The component as recited in  claim 1 , wherein said wall circumscribes said cooling cavity. 
     
     
         4 . The component as recited in  claim 1 , wherein first portion of said cooling cavity is fed with a first cooling fluid and said second portion of said cooling cavity is fed with a second, different cooling fluid. 
     
     
         5 . The component as recited in  claim 1 , wherein said first portion is an outer diameter portion and said second portion is an inner diameter portion of said cooling cavity. 
     
     
         6 . The component as recited in  claim 1 , wherein said first portion is circumferentially offset from said second portion. 
     
     
         7 . The component as recited in  claim 1 , wherein said rib connects between opposing sides of said wall. 
     
     
         8 . The component as recited in  claim 1 , wherein said rib extends in an axial direction inside of said cooling cavity. 
     
     
         9 . The component as recited in  claim 1 , comprising a plurality of openings through portions of said wall associated with both said first portion and said second portion. 
     
     
         10 . The component as recited in  claim 9 , wherein said plurality of openings are film cooling holes. 
     
     
         11 . A gas turbine engine, comprising:
 a component that defines a cooling circuit configured to cool said component with a cooling fluid, said cooling circuit including:
 a cooling cavity disposed inside of said component; and 
 an axial rib that divides said cooling cavity into a first portion and a second portion that is separate from said first portion. 
   
     
     
         12 . The gas turbine engine as recited in  claim 11 , wherein said rib fluidly isolates said first portion from said second portion. 
     
     
         13 . The gas turbine engine as recited in  claim 11 , wherein said cooling circuit is disposed inside an airfoil of said component. 
     
     
         14 . The gas turbine engine as recited in  claim 11 , wherein said cooling circuit is disposed inside of a body of said component. 
     
     
         15 . The gas turbine engine as recited in  claim 11 , wherein said cooling circuit includes a plurality of openings that expel said cooling fluid from both said first portion and said second portion. 
     
     
         16 . A method of cooling a gas turbine engine component, comprising:
 dividing a cooling cavity disposed inside the gas turbine engine component into a first portion and a second portion with a rib;   communicating a first cooling fluid from a first location into the first portion; and   communicating a second cooling fluid from a second location into the second portion.   
     
     
         17 . The method as recited in  claim 16 , comprising expelling the first and second cooling fluids from the cooling cavity through a plurality of openings. 
     
     
         18 . The method as recited in  claim 16 , wherein the second cooling fluid is separate from the first cooling fluid. 
     
     
         19 . The method as recited in  claim 16 , wherein the rib fluidly isolates the first portion from the second portion. 
     
     
         20 . The method as recited in  claim 16 , wherein one of the first portion and the second portion of the cooling cavity is positioned in a high pressure area and the other of the first portion and the second portions is positioned in a low pressure area.