Blade outer air seal with passage joined cavities

Abstract

A blade outer air seal assembly includes a body that defines a first cavity separated from a second cavity by a circumferential rib. The circumferential rib includes at least one passage which provides communication between the first cavity and the second cavity.

1 . A blade outer air seal assembly comprising:
 a body which defines a first cavity separated from a second cavity by a circumferential rib, said circumferential rib includes at least one passage which provides communication between said first cavity and said second cavity.   
     
     
         2 . The blade outer air seal assembly as recited in  claim 1 , further comprising an impingement plate which encloses said first cavity and said second cavity. 
     
     
         3 . The blade outer air seal assembly as recited in  claim 1 , wherein said at least one passage comprises three passages. 
     
     
         4 . The blade outer air seal assembly as recited in  claim 3 , wherein said three passages removes approximately 3.5% of said rib. 
     
     
         5 . The blade outer air seal assembly as recited in  claim 1 , wherein said at least one passage removes approximately 3.5% of said rib. 
     
     
         6 . The blade outer air seal assembly as recited in  claim 1 , wherein said first cavity is a forward cavity and said second cavity is axially aft of said first cavity. 
     
     
         7 . The blade outer air seal assembly as recited in  claim 6 , wherein said at least one passage comprises three passages. 
     
     
         8 . The blade outer air seal assembly as recited in  claim 7 , wherein said three passages removes approximately 3.5% of said rib. 
     
     
         10 . A method of communicating a secondary cooling airflow within a gas turbine engine comprising:
 segregating a first cavity from a second cavity by a circumferential rib, the circumferential rib having at least one passage; and   communicating secondary cooling airflow between the first cavity and the second cavity through the at least one passage.   
     
     
         11 . The method as recited in  claim 10 , communicating the secondary cooling airflow into the first cavity and the second cavity through a single impingement plate. 
     
     
         12 . The method as recited in  claim 11 , communicating the secondary cooling airflow from the first cavity and the second cavity through a multiple of edge holes to a core flow.