Blade outer air seal

Abstract

A blade outer air seal for a gas turbine engine includes a first side surface, a second side surface, and a wall. The wall extends between the first side surface and the second side surface and has one or more holes formed therein. The holes are spaced from the first side surface and/or the second side surface and have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal.

1 . A blade outer air seal for a gas turbine engine, the blade outer air seal comprising:
 a first side surface;   a second side surface; and   a wall extending between the first side surface and the second side surface, wherein one or more holes are formed in the wall and are spaced from at least one of the first side surface or second side surface, and wherein the one or more holes have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal.   
     
     
         2 . The blade outer air seal of  claim 1 , wherein the one or more holes have areas between about 0.02% and 0.30% of a surface area of the blade outer air seal 
     
     
         3 . The blade outer air seal of  claim 1 , wherein the one or more holes comprise six holes with three holes positioned adjacent the first side surface and three holes positioned adjacent the second side surface. 
     
     
         4 . The blade outer air seal of  claim 1 , further comprising internal passages that extend through the wall from the first side surface to the second side surface, and wherein the one or more holes communicate with internal passages. 
     
     
         5 . The blade outer air seal of  claim 4 , wherein the one or more holes comprise six holes with one hole for communicating with each one of the internal passages 
     
     
         6 . The blade outer air seal of  claim 4 , wherein each of the internal passages has a radial height between 30% to 40% of a total radial thickness the wall. 
     
     
         7 . The blade outer air seal of  claim 5 , wherein the internal passages together have an axial length that comprises between 75% and 85% of the axial length of the wall. 
     
     
         8 . The blade outer air seal of  claim 1 , further comprising one or more forward hooks that extend from the wall, wherein at least one of the forward hooks has a slot therein that is offset relative to an axis of symmetry of the blade outer air seal. 
     
     
         9 . The blade outer air seal of  claim 8 , wherein at least one of the forward hooks has an angled wall that extends from an outer radial surface of the at least one of the forward hooks to the wall. 
     
     
         10 . The blade outer air seal of  claim 1 , wherein the wall has a thermal barrier coating applied to an inner radial surface thereof, wherein the thermal barrier coating has a radial thickness between 3% and 10% of a total radial thickness of the wall, wherein the wall includes a bond coat, and wherein the bond coat has a radial thickness between 3% and 10% of a total radial thickness of the wall. 
     
     
         11 . A blade outer air seal for a gas turbine engine, the blade outer air seal comprising:
 a first side surface;   a second side surface; and   a wall extending between the first side surface and the second side surface, wherein the blade outer air seal has a wall with a bond coat and a thermal barrier coating, and wherein both the bond coat and the thermal barrier coating have a radial thickness between 3% and 10% of the total radial thickness of the wall.   
     
     
         12 . The blade outer air seal of  claim 11 , one or more holes are formed in the wall and are spaced from at least one of the first side surface or second side surface, and wherein the one or more holes have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal. 
     
     
         13 . The blade outer air seal of  claim 12 , wherein the one or more holes have areas between about 0.02% and 0.30% of a surface area of the blade outer air seal. 
     
     
         14 . The blade outer air seal of  claim 13 , wherein the one or more holes comprise six holes with three holes positioned adjacent the first side surface and three holes positioned adjacent the second side surface. 
     
     
         15 . The blade outer air seal of  claim 11 , further comprising internal passages that extend through the wall from the first side surface to the second side surface, and wherein the one or more holes communicate with internal passages. 
     
     
         16 . The blade outer air seal of  claim 15 , wherein each of the internal passages has a radial height between 30% to 40% of a total radial thickness the wall. 
     
     
         17 . The blade outer air seal of  claim 15 , wherein the internal passages together have an axial length that comprises between 75% and 85% of the axial length of the wall. 
     
     
         18 . The blade outer air seal of  claim 11 , further comprising one or more forward hooks that extend from the wall, wherein at least one of the forward hooks has a slot therein that is offset relative to an axis of symmetry of the blade outer air seal, and wherein at least one of the forward hooks has an angled wall that extends from an outer radial surface of the at least one of the forward hooks to the wall. 
     
     
         19 . A blade outer air seal for a gas turbine engine, the blade outer air seal comprising:
 a first side surface;   a second side surface;   a wall extending between the first side surface and the second side surface; and   one or more forward hooks extending from the wall, wherein at least one of the forward hooks has a slot therein that is offset relative to an axis of symmetry of the blade outer air seal.   
     
     
         20 . The blade outer air seal of  claim 19 , wherein at least one of the forward hooks has an angled wall that extends from an outer radial surface of the at least one of the forward hooks to the wall.