Gas turbine engine components with cooling hole trenches

Abstract

An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.

What is claimed is: 
     
         1 . An engine component, comprising:
 a body having an interior surface and an exterior surface;   a cooling hole formed in the body and extending from the interior surface; and   a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.   
     
     
         2 . The engine component of  claim 1 , wherein the nonconcave trench is defined by a nonconcave bottom wall extending in the downstream direction. 
     
     
         3 . The engine component of  claim 1 , wherein the nonconcave trench is defined by a straight bottom wall extending in the downstream direction. 
     
     
         4 . The engine component of  claim 3 , wherein the straight bottom wall is continuously straight from the cooling hole to the exterior surface. 
     
     
         5 . The engine component of  claim 1 , wherein the nonconcave trench is defined by a convex bottom wall extending in the downstream direction. 
     
     
         6 . The engine component of  claim 5 , wherein the convex bottom wall is continuously convex from the cooling hole to the exterior surface. 
     
     
         7 . The engine component of  claim 1 , wherein the cooling hole is a first cooling hole and the trench is a first cooling trench, and wherein the engine component further comprises additional cooling holes and additional trenches, each of the trenches being associated with a single cooling hole. 
     
     
         8 . The engine component of  claim 1 , wherein the cooling hole has a first cross-sectional shape in downstream portion with a first leading edge having a first shape, and the nonconcave trench has a second leading edge having a second shape, the second shape being similar to the first shape. 
     
     
         9 . The engine component of  claim 1 , wherein the cooling hole has a first length and the nonconcave trench extends in the downstream direction at a second length, the second length being at least three times the first length. 
     
     
         10 . The engine component of  claim 1 , wherein the nonconcave trench has a first width at a first position and a second width at a second position that is downstream of the first position, the second width being greater than the first width. 
     
     
         11 . The engine component of  claim 1 , wherein the cooling hole has a cross-sectional shape that is bean-shaped. 
     
     
         12 . The engine component of  claim 1 , wherein the cooling hole has a cross-sectional shape that is triad-shaped. 
     
     
         13 . The engine component of  claim 1 , wherein the cooling hole has a cross-sectional shape that is reverse B-shaped. 
     
     
         14 . The engine component of  claim 1 , wherein the cooling hole has a cross-sectional shape that is dumbbell-shaped. 
     
     
         15 . The engine component of  claim 1 , wherein the cooling hole has a cross-sectional shape that is a triangular. 
     
     
         16 . The engine component of  claim 1 , wherein the cooling hole has a cross-sectional shape that is an oval. 
     
     
         17 . A turbine section of a gas turbine engine, comprising:
 a housing defining a hot gas flow path;   a plurality of circumferential rows of airfoils disposed in the hot gas flow path;   a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils; and   a plurality of trenches, each of the plurality of trenches being associated with one of the plurality of cooling holes, wherein each of the trenches is defined by a straight bottom wall extending downstream of the respective cooling hole to an exterior surface of the respective airfoil.   
     
     
         18 . The turbine section of  claim 17 , wherein each of the cooling holes has a cross-sectional area that is bean-shaped, triad-shaped, reverse-B shaped, or dumbbell-shaped. 
     
     
         19 . A turbine section of a gas turbine engine, comprising:
 a housing defining a hot gas flow path;   a plurality of circumferential rows of airfoils disposed in the hot gas flow path;   a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils; and   a plurality of trenches, each of the plurality of trenches being associated with one of the plurality of cooling holes, wherein each of the trenches is defined by a convex bottom wall extending downstream of the respective cooling hole to an exterior surface of the respective airfoil.   
     
     
         20 . The turbine section of  claim 19 , wherein each of the cooling holes has a cross-sectional area that is bean-shaped, triad-shaped, reverse-B shaped, or dumbbell-shaped.