Gas turbine engine airfoil platform cooling

Abstract

An airfoil for a gas turbine engine includes an airfoil that extends from a platform that has first and second circumferential sides that respectively extend to first and second circumferential edges. The first circumferential side has a tapered surface at a first angle relative to a flow path surface. The second circumferential surface has a cooling hole that extends toward the second lateral edge at a second angle relative to the flow path surface. The tapered surface and the cooling hole are axially aligned with one another.

What is claimed is: 
     
         1 . An airfoil for a gas turbine engine comprising:
 an airfoil extending from a platform that has first and second circumferential sides respectively extending to first and second circumferential edges, the first circumferential side having a tapered surface at a first angle relative to a flow path surface, and the second circumferential surface having a cooling hole extending toward the second lateral edge at a second angle relative to the flow path surface, the tapered surface and the cooling hole axially aligned with one another.   
     
     
         2 . The airfoil according to  claim 1 , wherein the airfoil includes a cooling passage, the cooling hole in fluid communication with the cooling hole. 
     
     
         3 . The airfoil according to  claim 2 , wherein the second angle is 5-40°. 
     
     
         4 . The airfoil according to  claim 3 , wherein the second angle is 15-30°. 
     
     
         5 . The airfoil according to  claim 2 , comprising multiple cooling holes arranged in a cluster, the cluster arranged near a trailing edge of the airfoil on a pressure side. 
     
     
         6 . The airfoil according to  claim 5 , wherein the cluster is arranged within about three inches (76.2 mm) of an aft edge of the platform. 
     
     
         7 . The airfoil according to  claim 5 , wherein the cluster is within about 0.6 inch (15.2 mm) of the second lateral edge. 
     
     
         8 . The airfoil according to  claim 5 , wherein the cooling holes each have a diameter equivalent of 0.010-0.050 inch (0.25-1.27 mm). 
     
     
         9 . The airfoil according to  claim 1 , wherein the first angle is 1-20°. 
     
     
         10 . The airfoil according to  claim 9 , wherein the first angle is 2-15°. 
     
     
         11 . The airfoil according to  claim 9 , wherein the tapered surface extends within about three inches (76.2 mm) of the first circumferential edge to an aft edge of the platform. 
     
     
         12 . The airfoil according to  claim 11 , wherein the tapered surface extends less that 0.7 inch (17.78 mm) from the first circumferential edge. 
     
     
         13 . The airfoil according to  claim 1 , wherein the airfoil is a turbine blade. 
     
     
         14 . An array of airfoils for a gas turbine engine comprising:
 adjacent airfoils, each airfoil extending from a platform that has first and second circumferential sides respectively extending to first and second circumferential edges, the first circumferential side having a tapered surface at a first angle relative to a flow path surface, and the second circumferential surface having a cooling hole extending toward the second lateral edge at a second angle relative to the flow path surface, the tapered surface and the cooling hole axially aligned with one another.   
     
     
         15 . The array of airfoils according to  claim 14 , wherein the airfoils includes a cooling passage, the cooling hole in fluid communication with the cooling passage. 
     
     
         16 . The array of airfoils according to  claim 15 , wherein the second angle is 5-40°, and comprising multiple cooling holes arranged in a cluster, the cluster arranged near a trailing edge of the airfoil on a pressure side. 
     
     
         17 . The array of airfoils according to  claim 16 , wherein the cluster is arranged within about three inches (76.2 mm) of an aft edge of the platform, the cluster is within about 0.6 inch (15.2 mm) of the second lateral edge, wherein the cooling holes each have a diameter equivalent of 0.010-0.050 inch (0.25-1.27 mm). 
     
     
         18 . The array of airfoils according to  claim 16 , wherein the first angle is 1-20°. 
     
     
         19 . The array of airfoils according to  claim 18 , wherein the tapered surface extends within about three inches (76.2 mm) of the first circumferential edge to an aft edge of the platform, wherein the tapered surface extends less that 0.7 inch (17.78 mm) from the first circumferential edge. 
     
     
         20 . The array of airfoils according to  claim 14 , wherein the airfoil is a turbine blade.