Turbine vane

Abstract

A plurality of film cooling holes are formed, so as to communicate with a front cooling passage, in a vane surface on the front-edge side of a stator vane body of a turbine stator vane. The hole cross-section of each of the film cooling holes has a rectangular long-hole shape extending in a direction parallel to the cross-section along the span direction and having a rounded corner. The hole-center line of each of the film cooling holes is inclined with respect to the thickness direction in the cross-section along the span direction. The exit-side portion of the hole wall surface of each of the film cooling holes is inclined with respect to the thickness direction by a greater degree than that of the hole-center line.

What is claimed is: 
     
         1 . A turbine vane for a turbine of a gas turbine engine, and capable of being cooled by cooling air, the turbine vane comprising:
 a vane body including:
 a vane surface; 
 a cooling passage allowing the cooling air to flow into the vane body, and 
 a plurality of film cooling holes formed in the vane surface on a front edge side of the vane body so as to communicate with the cooling passage to jet out the cooling air through the plurality of film cooling holes, a hole cross section of each film cooling hole having a long-hole shape extending in a direction parallel to a cross section along a span direction of the vane body, a hole-center line of each film cooling hole tilting from a thickness direction of the vane body on a cross section of the vane surface along the span direction, and an exit-side and obtuse angle-side portion of a hole wall surface of each film cooling hole tilting further from the thickness direction than the hole-center line on the cross section along the span direction. 
   
     
     
         2 . The turbine vane according to  claim 1 , wherein
 an aspect ratio of the hole cross section of each film cooling hole is set in a range of 1.1 to 3.0.   
     
     
         3 . The turbine vane according to  claim 1 , wherein
 a tilt angle of the hole-center line of each film cooling hole to the thickness direction is set in a range of 20° to 60°.   
     
     
         4 . The turbine vane according to  claim 1 , wherein
 a tilt angle of the exit-side and obtuse angle-side portion of the wall surface of each film cooling hole to the thickness direction is set in a range of 5° to 20°.   
     
     
         5 . The turbine vane according to  claim 1 , wherein
 a plurality of other film cooling holes through which to jet out the cooling air are formed in a vane surface other than the vane surface on the front-edge side so as to communicate with the cooling passage.