Airfoil of gas turbine engine

Abstract

An airfoil of gas turbine engine is provided, which can improve cooling efficiency at a leading edge of the airfoil even when a location of combustion gas stagnation changes, without having to increase cooling air flowrate. The airfoil of gas turbine engine includes a cooling passage formed inside the airfoil to guide cooling air, and one or more cooling slots in elongated form, extending through the leading edge of the airfoil to a direction of the cooling passage and across a lengthwise direction of the leading edge.

What is claimed is: 
     
         1 . An airfoil of gas turbine engine comprising an efficient film cooling structure at a leading edge thereof, comprising:
 a cooling passage formed inside the airfoil to guide cooling air; and   one or more cooling slots in elongated form, extending through the leading edge of the airfoil to a direction of the cooling passage and across a lengthwise direction of the leading edge.   
     
     
         2 . The airfoil of  claim 1 , wherein one end of each of the one or more cooling slots is on a compressive surface of the airfoil, and the other end thereof is on a suction surface of the airfoil. 
     
     
         3 . The airfoil of  claim 1 , wherein both corners of each of the one or more cooling slots are rounded to a circular arc shape. 
     
     
         4 . The airfoil of  claim 1 , wherein the one or more cooling slots comprise a first cooling slot and a second cooling slot, and
 the film cooling structure further comprises one or more cooling holes formed on the leading edge between the first and second cooling slots, in a manner of extending through the leading edge in a cylindrical shape to a direction of the cooling passage.   
     
     
         5 . The airfoil of  claim 1 , wherein the one or more cooling slots are slanted with respect to an end of the airfoil. 
     
     
         6 . The airfoil of  claim 5 , wherein the one or more cooling slots are so slanted that the cooling slots become closer to the end of the airfoil at the cooling passage than at the leading edge. 
     
     
         7 . The airfoil of  claim 5 , wherein the one or more cooling slots are so slanted that the cooling slots become farther away from the end of the airfoil at the cooling passage than at the leading edge. 
     
     
         8 . The airfoil of  claim 1 , wherein the airfoil is an airfoil of a turbine nozzle vane or a turbine blade.