Airfoil trailing edge

Abstract

An airfoil includes a radially inner edge extending in a radial direction of the airfoil to a radially outer edge. Also included is a leading edge extending in an axial direction of the airfoil to a trailing edge. Further included is a trailing edge geometry comprising at least one wave segment having simultaneous curvature in at least two directions.

1 . An airfoil comprising:
 a radially inner edge extending in a radial direction of the airfoil to a radially outer edge;   a leading edge extending in an axial direction of the airfoil to a trailing edge; and   a trailing edge geometry comprising at least one wave segment having simultaneous curvature in at least two directions.   
     
     
         2 . The airfoil of  claim 1 , wherein the at least two directions comprises the axial direction and a circumferential direction. 
     
     
         3 . The airfoil of  claim 2 , wherein the at least one wave segment comprises a plurality of wave segments. 
     
     
         4 . The airfoil of  claim 3 , wherein at least one of the plurality of wave segments is radially oriented toward the radially inner edge and at least one of the plurality of wave segments is radially oriented toward the radially outer edge. 
     
     
         5 . The airfoil of  claim 3 , wherein each of the plurality of wave segments are radially oriented toward the radially outer edge. 
     
     
         6 . The airfoil of  claim 3 , wherein each of the plurality of wave segments are radially oriented toward the radially inner edge. 
     
     
         7 . The airfoil of  claim 2 , wherein the airfoil comprises a strut disposed in a compressor inlet region of a gas turbine engine. 
     
     
         8 . The airfoil of  claim 2 , wherein the airfoil comprises a stator vane disposed in a compressor section of a gas turbine engine. 
     
     
         9 . A compressor comprising:
 an airfoil;   a trailing edge of the airfoil; and   a trailing edge geometry comprising a plurality of wave segments including a first wave segment having a degree of curvature in an axial direction and a second wave segment having a degree of curvature in a circumferential direction.   
     
     
         10 . The compressor of  claim 9 , wherein the plurality of wave segments are disposed in an alternating arrangement of curvature in the axial direction and in the circumferential direction. 
     
     
         11 . The compressor of  claim 9 , wherein at least one of the plurality of wave segments is radially oriented toward a radially inner edge of the airfoil and at least one of the plurality of wave segments is radially oriented toward a radially outer edge of the airfoil. 
     
     
         12 . The compressor of  claim 9 , wherein each of the plurality of wave segments are radially oriented toward a radially outer edge of the airfoil. 
     
     
         13 . The compressor of  claim 9 , wherein each of the plurality of wave segments are radially oriented toward a radially inner edge of the airfoil. 
     
     
         14 . The compressor of  claim 9 , wherein the airfoil comprises a strut disposed in an inlet region of the compressor. 
     
     
         15 . The compressor of  claim 9 , wherein the airfoil comprises a stator vane disposed in the compressor. 
     
     
         16 . A gas turbine engine comprising:
 a compressor section;   a turbine section; and   an airfoil disposed in at least one of the compressor section and the turbine section, the airfoil having a trailing edge comprising a geometry having at least one wave segment including simultaneous curvature in an axial direction and in a circumferential direction.   
     
     
         17 . The gas turbine engine of  claim 16 , wherein the at least one wave segment comprises a plurality of wave segments. 
     
     
         18 . The gas turbine engine of  claim 17 , wherein at least one of the plurality of wave segments is radially oriented toward a radially inner edge of the airfoil and at least one of the plurality of wave segments is radially oriented toward a radially outer edge of the airfoil. 
     
     
         19 . The gas turbine engine of  claim 17 , wherein each of the plurality of wave segments are radially oriented toward a radially outer edge of the airfoil. 
     
     
         20 . The gas turbine engine of  claim 17 , wherein each of the plurality of wave segments are radially oriented toward a radially inner edge of the airfoil.