Gas turbine engine airfoil

Abstract

A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner portion of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A bowed tip portion extends perpendicular to a mid-camber line of the airfoil.

What is claimed is: 
     
         1 . A component for a gas turbine engine comprising:
 a platform having a radially inner side and a radially outer side;   a root portion extending from the radially inner portion of the platform; and   an airfoil extending from the radially outer side of the platform, the airfoil including:
 a pressure side extending between a leading edge and a trailing edge; 
 a suction side extending between the leading edge and the trailing edge; and 
 a bowed tip portion extending perpendicular to a mid-camber line of the airfoil. 
   
     
     
         2 . The component of  claim 1 , wherein the bowed tip portion extends in a circumferential direction and an axial direction. 
     
     
         3 . The component of  claim 2 , wherein the bowed tip portion beings at between 75% and 85% of a span of the airfoil. 
     
     
         4 . The component of  claim 3 , wherein the bowed tip portion begins at 80% of the span of the airfoil. 
     
     
         5 . The component of  claim 1 , wherein said bowed tip portion is bowed between 3 and 19.6 degrees perpendicular to the mid-camber line in a circumferential direction. 
     
     
         6 . The component of  claim 5 , wherein the bowed surface is bowed between 3 and 19.6 degrees perpendicular to the mid-camber line in an axial direction. 
     
     
         7 . The component of  claim 6 , wherein the bowed surface is bowed by the same degree in both the circumferential direction and the axial direction. 
     
     
         8 . The component of  claim 6 , wherein the bowed tip portion follows a curvilinear profile beginning at 3 degrees and increasing to 19.6 degrees. 
     
     
         9 . The component of  claim 6 , wherein a leading edge of the bowed tip portion includes a rounded contour to reduce vibration and oxidation. 
     
     
         10 . A gas turbine engine comprising:
 a compressor section and a turbine section; and   a circumferential array of airfoils located in one of the compressor section and the turbine section, wherein each of the airfoils include:
 a pressure side extending between a leading edge and a trailing edge; 
 a suction side extending between the leading edge and the trailing edge; and 
 a bowed tip portion extending perpendicular to a mid-camber line of the airfoil. 
   
     
     
         11 . The gas turbine engine of  claim 10 , wherein the bowed tip portion extends in a circumferential direction and an axial direction. 
     
     
         12 . The gas turbine engine of  claim 11 , wherein the bowed tip portion beings at between 75% and 85% of a span of the airfoil. 
     
     
         13 . The gas turbine engine of  claim 12 , wherein the bowed tip portion begins at 80% of the span of the airfoil. 
     
     
         14 . The gas turbine engine of  claim 10 , wherein said bowed tip portion is bowed between 2 and 15 degrees perpendicular to the mid-camber line in a circumferential direction. 
     
     
         15 . The gas turbine engine of  claim 14 , wherein the bowed surface is bowed between 3 and 19.6 degrees perpendicular to the mid-camber line in an axial direction. 
     
     
         16 . The gas turbine engine of  claim 15 , wherein the bowed surface is bowed by the same degree in both the circumferential direction and the axial direction. 
     
     
         17 . The gas turbine engine of  claim 15 , wherein the bowed tip portion follows a curvilinear profile beginning at 3 degrees and increasing to 19.6 degrees.