GAS TURBINE ENGINE AIRFOIL
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.
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.