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 side 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 curvature inflection point is located between 30% and 70% of an axial chord length 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 side of the platform; and
an airfoil is a blade and extends from the radially outer side of the platform to an unshrouded end, 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 plurality of curvature inflection points located on the pressure side of the airfoil between 30% and 70% of an axial chord length of the airfoil with a curvature inflection point occurring at a span location with a smallest radius of curvature for the span location, the smallest radius of curvature is measured in an X-Y plane about an axis parallel to a radial direction of the airfoil, and the plurality of curvature inflection point includes a first curvature inflection point located at 50% span of the airfoil and between 40% and 50% of the axial chord length.
2. The component of claim 1 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 0% span of the airfoil and between 60% and 70% of the axial chord length.
3. The component of claim 1 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 25% span of the airfoil and between 50% and 60% of the axial chord length.
4. The component of claim 1 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 75% span of the airfoil and between 30% and 40% of the axial chord length.
5. The component of claim 1 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 90% span of the airfoil and between 30% and 40% of the axial chord length.
6. The component of claim 1 , wherein the plurality of curvature inflection points on the pressure side of the airfoil includes a second curvature inflection point located at 0% span of the airfoil and between 60% and 70% of the axial chord length, a third curvature inflection point located at 25% span of the airfoil and between 50% and 60% of the axial chord length, a fourth curvature inflection point located at 75% span of the airfoil and between 30% and 40% of the axial chord length, and a fifth curvature inflection point located at 90% span of the airfoil and between 30% and 40% of the axial chord length.
7. The component of claim 6 , wherein the second curvature inflection point located at 0% span of the airfoil is axially downstream of the first curvature inflection point located at 50% span of the airfoil.
8. The component of claim 1 , wherein the plurality of curvature inflection points includes another curvature inflection point located at 0% span of the airfoil that is axially downstream of the first curvature inflection point located at 50% span of the airfoil.
9. 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 the array of airfoils are blades and extends from a platform to an unshrouded end and each airfoil includes:
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 plurality of curvature inflection points located on the pressure side of the airfoil between 30% and 70% of an axial chord length of the airfoil, a curvature inflection point occurring at a span location with a smallest radius of curvature for the span location, the smallest radius of curvature is measured in an X-Y plane about an axis parallel to a radial direction of the airfoil, and the plurality of curvature inflection points includes a first curvature inflection point located at 75% span of the airfoil and between 30% and 40% of the axial chord length.
10. The gas turbine engine of claim 9 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 0% span of the airfoil and between 60% and 70% of the axial chord length.
11. The gas turbine engine of claim 9 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 25% span of the airfoil and between 50% and 60% of the axial chord length.
12. The gas turbine engine of claim 9 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 50% span of the airfoil and between 40% and 50% of the axial chord length.
13. The gas turbine engine of claim 9 , wherein the plurality of curvature inflection points includes another curvature inflection point on the pressure side of the airfoil located at 90% span of the airfoil and between 30% and 40% of the axial chord length.
14. The gas turbine engine of claim 9 , wherein the plurality of curvature inflection points on the pressure side of the airfoil includes a second curvature inflection point located at 0% span of the airfoil and between 60% and 70% of the axial chord length, a third curvature inflection point located at 25% span of the airfoil and between 50% and 60% of the axial chord length, a fourth curvature inflection point located at 50% span of the airfoil and between 40% and 50% of the axial chord length, and a fifth curvature inflection point located at 90% span of the airfoil and between 30% and 40% of the axial chord length.
15. The gas turbine engine of claim 9 , wherein the plurality of curvature inflection points includes a second curvature inflection point located at 0% span of the airfoil that is axially downstream of a fourth curvature inflection point located at 50% span of the airfoil.
16. The gas turbine engine of claim 14 , wherein the second curvature inflection point located at 0% span of the airfoil is axially downstream of the fourth curvature inflection point at 50% span of the airfoil.