Airfoil thickness profile for minimizing tip leakage flow
A turbine engine assembly includes at least one rotor that has a plurality of blades, each of the blades includes an airfoil that has a pressure side and a suction side that each extend between a leading edge, a trailing edge, a tip and a base. The airfoil has a thickness between the pressure side and the suction side perpendicular to a camber line that varies between the leading edge and the trailing edge. The thickness includes a suction side thickness between the camber line and the suction side and a pressure side thickness between the camber line and the pressure side. A maximum ratio of the pressure side thickness to the suction side thickness is between 3 and 7.
1. A turbine engine assembly comprising:
at least one rotor having a plurality of blades, wherein each blade includes;
an airfoil having;
a pressure side and a suction side that each extend between a leading edge, a trailing edge, a tip, and a base; and
a thickness between the pressure side and the suction side perpendicular to a line of curvature that defines a curvature of the airfoil, wherein the thickness varies between the leading edge and the trailing edge, wherein the thickness comprises a suction side thickness between the line of curvature and the suction side and a pressure side thickness between the line of curvature and the pressure side, wherein a ratio of the pressure side thickness to the suction side thickness continually increases from the leading edge toward a maximum ratio of the pressure side thickness to the suction side thickness and the maximum ratio of the pressure side thickness to the suction side thickness is between 3 and 7.
2. The turbine engine assembly as recited in claim 1 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is disposed between 80% and 100% of a height of the airfoil between the base and the tip.
3. The turbine engine assembly as recited in claim 2 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is at a location between 5% and 40% of a meridional length between the leading edge and the trailing edge.
4. The turbine engine assembly as recited in claim 2 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is at a location between 10% and 30% of a meridional length between the leading edge and the trailing edge.
5. The turbine engine assembly as recited in claim 1 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is between 5 and 7.
6. The turbine engine assembly as recited in claim 3 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is 6.
7. The turbine engine assembly as recited in claim 6 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is at a location that is between 15% and 25% of the meridional length between the leading edge and the trailing edge.
8. The turbine engine assembly as recited in claim 1 , wherein the at least one rotor comprises a compressor rotor.
9. The turbine engine assembly as recited in claim 1 , wherein the at least one rotor comprises a turbine rotor.
10. A blade for compressor section of a turbine engine assembly comprising:
an airfoil having a pressure side and a suction side that each extend between a leading edge, a trailing edge, a tip and a base, the airfoil having a thickness between the pressure side and the suction side perpendicular to a line of curvature that defines a curvature of the airfoil, wherein the thickness that varies between the leading edge and the trailing edge, wherein the thickness comprises a suction side thickness between the line of curvature and the suction side and a pressure side thickness between the line of curvature and the pressure side, wherein a ratio of the pressure side thickness to the suction side thickness continually increases from the leading edge toward a maximum ratio of the pressure side thickness to the suction side thickness and the maximum ratio of the pressure side thickness to the suction side thickness is between 3 and 7.
11. The blade as recited in claim 10 , wherein the ratio of the pressure side thickness to the suction side thickness is disposed between 80% and 100% of a height of the airfoil between the base and the tip.
12. The blade as recited in claim 11 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is at a location between 5% and 40% of a meridional length between the leading edge and the trailing edge.
13. The blade as recited in claim 11 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is at a location between 10% and 30% of a meridional length between the leading edge and the trailing edge.
14. The blade as recited in claim 10 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is between 5 and 7.
15. The blade as recited in claim 10 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is 6.
16. The blade as recited in claim 15 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is at a location that is between 15% and 25% of the meridional length between the leading edge and the trailing edge.
17. A method of forming a blade utilized in a turbine engine assembly, the method comprising:
forming an airfoil of the blade to include a thickness between a pressure side and a suction side that is perpendicular to a line of curvature that defines a curvature of the airfoil, wherein the thickness includes a suction side thickness between the line of curvature and the suction side and a pressure side thickness between the line of curvature and the pressure side such that a ratio of the pressure side thickness to the suction side thickness continually increases from the leading edge toward a maximum ratio of the pressure side thickness to the suction side thickness and the maximum ratio of the pressure side thickness to the suction side thickness is between 3 and 7.
18. The method as recited in claim 17 , further comprising locating the maximum ratio of the pressure side thickness to the suction side thickness within a location between 80% and 100% of a height of the airfoil between a base and a tip portion.
19. The method as recited in claim 18 , further comprising locating the maximum ratio of the pressure side thickness to the suction side thickness within a location between 5% and 40% of a meridional length between a leading edge and a trailing edge.
20. The method as recited in claim 18 , wherein the maximum ratio of the pressure side thickness to the suction side thickness is between 5 and 7 and is within a location between 15% and 25% of the meridional length between a leading edge and a trailing edge.