Gas turbine engine airfoil
An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.
1. An airfoil for a turbine engine comprising:
an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a leading edge dihedral and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.
2. The airfoil according to claim 1 , wherein the leading edge dihedral at the 0% span position is in the range of −3° to −12°.
3. The airfoil according to claim 2 , wherein the leading edge dihedral at the 0% span position is about −4°.
4. The airfoil according to claim 2 , wherein the leading edge dihedral at the 0% span position is about −10°.
5. The airfoil according to claim 2 , wherein the leading edge dihedral extends from the 0% span position to a 20% span position having a leading edge dihedral in a range of −2° to −6°.
6. The airfoil according to claim 5 , wherein the leading edge dihedral includes a first point at a 75% span position and extends generally linearly from the first point to a second point at the 85% span position.
7. The airfoil according to claim 6 , wherein the first point is in a range of −8° to −10° dihedral.
8. The airfoil according to claim 6 , wherein the second point is in a range of −3° to −6° dihedral.
9. The airfoil according to claim 2 , wherein a maximum negative dihedral is in a range of 95-100% span position.
10. The airfoil according to claim 9 , wherein a least negative dihedral is in a range of 5-15% span position.
11. The airfoil according to claim 2 , wherein a maximum negative dihedral is in a range of 65-75% span position.
12. The airfoil according to claim 11 , wherein a least negative dihedral is in a range of 0-10% span position.
13. The airfoil according to claim 2 , wherein a maximum negative dihedral is in a range of 50-60% span position.
14. The airfoil according to claim 1 , wherein the airfoil is a fan blade for a gas turbine engine.
15. The airfoil according to claim 1 , wherein the airfoil has a relationship between a trailing edge dihedral and a span position, the trailing edge dihedral positive from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.
16. The airfoil according to claim 15 , wherein the relationship provides a generally C-shaped curve from the 0% span position to a 50% span position and then a 90% span position.
17. The airfoil according to claim 16 , wherein a trailing edge dihedral at the 0% span position is in a range of 20° to 25°.
18. The airfoil according to claim 17 , wherein a trailing edge dihedral at about the 50% span position is in a range of 2° to 6°.
19. The airfoil according to claim 17 , wherein a trailing edge dihedral at the 90% span position is in a range of 16° to 22°.
20. The airfoil according to claim 17 , wherein from a 65% span position to a 75% span position the trailing edge dihedral increases about 5°.
21. The airfoil according to claim 18 , wherein a positive-most trailing edge dihedral in a 80%-100% span position is within 5° of the trailing edge dihedral in the 0% span position.
22. The airfoil according to claim 17 , wherein a least positive trailing edge dihedral is in a 40%-55% span position.
23. The airfoil according to claim 16 , wherein the airfoil is a fan blade for a gas turbine engine.
24. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a low fan pressure ratio of less than 1.55;
a geared architecture coupling the fan section to the turbine section or compressor section; and
wherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a leading edge dihedral and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.
25. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section;
a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a low fan pressure ratio of less than 1.55;
a geared architecture coupling the fan section to the turbine section or compressor section; and
wherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a leading edge dihedral and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning, wherein the airfoil has a relationship between a trailing edge dihedral and a span position, the trailing edge dihedral positive from the 0% span position to the 100% span position.