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