An airfoil for a turbine engine includes pressure and suction sides that extend 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 total chord length and a span position and corresponds to a
An airfoil for a turbine engine includes pressure and suction sides that extend 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 total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm). The curve is at least a third order polynomial and has an initial positive slope.
대표청구항▼
1. An airfoil for a turbine engine comprising: 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 is a fan blade for a gas turbine engine, wherein the airfoil has a relations
1. An airfoil for a turbine engine comprising: 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 is a fan blade for a gas turbine engine, wherein the airfoil has a relationship between a total chord length and a span position corresponding to a curve having an increasing total chord length from the 0% span position to a first peak, the first peak occurs in the range of 45-65% span position, the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position, wherein the total chord length at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm), wherein the curve is at least a third order polynomial having an initial positive slope, and wherein the total chord length include a maximum differential between the maximum and minimum chord lengths along the entire span in the range of 3.0-4.0 inches (7.6-10.2 cm). 2. The airfoil according to claim 1, wherein the peak is provided by a first critical point in a range of 60-65% span position. 3. The airfoil according to claim 2, wherein a negative slope extends from the critical point to a second critical point in a range of 80-90% span position. 4. The airfoil according to claim 3, wherein the second critical point has an L/Rd ratio in the range of 0.32 to 0.35. 5. The airfoil according to claim 3, wherein a positive slope extends from the second critical point to the 100% span position, the total chord length at the 100% span position less than the total chord length at the peak. 6. The airfoil according to claim 1, wherein the peak is provided by a critical point in a range of 40-50% span position. 7. The airfoil according to claim 6, wherein a negative slope extends from the critical point to the 100% span position. 8. The airfoil according to claim 7, wherein the negative slope is constant from about a 55% span position to the 100% span position. 9. The airfoil according to claim 6, wherein the critical point has an L/Rd ratio in the range of 0.39 to 0.43. 10. An airfoil for a turbine engine comprising: 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 total chord length and a span position corresponding to a curve having an increasing total chord length from the 0% span position to a first peak, the first peak occurs in the range of 45-65% span position, the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position, wherein the total chord length at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm), wherein the curve is at least a third order polynomial having an initial positive slope, wherein the peak is provided by a critical point in a range of 50-60% span position, wherein a slope from the critical point to an inflection point is substantially zero, the inflection point in a range of 70-80% span position. 11. The airfoil according to claim 10, wherein a positive slope extends from the inflection point to the 100% span position. 12. The airfoil according to claim 11, wherein the 100% span position has an L/Rd ratio in the range of 0.38 to 0.42. 13. The airfoil according to claim 11, wherein the positive slope extending from the inflection point to the 100% span position is constant. 14. A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section;a fan section has a low fan pressure ratio of less than 1.55; andwherein 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 total chord length and a span position corresponding to a curve having an increasing total chord length from the 0% span position to a first peak, the first peak occurs in the range of 45-65% span position the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position, wherein the total chord length at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm), wherein the curve is at least a third order polynomial having an initial positive slope; and wherein the peak is provided by a critical point in a range of 50-60% span position, wherein a slope from the critical point to an inflection point is substantially zero, the inflection point in a range of 70-80% span position. 15. The gas turbine engine according to claim 14, comprising a geared architecture coupling the fan section to the turbine section or compressor section, and wherein the fan section has an array of twenty-six or fewer fan blades. 16. The gas turbine engine according to claim 14, wherein the low fan pressure ratio is less than 1.52. 17. The gas turbine engine according to claim 16, wherein the low fan pressure ratio is less than 1.50. 18. The gas turbine engine according to claim 17, wherein the low fan pressure ratio is less than 1.48. 19. The gas turbine engine according to claim 18, wherein the low fan pressure ratio is less than 1.46. 20. The gas turbine engine according to claim 19, wherein the low fan pressure ratio is less than 1.44.
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