Gas turbine engine airfoil
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
1. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section, the compressor section and the turbine section rotatable about an engine axis, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged upstream of the combustor section;
a fan section having an array of twenty-six or fewer fan blades, wherein the low pressure compressor is downstream from the fan section; and
an airfoil arranged in the low pressure compressor and including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear, the tangential stacking offset measured in a direction perpendicular to the engine axis, wherein the curve transitions from a positive slope to a negative slope in a range of 60% span to 75% span.
2. The gas turbine engine according to claim 1 , wherein the gas turbine engine is a two-spool configuration.
3. The gas turbine engine according to claim 1 , wherein the airfoil is rotatable relative to an engine static structure.
4. The gas turbine engine according to claim 1 , wherein the curve has a negative slope from 90% span to 100% span.
5. The gas turbine engine according to claim 4 , wherein the curve has a negative slope from 80% span to 100% span.
6. The gas turbine engine according to claim 1 , wherein the curve has a positive slope beginning at 0% span, where the positive slope leans toward the suction side.
7. The gas turbine engine according to claim 6 , wherein the positive slope extends from 0% span to 40% span.
8. The gas turbine engine according to claim 1 , wherein the low pressure compressor is counter-rotating relative to the fan blades.
9. The gas turbine engine according to claim 1 , wherein the fan section has a fan pressure ratio of less than 1.55.
10. The gas turbine engine according to claim 1 , wherein the positive slope leans toward the suction side and the negative slope leans toward the pressure side.
11. A gas turbine engine comprising:
a compressor section and a turbine section rotatable about an engine axis;
a combustor section arranged between the compressor section and the turbine section;
a fan section, wherein the compressor section is downstream from the fan section;
an airfoil arranged in the compressor section and including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear, the tangential stacking offset measured in a direction perpendicular to the engine axis, wherein the curve transitions from a positive slope to a negative slope in a range of 60% span to 75% span.
12. The gas turbine engine according to claim 11 , wherein the fan section has an array of twenty-six or fewer fan blades.
13. The gas turbine engine according to claim 12 , wherein the compressor section includes a low pressure compressor section and a high pressure compressor section, and the low pressure compressor is counter-rotating relative to the fan blades.
14. The gas turbine engine according to claim 11 , wherein the airfoil is rotatable relative to an engine static structure.
15. The gas turbine engine according to claim 11 , wherein the positive slope leans toward the suction side and the negative slope leans toward the pressure side.
16. The gas turbine engine according to claim 15 , wherein the curve has a negative slope from 80% span to 100% span.
17. The gas turbine engine according to claim 15 , wherein the curve has a positive slope from 0% span to 40% span.
18. The gas turbine engine according to claim 11 , wherein the fan section has a fan pressure ratio of less than 1.55.
19. The gas turbine engine according to claim 11 , further comprising a geared architecture coupling the fan section to the turbine section.
20. The gas turbine engine according to claim 19 , wherein the geared architecture has a gear ratio greater than 2.3.