Gas turbine engine airfoil
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
1. A compressor airfoil of a turbine engine having a geared architecture comprising:
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 trailing edge angle and span position that defines a non-linear curve with a non-negative slope from 0% span to 60% span corresponding to a non-decreasing trailing edge angle.
2. The compressor airfoil according to claim 1 , wherein the curve has a non-negative slope from 0% span to 80% span.
3. The compressor airfoil according to claim 2 , wherein the curve has a non-negative slope from 0% span to 100% span.
4. A compressor airfoil of a turbine engine having a geared architecture comprising:
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 trailing edge angle and span position that defines a curve with a positive slope from 0% span to 100% span.
5. 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 the compressor section; and
an airfoil arranged in the compressor section and including pressure and suction sides and extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a trailing edge angle and span position that defines a non-linear curve with a non-negative slope from 0% span to 60% span corresponding to a non-decreasing trailing edge angle.
6. The gas turbine engine according to claim 5 , wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged immediately upstream of the combustor section.
7. The gas turbine engine according to claim 6 , wherein the airfoil is provided in a compressor outside the high pressure compressor.
8. The gas turbine engine according to claim 7 , wherein the low pressure compressor is counter-rotating relative to the fan blades.
9. The gas turbine engine according to claim 7 , wherein the gas turbine engine is a two-spool configuration.
10. The gas turbine engine according to claim 7 , wherein the low pressure compressor is immediately downstream from the fan section.
11. The gas turbine engine according to claim 6 , wherein the airfoil is fixed relative to an engine static structure.
12. The gas turbine engine according to claim 5 , wherein the curve has a non-negative slope from 0% span to 80% span.
13. The gas turbine engine according to claim 12 , wherein the curve has a non-negative slope from 0% span to 100% span.
14. 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 the compressor section; and
an airfoil arranged in the compressor section and including pressure and suction sides and extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a trailing edge angle and span position that defines a curve with a positive slope from 0% span to 100% span.