GAS TURBINE ENGINE AIRFOIL
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential trailing edge position and span position that defines a curve with a non-positive slope from 90% span to 100% span. The non-positive slope corresponds to a pressure side-leaning trailing edge.
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 tangential trailing edge position and span position that defines a curve with a non-positive slope from 90% span to 100% span, the non-positive slope corresponding to a pressure side-leaning trailing edge.
2 . The compressor airfoil according to claim 1 , wherein the curve has a negative slope from 90% span to 100% span.
3 . The compressor airfoil according to claim 2 , wherein the curve has a negative slope from 80% span to 100% span.
4 . The compressor airfoil according to claim 2 , wherein the curve has a positive slope preceding the negative slope, the positive slope corresponding to a suction side-leaning trailing edge, where a transition between the positive and negative slope is in a range of 65% span to 95% span.
5 . The compressor airfoil according to claim 4 , wherein the transition is in a range of 75% span to 90% span.
6 . The compressor airfoil according to claim 1 , wherein the airfoil has a relationship between a tangential leading edge position and span position that includes another curve with a negative slope from 0% span to 30% span, the negative slope of the other curve corresponding to a pressure side-leaning leading edge.
7 . 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 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 extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a tangential trailing edge position and span position that includes a curve with a non-positive slope from 90% span to 100% span, the non-positive slope corresponding to a pressure side-leaning trailing edge.
8 . The gas turbine engine according to claim 7 , 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.
9 . The gas turbine engine according to claim 8 , wherein the airfoil is provided in a compressor outside the high pressure compressor.
10 . The gas turbine engine according to claim 9 , wherein the low pressure compressor is counter-rotating relative to the fan blades.
11 . The gas turbine engine according to claim 9 , wherein the gas turbine engine is a two-spool configuration.
12 . The gas turbine engine according to claim 9 , wherein the low pressure compressor is immediately downstream from the fan section.
13 . The gas turbine engine according to claim 8 , wherein the airfoil is rotatable relative to an engine static structure.
14 . The gas turbine engine according to claim 7 , the curve has a negative slope from 90% span to 100% span.
15 . The gas turbine engine according to claim 14 , wherein the curve has a negative slope from 80% span to 100% span.
16 . The gas turbine engine according to claim 14 , wherein the curve has a positive slope preceding the negative slope, the positive slope corresponding to a suction side-leaning trailing edge, where a transition between the positive and negative slope is in a range of 65% span to 95% span.
17 . The gas turbine engine according to claim 16 , wherein the transition is in a range of 75% span to 90% span.
18 . The gas turbine engine according to claim 7 , wherein the airfoil has a relationship between a tangential leading edge position and span position that includes another curve with a negative slope from 0% span to 30% span, the negative slope of the other curve corresponding to a pressure side-leaning leading edge.