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US 10,502,229 B2Granted
Gas turbine engine airfoil
AssigneeUnited Technologies Corporation
InventorsEdward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
Life of this patent
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Abstract
An airfoil of a turbine engine 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 leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span.
Claims16
A gas turbine engine comprising:
- a combustor section arranged between a compressor section and a turbine section, 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 fan section has a fan pressure ratio of less than 1.55, wherein the low pressure compressor is counter-rotating relative to the fan blades, wherein the low pressure compressor is downstream from the fan section;
- a geared architecture coupling the fan section to the turbine section or the compressor section;
- and
- an airfoil provided in a compressor outside the high pressure compressor section, wherein the airfoil is rotatable relative to an engine static structure, the airfoil 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 leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span wherein the leading edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the leading edge.
2 more elements
A gas turbine engine comprising:
- a combustor section arranged between a compressor section and a turbine section, 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 fan section has a fan pressure ratio of less than 1.55, wherein the low pressure compressor is counter-rotating relative to the fan blades, wherein the low pressure compressor is downstream from the fan section;
- a geared architecture coupling the fan section to the turbine section or the compressor section;
- and
- an airfoil provided in a compressor outside the high pressure compressor section, wherein the airfoil is rotatable relative to an engine static structure, the airfoil 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 trailing edge angle and span position that includes a curve with a non-positive slope from 90% span to 100% span, wherein the trailing edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the trailing edge.
2 more elements
Dependencies are inferred from the claim text.