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US 10,590,775 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
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Abstract
An airfoil of a turbine engine 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 stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.
Claims9
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 low fan pressure ratio of less than 1.55, wherein the low pressure compressor is downstream from the fan section, wherein the low pressure compressor is counter-rotating relative to the fan blades;
- and
- an airfoil including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil is arranged in the low pressure compressor, wherein the airfoil has a relationship between a stagger angle and span position that defines a curve, the stagger angle of the curve is greater than 32° but less than 40° from a 90% span position to the 100% span position, wherein the stagger angle is less than 40° along entire span of the airfoil.
1 more element
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 low fan pressure ratio of less than 1.55, wherein the low pressure compressor is downstream from the fan section;
- and
- an airfoil including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil is arranged in the low pressure compressor, wherein the airfoil has a relationship between a stagger angle and span position that defines a curve, the stagger angle of the curve is greater than 32° but less than 40° from a 90% span position to the 100% span position, wherein the stagger angle has a maximum at the 100% span position, and wherein the stagger angle is less than 40° along the entire span of the airfoil.
1 more element
Dependencies are inferred from the claim text.