Gas turbine engine airfoil
AssigneeRtx 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 for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.
Claims18
A rotor for a gas turbine engine comprising:
- an airfoil including a pressure side and a suction side extending in a radially outward direction from a 0% span position to a 100% span position;
- wherein the rotor is configured to rotate about an axis when mounted in a gas turbine engine;
- wherein the airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to the axis;
- wherein the airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span;
- and
- wherein the stagger angle at 100% span is greater than the stagger angle at 50% span and the stagger angle at 0% span.
A gas turbine engine comprising:
- a fan section including a fan;
- a compressor section including a low pressure compressor and a high pressure compressor;
- a turbine section including a low pressure turbine and a high pressure turbine, the low pressure turbine coupled to the fan;
- wherein the compressor section includes an airfoil rotatable about an engine longitudinal axis, the airfoil including a pressure side and a suction side extending in a radially outward direction from a 0% span position to a 100% span position;
- wherein the airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to the engine longitudinal axis;
- wherein the airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span;
- and
- wherein the stagger angle at 100% span is greater than the stagger angle at 50% span and the stagger angle at 0% span.
Dependencies are inferred from the claim text.