Gas turbine engine airfoil
A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0° view. The various views include the 0° view which projects into an axial plane in the axial direction. A 90° view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0° and 90° views. The airfoil has a maximum leading edge projection in a 20° to 40 ° view. The radial direction is normal to the axial and tangential directions.
1. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section that extend in an axial direction;
a fan section arranged upstream from the compressor section; and
an airfoil that is arranged in one of the fan section, the compressor section and the turbine section, the airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views, the plane is parallel with the axial direction in a 0° view, the various views include the 0° view which projects into an axial plane in the axial direction, a 90° view which projects into a tangential plane in a tangential direction normal to the axial direction, and views between the 0° and 90° views, wherein the airfoil has a maximum leading edge projection in a 20° to 40° view, and wherein the radial direction is normal to the axial and tangential directions.
2. The gas turbine engine according to claim 1 , wherein the maximum leading edge projection is in a 30° view.
3. The gas turbine engine according to claim 2 , wherein the maximum leading edge projection is in a range of 35% to 55% span position.
4. The gas turbine engine according to claim 1 , wherein the airfoil is a fan blade in the fan section.
5. The gas turbine engine according to claim 4 , wherein the fan blade is a composite blade.
6. The gas turbine engine according to claim 5 , wherein the composite blade is a swept blade.