Patent ID: 9599064
Date: 2017-03-21
CPC Classifications: F01D,F02C,F02K,F04D,F05D,Y02T

Claim:
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 chord length 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 maximum chord length projection is in about a 40° view that is in a range of 60% to 70% span position, and wherein the radial direction is normal to the axial and tangential directions.