Patent ID: 9458723
Filing Date: 2016-10-04
CPC Classification: F01D,F05D

Claim Text:
1. A turbine blade of a gas turbine engine having a gaspath, the turbine blade comprising an airfoil having an intermediate portion contained within the gaspath and defined by a nominal un-coated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 2 to 13 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine blade, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z, wherein X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile section, the profile sections at the Z distances being joined smoothly with one another to form an airfoil shape of the intermediate portion, wherein the turbine blade has a manufacturing tolerance of ±0.015 inches in a direction perpendicular to the airfoil.