Patent ID: 9546556
Date: 2017-01-17
CPC Classifications: F01D

Claim:
1. A turbine blade for a gas turbine engine comprising: an airfoil extending in a first radial direction from a platform; and a root extending from the platform in a second radial direction and having opposing lateral sides providing a firtree-shaped contour, the contour including first, second and third lobes on each of the lateral sides and that tapers relative to the radial direction away from the platform, the first, second and third lobes each provide contact surfaces arranged at about 45° relative to the radial direction, and a contact plane on each lateral side at an angle of about 11° relative to the radial direction defining a contact point on each of the contact surfaces, the first, second and third lobes each include first, second and third grooves that are substantially aligned with one another along an offset plane spaced a uniform offset distance from the contact plane.