Patent ID: 11867081
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A turbine blade for a gas turbine engine, the turbine blade comprising:
an airfoil having a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending from a platform in a spanwise direction to a tip; and
wherein the external airfoil surface is formed in substantial conformance with cross-section profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the set of Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.