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

Claim 12:
13. A gas turbine engine comprising:
a low pressure (LP) turbine configured to drive a low pressure compressor;
wherein the LP turbine comprises at least one stage of turbine blades, wherein at least one of the turbine blades of the at least one stage comprises an airfoil having leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a span 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 and trailing edges at the span location.