US 12,345,174 B1
Turbine engine airfoil
Abdulhalim Twahir, La Prairie (CA); Panagiota Tsifourdaris, Montreal (CA); and Daniel Lecuyer, St-Bruno-de-Montarville (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Jun. 14, 2024, as Appl. No. 18/744,196.
Int. Cl. F01D 5/14 (2006.01)
CPC F01D 5/141 (2013.01) [F05D 2240/12 (2013.01); F05D 2250/74 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An apparatus for a turbine engine, comprising:
an airfoil including a first end, a second end, a leading edge, a trailing edge, a pressure side and a suction side;
the leading edge and the trailing edge joined by the pressure side and the suction side to provide an exterior airfoil surface extending in a spanwise direction from the first end of the airfoil to the second end of the airfoil;
the exterior airfoil surface formed in conformance with a plurality of cross-section profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1;
the 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; and
the local axial chord corresponding to a width of the airfoil between the leading edge and the trailing edge at the span location.