US 11,898,459 B1
Turbine blade cooling hole arrangement
Emma J. Place, New Hartford, CT (US); Dominic J. Mongillo, Jr., West Hartford, CT (US); and Jeremy B Fredette, West Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jul. 1, 2022, as Appl. No. 17/856,332.
Claims priority of provisional application 63/217,949, filed on Jul. 2, 2021.
Int. Cl. F01D 5/18 (2006.01); F01D 5/02 (2006.01)
CPC F01D 5/186 (2013.01) [F01D 5/02 (2013.01); F05D 2220/3212 (2013.01); F05D 2230/21 (2013.01); F05D 2250/74 (2013.01); F05D 2260/202 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in an airfoil of the turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on the turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of the turbine blade.