公开(公告)号：US11898459B1

公开(公告)日：2024-02-13

申请号：US17856332

申请日：2022-07-01

Applicant: Raytheon Technologies Corporation

Inventor： Emma J. Place ,  Dominic J. Mongillo, Jr. ,  Jeremy B Fredette

IPC: F01D5/18 ,  F01D5/02

CPC classification number: F01D5/186 ,  F01D5/02 ,  F05D2220/3212 ,  F05D2230/21 ,  F05D2250/74 ,  F05D2260/202

Abstract: Disclosed is a turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes being 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.