公开(公告)号：US11781433B1

公开(公告)日：2023-10-10

申请号：US18077824

申请日：2022-12-08

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Yanhu Guo ,  Nelson D. Gonzalez

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2240/307 ,  F05D2250/74 ,  F05D2260/202

Abstract: A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. Further, the plurality of cooling holes are positioned at specific locations to improve film-cooling of the turbine blade while reducing negative impacts on performance of the turbine blade.