公开(公告)号：US11885235B2

公开(公告)日：2024-01-30

申请号：US17651179

申请日：2022-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Alex D. Wong ,  Yanhu Guo

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/22141

Abstract: An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

公开(公告)号：US20230258090A1

公开(公告)日：2023-08-17

申请号：US17651179

申请日：2022-02-15

Applicant: Raytheon Technologies Corporation

Inventor： Carlos Calixtro ,  Alex D. Wong ,  Yanhu Guo

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2260/202

Abstract: An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.